УСТРОЙСТВО ДЛЯ ОТБОРА ПРОБЫ ГАЗА В ВЫСОКОЭНТАЛЬПИЙНЫХ УСТАНОВКАХ КРАТКОВРЕМЕННОГО ДЕЙСТВИЯ И СПОСОБ ИЗМЕРЕНИЯ РАСХОДА ГАЗА С ИСПОЛЬЗОВАНИЕМ ЭТОГО УСТРОЙТСВА

Изобретение относится к технике исследования свойств и состава рабочего газа в высокоэнтальпийных установках кратковременного действия. Устройство для отбора пробы газа в высокоэнтальпийных установках кратковременного действия содержит герметично соединенные собственно пробоотборник с заостренной передней кромкой и расширяющимся внутренним каналом. Устройство включает также пироклапан, в корпусе которого размещены поршень клапана, узел подключения управляющих высоковольтных проводов для подрыва порохового заряда и выполнено перепускное отверстие в баллон для сбора и хранения пробы газа. Баллон для сбора пробы снабжен поршнем, а в канале пробоотборника установлена теплопроводная вставка с развитой площадью внутренних поверхностей. При этом узел подключения управляющих высоковольтных проводов для подрыва порохового заряда установлен в аэродинамической тени пироклапана и дополнительно снабжен двухэлектродной системой, а в корпусе пироклапана выполнено дренажное отверстие для сброса давления ...

УСТРОЙСТВО И СПОСОБ АНАЛИЗА ИЗМЕРЕНИЙ В АЭРОДИНАМИЧЕСКОЙ ТРУБЕ

Изобретения относятся к экспериментальной аэродинамике и могут быть использованы для проведения измерений в аэродинамической трубе. Устройство содержит процессор, который выполнен с возможностью осуществления следующих стадий измерений: автоматической идентификации и/или сегментации, по меньшей мере, одного элемента потока с помощью процессора посредством использования записанного изображения, основанного на цветовых оттенках, по меньшей мере, одного элемента потока, при этом изображение записано в процессе проведения измерений в аэродинамической трубе, и вычислении геометрических характеристик, по меньшей мере, одного элемента потока на основании изображения, по меньшей мере, одного элемента потока. Способ содержит следующие стадии: автоматическую идентификацию и/или сегментацию, по меньшей мере, одного элемента потока, с помощью процессора посредством использования записанного изображения, основанного на цветовых оттенках, по меньшей мере, одного элемента потока, причем изображение записано ...

ИЗМЕРИТЕЛЬНАЯ СИСТЕМА ДЛЯ КОНТРОЛЯ ТЕХНОЛОГИЧЕСКИХ СИСТЕМ АЭРОДИНАМИЧЕСКОЙ ТРУБЫ

Изобретение относится к области измерительной техники и промышленной электроники и может быть использовано для управления оборудованием технологических систем аэродинамической трубы (АДТ). Устройство содержит измерительные датчики, установленные в модель летательного аппарата, испытываемой в аэродинамической трубе, измерительные датчики и датчики дискретных сигналов, установленные в технологических системах аэродинамической трубы, оборудование, включающее компьютер, блок питания, 6-канальный тензометрический интегрирующий аналого-цифровой преобразователь для измерения сигналов с тензорезисторных датчиков, 32-канальный быстродействующий аналого-цифровой преобразователь для измерения сигналов датчиков, имеющих нормированное выходное напряжение, 4-канальный измеритель частоты для измерения сигналов датчиков с частотным выходом, 8-канальный блок вывода дискретных сигналов для управления первичными измерительными преобразователями, два 32-канальных аналого-цифровых преобразователя для измерения ...

Тензометрический динамометр

Полезная модель относится к области аэромеханических измерений и может быть использована в устройстве специализированных тензометрических динамометров (ТД) - т.н. тензометрических весов, применяемых для определения составляющих (компонент) векторов аэрогазодинамической силы и момента, действующих на модели испытуемых объектов (в том числе модели летательных аппаратов) в потоке аэрогазодинамических установок. Устройство содержит жесткие силовводящий и силовыводящий элементы для взаимодействия с испытуемым объектом и жесткой опорой, в которых выполнены гнезда для размещения соединяющих их тензометрических элементов с упругой измерительной системой в виде связанных между собой посредством концевых и промежуточных оснований упругих параллелограммов с парами поперечных и продольных упругих балок, ориентированных в соответствии с заданной системой координат, и тензопреобразователи, соответственно установленные на чувствительных элементах параллелограммов и соединенные в мостовые измерительные ...

ДИНАМОМЕТРИЧЕСКИЙ ЭЛЕМЕНТ

Изобретение относится к области аэромеханических измерений и может быть использовано для измерения составляющих векторов аэродинамической силы и момента, действующих на модели летательных аппаратов, судов, испытываемых в аэродинамических трубах, опытовых бассейнах и гидроканалах. Динамометрический элемент состоит из двух оснований - левого и правого, которые связаны между собой упругим шарниром, образованным двумя пакетами балок, и чувствительным элементом, расположенным между пакетами. Отличительной особенностью элемента являются балки пакетов упругого шарнира, выполненные переменными по длине таким образом, что количественные значения их длин изменяются по линейному закону в зависимости от расстояния балки до продольной оси упругого шарнира. Высоты балок также изменяются в зависимости от их длины. Причем отношение высот любых двух соседних балок равно отношению квадратов их длин. Технический результат заключается в расширении диапазона и повышении точности измерений. 4 ил., 3 табл.

ИЗМЕРИТЕЛЬНО-УПРАВЛЯЮЩИЙ ВЫЧИСЛИТЕЛЬНЫЙ КОМПЛЕКС АЭРОДИНАМИЧЕСКОЙ ТРУБЫ

... 1. Измерительно-управляющий вычислительный комплекс аэродинамической трубы, содержащий аэродинамическую трубу, объект испытаний, размещенный в ней на тензометрических весах, закрепленных на программно-управляемой исполнительными механизмами державке, аналоговые датчики давления и температуры, датчики перемещения, расположенные на осях приводов исполнительных механизмов, цифровые датчики давления и оборудование в стандарте VME, включающее тензометрический модуль, модуль аналого-цифрового ввода-вывода, модуль измерения частоты, модуль дискретного вывода, процессорный модуль; при этом тензометрические весы соединены аналоговыми линиями связи с тензометрическим модулем, приводы исполнительных механизмов соединены цифровыми линиями связи с модулем дискретного вывода, аналоговые датчики давления и температуры соединены аналоговыми линиями связи с модулем аналого-цифрового ввода-вывода, цифровые датчики давления соединены цифровыми линиями связи с модулем измерения частоты; притом все оборудование ...

СТЕНД ДЛЯ ИЗМЕРЕНИЯ ВЕРТИКАЛЬНОЙ НАГРУЗКИ, ВОЗДЕЙСТВУЮЩЕЙ НА ОБЪЕКТ АВИАЦИОННОЙ ТЕХНИКИ

... 1. Стенд для измерения вертикальной нагрузки, воздействующей на объект авиационной техники, содержащий динамометрическую платформу с закрепленным на ней объектом, установленную посредством гибких стоек на неподвижную опорную раму с возможностью перемещения платформы по трем ортогональным осям, отличающийся тем, что объект закреплен на платформе при помощи пилона, гибкие стойки включают в средней части жесткие участки, где на жестких участках установлены трехкомпонентные пьезоэлектрические датчики виброускорений со встроенными усилителями напряжения, причем одна из трех ортогональных измерительных осей каждого датчика направлена вдоль гибкой стойки, усилители напряжения через кабели подключены к источникам питания, а источники питания через кабели подсоединены к регистратору-анализатору сигналов напряжений.2. Стенд по п.1, отличающийся тем, что платформа с объектом и опорная рама установлены в барокамере.

СПОСОБ ВИЗУАЛИЗАЦИИ ТЕЧЕНИЯ ГАЗА ИЛИ ЖИДКОСТИ НА ПОВЕРХНОСТИ ОБЪЕКТА ПРИ ОГРАНИЧЕННОМ РАЗРЕШЕНИИ ПРИЕМНИКА ИЗОБРАЖЕНИЙ

Изобретение относится к области экспериментальной аэро- и гидродинамики, в частности к оптическим способам исследований структуры потока газа или жидкости на поверхности объектов, и может быть использовано для визуализации течения газа или жидкости на поверхности подвижных объектов. Исследуемую поверхность объекта покрывают слоем вязкой жидкости, на которую наносят оптически инородные твердые частицы в виде плоских тел, размер которых соизмерим с пространственным разрешением приемника изображения, а толщина меньше толщины слоя вязкой жидкости. Под действием внешнего потока частицы перемещаются вместе с вязкой жидкостью, не меняя своего состояния. При интересующем режиме потока газа или жидкости с помощью приемника изображений регистрируют два или более последовательных изображений распределения твердых частиц на исследуемой поверхности объекта. Анализируя зарегистрированную последовательность изображений, определяют параметры движения твердых частиц и из полученных параметров восстанавливают ...

СПОСОБ ОПРЕДЕЛЕНИЯ РАСХОДНОЙ ХАРАКТЕРИСТИКИ ГИДРАВЛИЧЕСКОГО ТРАКТА ПРИ ТУРБУЛЕНТНОМ РЕЖИМЕ ИСТЕЧЕНИЯ

Изобретение относится к способам и устройствам, используемым для расчета пропускной способности проектируемых гидравлических трактов транспортных и дозирующих систем в химической, нефтехимической, авиационной, текстильной, лакокрасочной и других отраслях промышленности, в частности узлов транспортирования клеевых составов в сборочных производствах с клеевыми соединениями. Предлагаемый способ реализуется путем проливки модели тракта с проектными конструктивами местных сопротивлений и участков соединительных трубопроводов длиной l≤Lс внутренними диаметрами dводопроводной водой посредством ее многократного порционного дозирования в мерную тару и взвешивания доз на электронных весах при различных величинах действующего напора H, ступенчато изменяемых от максимального (H) до минимального (H) значений и поддерживаемых во время каждой j-й операции проливки (j=l, 2 … n, n≈20 - число проливок в данном цикле измерений) на заданном постоянном уровне, и оперативного последовательного расчета для каждой ...

Устройство для исследования ближнего поля давления модели в аэродинамической трубе

Изобретение относится к области аэродинамики и предназначено для исследования ближнего поля давления модели при сверхзвуковом обтекании в аэродинамической трубе. Устройство содержит генератор ударной волны (модель), поверхность с нанесенным барочувствительным покрытием, расположенную параллельно потоку в ближней зоне модели летательного аппарата, ультрафиолетовые излучатели, как минимум, один регистратор сигнала от барочувствительного покрытия (цифровую камеру) для регистрации интенсивности люминесценции барочувствительного покрытия, в качестве поверхности для нанесения барочувствительного покрытия использован участок стенки рабочей части аэродинамической трубы. При этом длина, ширина участка с нанесенным покрытием, кратчайшее расстояние от стенки рабочей части аэродинамической трубы до носика модели, а также расстояние х от передней точки (носика) проекции модели на стенку трубы до участка с нанесенным барочувствительным покрытием определяются соответствующими выражениями, учитывающими ...

Способ измерения статического давления в ближнем поле летательного аппарата вне пограничного слоя в аэродинамических трубах

Изобретение относится к области аэродинамики и предназначено для исследования ближнего поля давления модели летательного аппарата (ЛА) при сверхзвуковом обтекании в аэродинамической трубе (АДТ). Способ реализуется следующим образом: модель ЛА закрепляют на ножевой державке к стенке РЧ АДТ с таким расчетом, чтобы обеспечить положение ударной волны (УВ) от носика модели ЛА, отраженной от ближайшей стенки РЧ АДТ, ниже по потоку относительно УВ от хвостовой части модели ЛА. В РЧ АДТ вне области пограничного слоя размещают измерительное устройство, содержащее набор насадков статического давления, подключенных к электронным манометрам и закрепленных на координатном устройстве, обеспечивающем возможность перемещения координатного устройства вдоль оси РЧ АДТ по заданному набору координат. В процессе испытаний посредством измерительного устройства проводят измерение распределения статического давления вдоль оси РЧ каждым из насадков статического давления. Проводят измерения параметров набегающего ...

УСТРОЙСТВО ДЛЯ АЭРОДИНАМИЧЕСКИХ ИСПЫТАНИЙ МОДЕЛИ С УПРАВЛЯЮЩИМИ СОПЛАМИ В СВОБОДНОМ ПОЛЕТЕ

Устройство для аэродинамических испытаний модели с управляющими соплами в свободном полете, содержащее поддон для закрепления модели на штоке метательного устройства, систему подвода сжатого газа к управляющему соплу и элементы уплотнения соплового отверстия модели, отличающееся тем, что, с целью повышения точности определения аэродинамических характеристик модели за счет снижения потерь управляющего газа и уменьшения возмущающих сил и моментов при отделении модели от поддона, оно снабжено шарнирно закрепленными на поддоне захватами и распорным кольцом, телескопически установленным на штоке и связанным с помощью тросов с корпусом метательного устройства, при этом захваты выполнены в виде подпружиненных двуплечих рычагов, одни плечи которых посредством распорного кольца, взаимодействующего с другими плечами двуплечих рычагов, поджаты к корпусу и к управляющим соплам модели, причем элементы уплотнения соплового отверстия модели закреплены на плечах двуплечих рычагов, контактирующих с управляющими ...

УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ АЭРОДИНАМИЧЕСКИХ СИЛ И МОМЕНТОВ ПРИ ПОДВОДЕ ГАЗА К МОДЕЛИ

Устройство для измерения аэродинамических сил и моментов при подводе газа к модели, содержащее поршень для крепления модели, выполненный с радиальными отверстиями и установленный на упругих элементах тензовесов, и закрепленные на державке трубопроводы для подвода газа, сообщающиеся с помощью радиально установленных пар сильфонов с радиальными отверстиями в поршне, отличающееся тем, что, с целью повышения чувствительности и достоверности опытных данных, продольные оси сильфонов размещены в поперечной плоскости, проходящей через центр жесткости упругих элементов тензовесов, а в поршне выполнены продольные каналы, соединяющие радиальные отверстия с полостями соответствующих сильфонов.

Способ измерения поверхностного трения

Изобретение относится к экспериментальной аэродинамике. Цель изобретения - повышение точности результатов измерений за счет исключения влияния погрешностей, вносимых градиентами давления и нестабильностью температуры Способ заключается в том, что измеряют поверхностное трение с помощью плавающего элемента аэродинамических тензорезисторных весов путем регистрации деформаций изгиба весового элемента Плавающий элемент устанавливают с зазором по его периметру, заполняют зазоры полимеризую- щимся студнем, в качестве которого применяют смесь силиконового масла и силиконового каучука в массовом соотношении 4:1. 1 зл. ф-лы, 1 ил.

СПОСОБ ОПРЕДЕЛЕНИЯ ДРОССЕЛЬНОЙ ХАРАКТЕРИСТИКИ МОДЕЛИ ВОЗДУХОЗАБОРНИКА

Изобретение относится к области экспериментальной аэродинамики и может быть использовано для испытаний моделей воздухозаборников в аэродинамических трубах. Цель изобретения - сокращение времени эксперимента. После перемещения регулируемого органа 3 модели с заданным шагом измеряют параметры дроссельной характеристики ν и f (коэффициенты восстановления полного давления и расхода воздуха), сравнивают измеренное значение ni с заранее заданным начальным значением νн , определяют на каждом шаге приращение длины характеристик и угла наклона касательной характеристики относительно значений этих приращений на предыдущем шаге, проверяют на каждом шаге наличие диагностического сигнала от индикатора 4 помпажа, фиксируют регулируемый орган 3 в течение заданного временного интервала и измеряют параметры ν и f при выполнении хотя бы одного из условий ni≥νн ΔL≥ΔLдоп Δθ≥Δθдоп и наличии сигнала от индикатора 4 помпажа, при наличии сигнала от индикатора 4 помпажа возвращают регулируемый орган 3 в исходное ...

ПРИЕМНИК ВОЗДУШНОГО ДАВЛЕНИЯ

Изобретение относится к области авиации, к устройствам для определения параметров полета летательных аппаратов или параметров потока в аэродинамических трубах, в частности для измерения трех компонент вектора скорости и статического давления. Устройство состоит из головной части с расположенными на ней приемными отверстиями, соединенными каналами со штуцерами, и присоединенной к ней с тыльной стороны державки. На поверхностях головной части и державки расположены турбулизаторы потока. В качестве турбулизаторов могут служить расположенные на поверхности приемника воздушных давлений выемки или выступы различной формы, а также ребра, полученные в результате сопряжения образующих поверхность головной части и державки элементов плоских или криволинейных поверхностей. Технический результат заключается в упрощении конструкции, расширении диапазона измерений, расширении области практического применения. 9 з.п. ф-лы, 10 ил.

Способ тепловых испытаний керамических обтекателей

Изобретение относится к способам воспроизведения аэродинамического теплового воздействия на обтекатель летательного аппарата в наземных условиях. Заявлен способ тепловых испытаний керамических обтекателей, который включает нагрев наружной поверхности по заданному режиму и измерение температуры. Для изделий из партии при нагреве синхронно с измерением температуры наружной и внутренней поверхностей регистрируются диаметральные перемещения в заданных сечениях. При этом температурный режим задается по температуре наружной поверхности, а для следующих изделий, подлежащих испытанию, в случае выхода из строя термопар в обратной связи тепловой режим задается по уровню диаметральных перемещений, полученных по результатам испытаний предыдущих изделий из партии. Причем качество испытания всей партии оценивается по разнице минимума и максимума всех результатов измерения диаметральных перемещений по всей партии. Технический результат - повышение точности контроля теплового нагружения керамических оболочек ...

АЭРОДИНАМИЧЕСКИЙ СТЕНД

Аэродинамический стенд, содержащий перегородку, в которой с помощью шарнирного узла размещено сопло, отличающийся тем, что, с целью повышения надежности работы, шарнирный узел выполнен в виде рамы, охватывающей сопло, двух пар цапф с подшипниками и снабжен уплотнениями, размещенными между соплом и рамой, и рамой и перегородкой, при этом пары цапф установлены взаимно перпендикулярно и одна пара размещена на сопле, а другая - на раме.

АЭРОДИНАМИЧЕСКИЕ ВЕСЫ

... 1. Аэродинамические весы, содержащие рычажную систему с весовыми элементами, соединенную с двумя траверсами, каждая из которых соединена с качалками поворотных рычагов, параллельных траверсам, и с передним узлом подвески модели, механизм изменения угла атаки, соединенный с помощью вертикальной тяги с контргрузом, расположенным в вертикальной плоскости симметрии весов, с задним узлом подвески модели, при этом передние узлы подвески модели размещены симметрично относительно вертикальной плоскости симметрии весов и посредством дополнительных тяг связаны с наклонными растяжками и с дополнительными контргрузами, причем одна из траверс посредством боковой тяги соединена с весовым элементом, отличающиеся тем, что, с целью повышения точности измерения аэродинамических нагрузок, действующих на модель, весы снабжены горизонтальной тягой, соединяющей траверсы между собой, при этом траверсы ориентированы перпендикулярно и симметрично относительно плоскости симметрии весов, причем соединение каждой ...

СПОСОБ ИССЛЕДОВАНИЙ ПАРАМЕТРИЧЕСКОГО РЕЗОНАНСА ПРИ АВТОКОЛЕБАНИЯХ ПО КРЕНУ АЭРОДИНАМИЧЕСКИХ МОДЕЛЕЙ

Способ исследований параметрического резонанса при автоколебаниях по крену аэродинамических моделей, включающий помещение модели в поток аэродинамической трубы, вывод ее на угол атаки, при котором возбуждаются автоколебания и изменение их параметров, отличающийся тем, что, с целью повышения точности моделирования реальных условий полета летательного аппарата за счет задания параметрических возмущений по углу атаки, после вывода модели на угол атаки задают колебательные перемещения ее по вертикали, с непрерывно изменяющейся частотой и измеряют частоту этих перемещений.

СТЕНД ДЛЯ АЭРОДИНАМИЧЕСКИХ И ДИНАМИЧЕСКИХ ИССЛЕДОВАНИЙ ЛЕТАТЕЛЬНЫХ АППАРАТОВ

Стенд для аэродинамических и динамических исследований летательных аппаратов, содержащий сопло, рабочую часть, диффузор и тросовую подвеску модели, отличающийся тем, что, с целью повышения достоверности результатов, на стенках рабочей части перпендикулярно оси стенда установлены горизонтальные направляющие с подвижными опорами, на которых закреплен трос, сочлененный с трехстепенным шарниром посредством втулки с роликами, обжимающими трос.

Устройство для определения аэродинамических нагрузок, действующих на оперение модели

... 1. Устройство для определения аэродинамических нагрузок, действующих на оперение модели, например модели со складными рулями и крыльями, содержащее модель объекта, установленную на хвостовой державке, закрепленной в стойке аэродинамической трубы (AT), и измерительное весовое устройство, соединяющее державку с испытуемой моделью, отличающееся тем, что измерительное весовое устройство представляет собой тензовесы рулей и тензовесы крыльев, установленных в хвостовом и крыльевом отсеках модели соответственно, измерительная поворотная консоль руля посажена на тензовесы рулей через специальный рулевой кронштейн, измерительная поворотная консоль крыла посажена на тензовесы крыльев через специальный крыльевой кронштейн, а остальные поворотные консоли оперений, кроме измерительных, жестко прикреплены к корпусу модели посредством соответствующих им стандартных рулевых и крыльевых кронштейнов, причем специальные и стандартные кронштейны имеют унифицированное посадочное место для осуществления замены ...

Способ тарировки пневмометрических зондов, используемых в периодически пульсирующих потоках

Аэродинамические тензометрические весы

Динамометр для испытания моделей в аэродинамической трубе

Аэродинамические весы

Устройство для измерения давления

Устройство для защиты модели от воздействия механических примесей при испытаниях в аэродинамических установках

Устройство для подачи воздуха на продувку пневмометрических насадков

Устройство для определения аэродинамических компонент (сил и момента) осесимметричных тел в потоке разряженного газа

Способ определения нулевых показаний аэродинамических весов

Устройство для определения сил светового давления на модели сложной формы

Устройство для измерения и регистрации скорости ударной волны в аэродинамических установках

Устройство для тарировки трубок стантона

NOZZLE FOR MEASURING DYNAMIC PRESSURE IN HYPERSONIC FREE-MOLECULE GAS FLOW

Шестикомпонентные аэродинамические весы

Способ устранения вредных рефлексов в оптических системах

Насадок термоанемометра

Устройство для исследования структуры электронного пучка

УСТРОЙСТВО ДЛЯ ИССЛЕДОВАНИЯ СТРУКТУРЫ ЭЛЕКТРОННОГО ПУЧКм, включающее электронную пушку, цилиндр Фарадея, объектив с щелевой диафрагмой, спектрограф, фотоэлектрический 'умножитель, усилитель-самописец и осциллограф,при этом выход фотоэлектрического умножителя, усилитель-самописец и гтервый вход осциллографа соединены,' последовательно, отличающееся тем, что, с целью повышения точности измерения скорости потока и функции распределения частиц газа по скоростям, оно снабжено зондом, чувствительный элемент которого выполнен в виде нити, натянутой перпендикулярно плоскости диафрагмы объектива и расположенной в одной плоскости с щелью, при этом зонд прикреплен к объективу и электрически соединен со вторым, входом осциллографа.

Весовой элемент для консольно закрепленных аэродинамических моделей

Устройство для измерения давлений на вращающихся объектах

INTEGRIERBARER TRAGFLÄCHENMESSAUFNEHMER FÜR DIE GESAMTTEMPERATUR

Verfahren und Vorrichtung zur Bestimmung von lokalen Dichteschwankungen in Grenzschichten eines umströmten Körpers

Kraftmesssystem, Verfahren zum Erfassen von Kräften und Momenten an einem rotierenden Körper und Windkanal mit einem darin angeordneten und zumindest einen Propeller aufweisenden Modell mit einem Kraftmesssystem

Ein Kraftmesssystem zum Erfassen von Kräften eines rotierenden Körpers (4) weist eine Kraftmesseinrichtung (8) auf, die an dem rotierenden Körper (4) angeordnet ist, sowie eine Positionserfassungeeinheit (14) zur Erfassung der Rotation des rotierenden Körpers (4) und eine Auswerteeinheit (10), die mit der Kraftmesseinrichtung (8) und der Positionserfassungseinheit (14) verbunden ist. Die Auswerteeinheit (10) ist dazu eingerichtet, in Abhängigkeit der jeweils erfassten Position des rotierenden Körpers (4) einen von der Kraftmesseinrichtung (8) ermittelten Kraftwert zu erfassen. Das Kraftmesssystem erlaubt eine möglichst flexible und präzise Ermittlung von Kräften und Momenten an einem rotierenden Körper, unabhängig von der vorherrschenden Rotationsgeschwindigkeit des rotierenden Körpers. A force measuring system for detecting forces of a rotating body (4) has a force measuring device (8) which is arranged on the rotating body (4), as well as a position detection unit (14) for detecting the rotation of the rotating body (4) and an evaluation unit (10), which is connected to the force measuring device (8) and the position detection unit (14). The evaluation unit (10) is set up to record a force value determined by the force measuring device (8) as a function of the position of the rotating body (4) recorded in each case. The force measuring system allows the most flexible and precise determination possible of forces and moments on a rotating body, regardless of the prevailing rotation speed of the rotating body.

Windkanalwaage zur Mehrfachkonfiguration

Die Erfindung betrifft einen Prüfstand, insbesondere eine konvertierbare Windkanalwaage, mit einem Ausheberahmen (25, 25a) zum Ausheben zumindest einer Radbandeinheit (1, 2, 26), wobei die Radbandeinheit (1, 2, 26) zumindest ein Band aufweist, das um zumindest zwei Rollen geschlungen ist, einer Waageplattform (3), die relativ bewegbar zu einem Prüfstandrahmen (14) gelagert ist, zumindest einem Krafterfassungsmittel, das zwischen der Waageplattform (3) und dem Prüfstandrahmen (14) angeordnet ist, um Kräfte zwischen der Waageplattform (3) und dem Prüfstandrahmen (14) zu erfassen, wobei zumindest ein selbstzentrierendes Andockmittel (11) zwischen einem Hilfsrahmen (13) und der Waageplattform (3) vorgesehen ist.

Dynamic calibration of derivative balances in wind tunnel aircraft model - applying defined braking force to oscillated calibration model using eddy current brake and measuring load on model

The eddy current braking device (10) with a variable magnetic field source (12) applies a defined braking force to a non-magnetisable calibration element exposed to the field. A wind tunnel model (34) contains a plate (60) of the same thickness and material as the calibration element. The model is oscillated so that the plate moves like an element to be braked in the magnetic field, using knowledge of the eddy current device's braking effect based on the magnetic field strength and the speed-related instantaneous braking force opposing the model oscillation. The load on the model, which results from the braking force, is measured and the measurement system is calibrated according to the determined braking force and the measurement results produced by the measurement device. USE/ADVANTAGE - For use with equipment for performing dynamic measurements on aircraft models in wind tunnels. Aerodynamic damping can be simulated for calibration of instrumentation before measurements are made.

Improvements relating to pressure sensitive paint

NUCLEAR REACTOR CONTAINMENT SPRAY TESTING SYSTEM

... 1524002 Testing spray system WESTING- HOUSE ELECTRIC CORP 14 April 1977 [22 April 1976] 15511/77 Heading G6C A containment spray system 24, 26 in the containment structure 10 of a nuclear reactor is tested by introducing into the system gas at a temperature different from that of the atmosphere within the containment structure, and scanning the nozzles 26 of the system with an infrared viewing device.

SYSTEM FOR THE COMPENSATION OF AERODYNAMIC MEASUREMENTS IN A WIND TUNNEL

DEVICE AND PROCEDURE FOR AUTOMATIC MANUFACTURING OF VOLUME WITH THREAD FOR THE VISUALIZATION OF AIR FLOWS ON AERODYNAMIC SURFACES

DEVICE FOR TRANSFERRING THE PRESSURE BETWEEN A REMOVABLE ONE AND CELEBRATIONS A PART OF A MODEL IN AN AERODYNAMIC WIND TUNNEL

MEASURING SYSTEM FOR THE DETERMINATION OF AIR DATA OF AN AIRCRAFT AS WELL AS A PROCEDURE FOR THE DETERMINATION OF THE AIR DATA

PROCEDURE FOR THE DETERMINATION OF A SURFACE CONTACT STRENGTH

METHOD AND DEVICE FOR DETERMINING THE AERODYNAMIC WALL SHEAR STRESSES ON THE SURFACE OF A BODY, AROUND WHICH AIR FLOWS

Method and system for rendering visible a plume of dispersing fluid so as to reveal its source

A method for monitoring a fluid release plume (1) emitted by an industrial plant and/or an underground hydrocarbon fluid deposit into an adjacent space (3) comprises: a) monitoring the space (3) by means of a video camera during a selected period of time to generate an input video movie of the space (3); b) decomposing the generated input video movie into a series (s) of different spatial frequency bands; c) filtering the series (s) of spatial frequency bands by means of at least one temporal filter; d) amplifying the series (s) of filtered spatial frequency bands by a series of selected amplification factors ( ...

FLOW IRREVERSIBILITY MEASUREMENT SYSTEM

A detector for detecting fluid flow irreversibility is disclosed herein. The detector uses a spatial velocity field to determine the entropy production distribution of the flow, and generates a loss coefficient distribution on the basis the determined entropy distribution.

DEVICE AND METHOD FOR PRODUCING A TEST ADHESIVE STRIP ROLL FOR VISUALIZING AIR CURRENTS

AERODYNAMIC PROBE INTERNAL CONSTRUCTIONS

PCT/US90/06567 A short, strut-mounted, multifunction air data sensing probe (20) providing reduced drag, weight and radial cross section has a modular internal construction providing a multiple passageway pressure assembly (35) to transfer sensed pressure signals from individual sensing ports (25,31,32) on a probe barrel (21) to pressure carrying conduits (57,62,66,73,74) extending into the mounting strut (30) of the probe (20). The modular construction eliminates the need for having interior chambers made by fixing a series of difficult to locate bulkheads on the probe interior, with separate lines running from each of the chambers to provide the pressure signal from each of the ports. The modular construction also permits mounting a deicing heater (95) on internal parts other than the outer probe shell so that the manufacture of the probe (20) is further simplified, and the types of material used for the probe shell (21) can be changed without concern about heater mounting.

LUMINESCENT PRESSURE SENSITIVE COMPOSITION

A luminescent pressure sensitive composition for determining an air pressure pattern comprises a binder, preferably a polymer binder, with a luminophore, of which the intensity of luminescence depends on air pressure. The luminophore of which the intensity of luminesence depends on air pressure (active luminophore) is mixed together with an additional luminophore of which the intensity of luminescence has different dependence on air pressure than said active luminophore (reference luminophore). (Fig. 1 ) ...

Procédé de mesure d'un angle formé par une direction de référence d'un corps solide avec la direction du mouvement relatif à vitesse supersonique du fluide dans lequel ce solide est immergé.

Verfahren zum Herstellen von Hyperschallströmungen und Vorrichtung zu dessen Ausführung

Verfahren zum Betrieb von Versuchseinrichtungen für Hyperschallströmung

Radraumstr�mungsvisualisierung with druckoder temperature-sensitive color.

Ein Verfahren zum Messen von lokalen Temperaturabweichungen an einer Schnittstelle zwischen heissen Verbrennungsgasen in einem Heissgaspfad einer Turbine und einer kühleren Spülluft in einem Turbinenrotorradraum beinhaltet den Schritt einer Aufbringung einer druck- oder temperaturempfindlichen Farbe (64, 66, 68) auf eine drehbare Turbinenkomponente dort, wo das heisse Verbrennungsgas mit der Spülluft in Wechselwirkung tritt; den Schritt einer Anordnung einer Beleuchtungsvorrichtung (70, 72, 74) und wenigstens einer Bilddetektionsvorrichtung (76, 78, 80) auf einer stationären Komponente, die unmittelbar an der druckempfindlichen Farbe angeordnet ist; und während des Betriebs der Turbine den Schritt der bildlichen Aufnahme von Farbänderungen in der druckempfindlichen Farbe, die durch lokale Schwankungen des Sauerstoffpartialdrucks verursacht werden, welcher sich mit der Temperatur verändert.

СПОСІБ ПІДІГРІВУ РОБОЧОГО СТИСНУТОГО ГАЗУ В ГАЗОСТРУМИННОМУ МЛИНІ І ГАЗОСТРУМИННИЙ МЛИН

Винахід відноситься до галузі тонкого здрібнювання матеріалів цементної та інших промисловостей, а також до галузі експериментальної аеродинаміки. Спосіб підігріву робочого стиснутого газу у газоструминному млині послідовно включає підведення повітря по патрубках до млина, його електричний нагрів і передачу в помольну камеру, при цьому газ нагрівають у підвідному патрубку, прикладаючи до нього змінювану по довжині трубопроводу електричну напругу. Газоструминний млин включає джерела електричного струму, камери підігріву робочого газу, що містять оболонку і теплоізоляційний матеріал із встановленими в них електронагрівними патрубками підведення стиснутого газу, розгінні пристрої з робочим соплом і трубкою, помольну камеру, класифікатор, пилоосаджувальні і витяжні пристрої. Патрубки підведення приєднані щонайменше до одного джерела електричної напруги і мають щонайменше одну діелектричну ділянку з боку підведення газу. Винахід дозволяє істотно підвищити температуру стиснутого продувного газу ...

STAND for tuning the propeller group of unmanned aerial vehicles

СПОСІБ ПОДРІБНЕННЯ РУДНИХ МАТЕРІАЛІВ У ЗУСТРІЧНИХ ГАЗОДИНАМІЧНИХ ПОТОКАХ ПРИ ТЕРМІЧНІЙ ОБРОБЦІ

Спосіб подрібнення рудних матеріалів у зустрічних газодинамічних потоках при термічній обробці включає подрібнення матеріалу з одночасним термічним впливом, відвід твердої фази з області обробки, поділ твердої і газової фаз продукту, осадження й охолодження твердої фази. Матеріал, який руйнується, вводять у зустрічні потоки газу, відбирають із твердої фази, що відводиться, задані найбільш великі частки зруйнованого матеріалу і повертають частину, що залишається, у зустрічні потоки на подрібнення. В зону зустрічі потоків подають додатковий струмінь газу з температурою, що перевищує температуру зустрічних потоків, а температуру зустрічних потоків збільшують у процесі обробки, доводячи її до температури додаткового струменя.

Лабораторный стенд для тестирования противоградовых пиротехнических композиций

Изобретение относится к области анализа материалов путем определения их физических параметров, а именно к лабораторному стенду для тестирования пиротехнических противоградовых композиций. Лабораторный стенд для тестирования пиротехнических противоградовых композиций содержит аэрозольный бокс, термостатическую облачную камеру, регистрирующую аппаратуру и аэродинамическую трубу, установленную перед аэрозольным боксом. Аэродинамическая труба с технологическим отверстием для введения/вывода противоградовой ракеты снабжена системой для фиксации ракеты, системой зажигания пиротехнической композиции ракеты для получения аэрозоля, вентилятором высокого давления, системой рассекания и смешивания потока аэрозоля и системой взятия проб аэрозоля. Система взятия проб включает зонд, размещенный в зоне наиболее эффективного перемешивания аэрозоля, и систему трубопроводов, соединяющих аэродинамическую трубу с аэрозольным боксом. П. формулы: 1 Фиг.: 1 ...

Лабораторный стенд для тестирования противоградовых пиротехнических композиций

Изобретение относится к области анализа материалов путем определения их физических параметров, а именно к лабораторному стенду для тестирования пиротехнических противоградовых композиций. Лабораторный стенд для тестирования пиротехнических противоградовых композиций содержит аэрозольный бокс, термостатическую облачную камеру, регистрирующую аппаратуру и аэродинамическую трубу, установленную перед аэрозольным боксом. Аэродинамическая труба с технологическим отверстием для введения/вывода противоградовой ракеты снабжена системой для фиксации ракеты, системой зажигания пиротехнической композиции ракеты для получения аэрозоля, вентилятором высокого давления, системой рассекания и смешивания потока аэрозоля и системой взятия проб аэрозоля. Система взятия проб включает зонд, размещенный в зоне наиболее эффективного перемешивания аэрозоля, и систему трубопроводов, соединяющих аэродинамическую трубу с аэрозольным боксом. П. формулы: 1 Фиг.: 1 ...

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Стенд для определения аэродинамических характеристик вихря модели крыла летательного аппарата на ракетном треке

Полезная модель относится к области экспериментальной аэродинамики, в частности к методам и средствам получения в прямом движении в неподвижной атмосфере нестационарных характеристик вихря (включая и пульсационные составляющие) за моделью крыла летательного аппарата и может быть использована при конструировании летательных аппаратов, при организации перемещения летательного аппарата в воздухе и для задач разработки системы вихревой безопасности ЛА (пилотируемых и беспилотных).Стенд определения аэродинамических характеристик вихря модели крыла летательного аппарата содержит тележку, установленную на рельсах ракетного трека, по меньшей мере, одну измерительную гребенку с датчиками скорости и приемниками давления, предназначенными для непрерывного измерения нестационарных характеристик вихря, дымогенератор, видеокамеру и тепловизор для визуализации и съемки вихря. 4 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 178 659 U1 (51) МПК G01M 9/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК G01M 9/06 (2006.01) (21)(22) Заявка: 2017125481, 17.07.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: Приоритет(ы): (22) Дата подачи заявки: 17.07.2017 (45) Опубликовано: 16.04.2018 Бюл. № 11 RU 137378 U1, 10.02.2014. RU 144390 U1, 20.08.2014. SU 313119 A1, 31.08.1971. US 2331304 A1, 12.10.1943. (54) Стенд для определения аэродинамических характеристик вихря модели крыла летательного аппарата на ракетном треке (57) Реферат: Полезная модель относится к области (пилотируемых и беспилотных). экспериментальной аэродинамики, в частности Стенд определения аэродинамических к методам и средствам получения в прямом характеристик вихря модели крыла летательного движении в неподвижной атмосфере аппарата содержит тележку, установленную на нестационарных характеристик вихря (включая рельсах ракетного трека, по меньшей мере, одну и пульсационные составляющие) за моделью измерительную гребенку с датчиками скорости ...

Device and method for measuring pressure on wind turbine components

A device for measuring fluid pressure, includes at least one flexible layer having a first surface adapted for fixing the layer to a structure, and having a second surface having at least one recess; at least one pressure sensor, provided in the at least one recess; and at least two wires connected to the at least one pressure sensor for connecting the at least one pressure sensor to a signal receiving unit. Further, a method for measuring fluid pressure is provided.

Apparatuses and methods for visualizing air flow around vehicles

Described herein are embodiments of an apparatus for visualizing air flow around a vehicle. Such embodiments can comprise one or more gas emitters supportable by a vehicle, one or more imaging devices having a field of view of at least a portion of the gas flowing over the vehicle, and a light source for irradiating at least a portion of the field of view of the one or more imaging devices. Some embodiments of the apparatus can have a signal processor configured to generate an image based on an input from the imager. The apparatus can be configured such that the gas is not detectable to the naked eye so as to not obstruct a vehicle operator's field of vision. The apparatus can be configured to produce an image of the flow of the gas over the one or more surfaces of the vehicle when in an operational state.

Probe for Measuring a Local Angle of Attack and Method Implementing Same

A probe for measuring a local angle of attack designed to be fixed to a wall and a method implementing the probe are provided. The probe comprises at least three pressure sampling ports disposed over a nose of the probe body, pressure measurement means associated with the pressure sampling ports and calculation means capable of determining an angle of attack of the flow with respect to the main direction of the probe body as a function of the pressures measured by the pressure measurement means. The calculation means are configured for choosing from amongst the pressure sampling ports those allowing the best measurement precision of the local angle of attack to be obtained and for calculating the local angle of attack with respect to the main direction using the pressure measurements carried out in the chosen pressure sampling ports. 1. A probe for measurement of the local angle of attack of a fluid flow along a wall , the probe comprising:a probe body designed to be fixed to the wall and aligned in a main direction, around which the angle of attack can be measured within a range of angle of attack, at least five pressure sampling ports disposed over a nose of the probe body, the nose being situated on one side of the body with respect to the largest cross section of the body perpendicularly to the main direction, the nose forming a surface locally perpendicular to the angle of attack inside of the range, pressure measurement means associated with the pressure sampling ports and calculation means capable of determining an angle of attack of the flow with respect to the main direction of the probe body as a function of the pressures measured by the pressure measurement means, wherein the calculation means are configured for choosing from amongst the pressure sampling ports those allowing the best measurement precision of the local angle of attack and for calculating the local angle of attack with respect to the main direction using the pressure measurements carried ...

APPARATUS FOR DETERMINING FORCES AND MOMENTS ACTING ON MOTOR VEHICLES IN A WIND TUNNEL

The invention relates to a belt unit in a wind tunnel balance for motor vehicles, in particular for determining forces and moments acting on a motor vehicle in a wind tunnel, wherein an area exposed to wind is minimized by means of a trapezoidal support, which is raised with respect to a normal zero position, and appropriately adapted test stand covers. The wind-exposed area of the endless belt of the belt test stand can be reduced here to a value which is only slightly above the necessary wheel contact area (tire shuffle). As a result, error forces can be reduced further, so that the result is highly increased measurement accuracy. 1. A belt unit for motor vehicles , in particular for determining forces and moments acting on a motor vehicle in a wind tunnel , comprisingat least one belt unit which has a first drum and a second drum, wherein an endless belt is wrapped around the first and second drums, andsupport which supports the endless belt and is arranged below a carrying run of the endless belt between the first and second drums.whereinthe support has a top side which is arranged by a predetermined distance AL above an upper tangential connecting line of the drum outer surfaces.2. The belt unit according to claim 1 , wherein the top side of the support has an outwardly curved shape.3. The belt unit according to claim 1 , wherein and end region of a test stand cover claim 1 , which faces the support claim 1 , is arranged above the respective drum.4. The belt unit according to claim 1 , wherein a portion of the endless belt claim 1 , which extends between the drum and the support is arranged between the inner side of the end region and the drum.5. The belt unit according to claim 1 , wherein the free area of the endless belt which is not covered by the test stand cover corresponds substantially to a size of a tire shuffle of a vehicle tire resting on the endless belt claim 1 , plus a positioning tolerance of the vehicle.6. The belt unit according to claim 1 , ...

Inlet Icing Protection Simulation System

A method and apparatus for generating a flow of heated air in an airfoil model of an inlet of an aircraft engine. Heated air is sent into a duct system associated with the airfoil model of the inlet of the aircraft engine. The heated air is circulated within the airfoil model of the inlet of the aircraft engine using the duct system in a manner that simulates air flowing in the inlet of the aircraft engine.

SYSTEMS AND METHODS FOR CORRECTING ACOUSTIC ERROR IN PRESSURE SENSORS

Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided. 1. A system comprising:an aircraft component;a port disposed within the aircraft component;a static pressure sensor disposed within the port and configured to provide primary pressure data in response to at least environmental air pressure and an acoustic disturbance;an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance; anda processor communicatively coupled to the static pressure sensor and the acoustic sensor and configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data.2. The system of claim 1 , wherein the acoustic data corresponds to at least an amplitude and a frequency of the acoustic disturbance.3. The system of claim 1 , wherein the processor is configured to determine an acoustic modifier from the provided acoustic data and apply the acoustic modifier to the provided primary pressure data to determine the corrected static pressure data claim 1 , and wherein the acoustic modifier is configured to correct for an ...

Pressure Profiling System

A solution for acquiring pressure data for an object, such as an airfoil, is provided. One or more pressure sensor nodes are utilized, each of which includes a set of pressure sensors and a processing component. The pressure sensor node(s) are affixed to the object in a manner that enables the pressure sensors to acquire pressure data for a set of locations on the surface of the object. A pressure sensor node also can include a wireless communications component to provide wireless communications between the pressure sensor node and a computer system. 1. A system comprising:an object; and a substrate;', 'a set of pressure sensors mounted to the substrate;', 'a processing component mounted to the substrate and operatively connected to the set of pressure sensors; and', 'a wireless communications component mounted to the substrate and operatively connected to the processing component, wherein the pressure sensor node is affixed to the object in a manner that enables the set of pressure sensors to acquire data corresponding to a pressure at a set of locations on a surface of the object, and wherein the processing component is configured to receive data from the set of pressure sensors and communicate pressure data corresponding to the pressure at the set of locations to a computer system using the wireless communications component., 'a pressure sensor node affixed to the object, the pressure sensor node comprising2. The system of claim 1 , wherein the substrate comprises a flexible substrate claim 1 , and wherein the pressure sensor node is affixed to a curved surface of the object.3. The system of claim 2 , wherein the set of pressure sensors includes a plurality of closely spaced pressure sensors claim 2 , and wherein the processing component is further configured to selectively process data from only a subset of the plurality of closely spaced pressure sensors.4. The system of claim 1 , wherein the pressure sensor node is located in a groove in a surface of the ...

METHOD FOR ALLEVIATING AND PROTECTING LOADS FOR AN AIRCRAFT

A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface. 1. A method for alleviating and protecting loads of a lifting surface of an aircraft comprising a control unit in which is stored an acceptable interval of tolerance of shapes for the lifting surface , the lifting surface comprising a fixed proximal end and a free distal end and being equipped with at least one control surface and a maneuvering system provided to displace the control surface relative to the lifting surface , the lifting surface also comprising a distal sensor fixed to a structure of the lifting surface in a vicinity of its distal end and a proximal sensor fixed to the structure of the lifting surface in the vicinity of its proximal end , each sensor being connected to a control unit and configured to measure a dimensional characteristic linked to distortion of the lifting surface , the method for alleviating and protecting loads comprising:a first process and a second process, wherein the first process comprises, for the control unit, assigning a first value to a strain attribute if the lifting surface is not placed under controlled strain or a second ...

Two-Axis Sensor Body For A Load Transducer

In one aspect, a transducer body includes a support having clevis halves. The sensor body includes a generally rigid peripheral member disposed about a spaced-apart central hub joined to each of the clevis halves. At least three flexure components couple the peripheral member to the hub. The flexure components are spaced-apart from each other at generally equal angle intervals about the hub; the sensor body further including a flexure assembly for some flexure components joining the flexure component to at least one of the hub and the peripheral member, the flexure assembly being compliant for forces in a radial direction from the hub to the peripheral member. Each flexure assembly is configured such that forces transferred concentrate strain at a midpoint along the length of each corresponding flexure component.

MULTIPLE CONFIGURATION WIND TUNNEL BALANCE AND METHOD FOR CONVERTING THE WIND TUNNEL BALANCE

The invention described herein relates to a wind tunnel test stand, in particular a multiple configuration wind tunnel test stand, which can be converted at least into a one-belt, three-belt and/or five-belt configuration with a lower level of complexity, while ensuring increased measurement accuracy. 118-. (canceled)19. A multiple configuration wind tunnel test stand that is at least convertible into a one-belt , three-belt and/or five-belt configuration , the test stand comprising:a test stand frame for receiving forces;a weighing platform which is supported relatively movably with respect to said test stand frame;at least one force sensing means arranged between said weighing platform and said test stand frame for sensing forces between said weighing platform and said test stand frame;at least one belt unit with a conveyor belt wound around two rollers; anda carriage for accommodating at least one belt unit of a one-belt or three-belt configuration, wherein said carriage is supported relatively movably with respect to said test stand frame in X- and Y-directions.20. The wind tunnel test stand of wherein said carriage and said weighing platform are coupled in X and/or Y direction such that a relative movement between said carriage and said weighing platform in the corresponding direction is prevented.21. The wind tunnel test stand of wherein claim 19 , in a one-belt configuration claim 19 , a one-belt belt unit is arranged on said carriage.22. The wind tunnel test stand of wherein claim 19 , in a three-belt configuration claim 19 , at least two side belt units are arranged on said carriage.23. The wind tunnel test stand of wherein claim 19 , in the three-belt or five-belt configuration claim 19 , a middle belt unit is provided between wheel belt units of the five-belt configuration or side belt units of the three-belt configuration claim 19 , on which the wheels of said motor vehicle to be tested can be placed claim 19 , wherein said middle belt unit is fixedly ...

Determining air flow characteristic

It is described a method for determining a characteristic of air flow close to a surface of a rotating blade of a wind turbine, the method including: measuring at least one value of the temperature of air close to the surface of the blade; and deriving the characteristic of the air flow based on the temperature value.

Predicting transition from laminar to turbulent flow over a surface using mode-shape parameters

In accordance with embodiments disclosed herein, there are provided methods, systems, and apparatuses for predicting whether a point on a computer-generated aircraft or vehicle surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. Included in the list of boundary-layer properties are computed coefficients or weights of mode shapes that describe the boundary-layer profiles. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates. Each covariance vector is used with the vector of regressor weights to determine a predicted local growth rate at the point. Based on the predicted local growth rates, an n-factor envelope at the point is determined.

HOLDING DEVICE FOR A WIND TUNNEL BALANCE AND TEST METHOD

The device described herein and the associated method relate, in particular, to a holding device for a wind tunnel test stand in particular for a wind tunnel balance. The device may comprise a holding base which may be arranged outside of a conveyor belt of the wind tunnel test stand and a support element having at least two ends Via a connection element one end of the support element may be connected to a wheel of a test object Furthermore, a support device may be provided, which may be connected to the support element in such a way that a change in a rotational orientation of the support element can cause a lifting or lowering movement of the support device 115-. (canceled)16. A holding device for a wind tunnel test stand including a wind tunnel balance , the holding device comprising:a holding base which can be arranged outside a conveyor belt of the wind tunnel test stand;a support element having at least two ends, wherein one end is connected to the holding base and another end is connected to a wheel of a test object by means of a connecting element, and wherein the connecting element decouples the support element and the wheel from one another in a rotational direction; anda support device, which is connected to the support element such that a change in a rotational orientation of the support element causes a lifting or lowering movement of the support device.17. The holding device of wherein the support element is connected to the holding base in such a way that a rotational orientation of the support element relative to the holding base is variable claim 16 , wherein the rotational orientation of the support element can be changed by means of a torque and the torque is generatable/changeable manually and/or mechanically.18. The holding device of wherein the holding base comprises an orienting device for mechanically changing the rotational orientation of the support element and the orienting device comprises a torque motor or a lifting element operated by ...

SYSTEM AND METHOD FOR FLEXIBLE SOLAR TRACKER AND TESTING

Disclosed herein is a technique of configuring flexible photovoltaic tracker systems with high damping and low angle stow positions. Under dynamic environmental loads implementing a high amount of damping (e.g., greater than 25% of critical damping, greater than 50% of critical damping) or a very high amount of damping (e.g., 100% or greater of critical damping, infinite damping) enables the flexible tracker system to prevent problematic aeroelastic behaviors while positioned in a low stow angle. The disclosed technique is further applied to a prototyping process during wind tunnel testing. 121-. (canceled)22. A flexible solar tracker system comprising:an actuator configured to set a position of a set of photovoltaic (PV) panels in a row via a torque tube, the actuator having a flexible configuration with respect to the set of PV panels;dampers interspersed through the row of the set of PV panels, the dampers employing a high damping ratio when measured under peak design wind loading; anda controller configured to cause the actuator to set a low angle stow position of the set of PV panels.23. The system of claim 22 , wherein the low angle stow position is less than 20 degrees from horizontal plane.24. The system of claim 22 , wherein total system damping ratio of the flexible solar tracker system is based on any of:a pluck test;a predictive model; orprevious wind tunnel tests.25. The system of claim 22 , wherein the high damping ratio is critically damped.26. The system of claim 22 , wherein the high damping ratio is overdamped.27. The system of claim 22 , wherein the flexible solar tracker system includes non-functional claim 22 , substitute panels configured for wind tunnel testing.28. The system of claim 22 , wherein the set of PV panels in the row contains multiple strings of PV panels.29. The system of claim 22 , wherein the dampers have a variable damping ratio that varies passively based on environmental conditions.30. The system of claim 29 , wherein the ...

METHOD OF EVALUATING INTEGRATED RUNNING ENERGY OF VEHICLE IN WIND TUNNEL

A method of evaluating integrated running energy of a vehicle in a wind tunnel may include estimating change in fuel efficiency according to change of vehicle parts thereby facilitating precise measurement of running energy. 1. A method of evaluating integrated running energy of a vehicle in a wind tunnel , the method comprising:placing the vehicle in the wind tunnel;changing vehicle speeds by rotating wheels of the vehicle to obtain a plurality of constant speed sections and a plurality of speed change sections, wherein the vehicle speeds are held constant in each constant speed section, the plurality of constant speed sections have different constant speeds with each other, and the vehicle speeds are increased or decreased between adjoining constant speed sections in the plurality of speed change sections;measuring and collecting exerted forces for rotating the wheels in each of the plurality of constant speed sections and exerted forces for rotating the wheels in each of the plurality of speed change sections;separating the exerted forces in each of the plurality of constant speed sections from the exerted forces in each of the plurality of speed change sections;determining running energy of the plurality of constant speed sections according to the separated exerted forces in each of the plurality of constant speed sections and determining running energy of the plurality of speed change sections according to the separated exerted forces in each of the plurality of speed change sections; andacquiring the integrated running energy of the vehicle according to the running energy of the plurality of constant speed sections and the running energy of the plurality of speed change sections.2. The method of claim 1 , wherein the wind tunnel includes:a wheel rotating device configured to rotate the wheels of the vehicle; anda force measurement portion configured to measure driving force by which the wheel rotating device rotates the wheels to measure the exerted forces.3. ...

Technology to Control a Model and Balance Support System's Dynamics and Isolate the Balance as Needed to Increase Test Facilities Productivity

A balance protection system for a wind tunnel test system that includes a balance component, a model component connected to the balance component and a sting component connected to the balance component is disclosed. The balance protection system includes a first set of features on the model component that mate with a second of features on to the sting component. The clearances between the first and second set of features determine an amount of allowed movement of the model with respect to the balance. Actuators can be used to actively adjust the amount of clearance and respective allowed movement of the model with respect to the balance. Limiting movement of the model with respect to the balance protects the balance from damage caused by excessive forces applied to the model.

MEASURING AIR FLOWS ALONG A WALL

A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern. 1. A device for measuring a flow of air , the device comprising:an optical sensor configured to measure an illuminance distribution over a free surface of the optical sensor; anda mobile member movably mounted on the optical sensor and partially covering the free surface, the mobile member being adapted to be freely oriented with a local flow of air, thereby modulating distribution of illuminance over the free surface so that a current measurement by the optical sensor of the distribution of the illuminance indicates current orientation of the mobile member representing current flow of air.2. The device as claimed in claim 1 , wherein the optical sensor comprises an annular photodetector comprising a predetermined number of light-detecting tracks and delivering signals representing the illuminance received by each of the tracks claim 1 , thereby generating the measurement of the distribution of the illuminance over the free surface of the optical sensor.3. The device as claimed in claim 1 , wherein the optical sensor comprises printed organic electronic components and wherein the optical sensor has an angular measurement accuracy of 1° to 5°.4. The device as claimed in claim 1 , wherein the mobile member includes a plane part covering a part of the free surface of the optical sensor.5. The device as claimed in claim 4 , wherein the ...

WIND TUNNEL STING, WIND TUNNEL STING DAMPER, AND METHOD THEREFOR

A wind tunnel sting comprising a support member and a wind tunnel sting damper. The support member having a first support-member end configured for coupling with a wind tunnel, and a second support-member end configured for coupling with a balance. The wind tunnel sting damper having a reactive member, and a viscoelastic member disposed between the reactive member and the support member wherein, the reactive member is sized relative to the support member so as to radially compress the viscoelastic member against the support member. 1. A wind tunnel sting comprising: a first support-member end configured for coupling with a wind tunnel, and', 'a second support-member end configured for coupling with a balance; and, 'a support member having a reactive member, and', 'a viscoelastic member disposed between the reactive member and the support member;, 'a wind tunnel sting damper havingwherein, the reactive member is sized relative to the support member so as to radially compress the viscoelastic member against the support member.2. The wind tunnel sting of claim 1 , wherein:the support member further comprises an outer surface; andthe reactive member circumscribes the outer surface of the support member so as to compress the viscoelastic member against the outer surface.3. The wind tunnel sting of claim 1 , wherein:the support member further comprises an inner channel; andthe reactive member is disposed within the inner channel of the support member so as to compress the viscoelastic member against the inner channel.4. The wind tunnel sting of claim 1 , wherein the reactive member is separate and distinct from the support member claim 1 , the reactive member being spaced apart from the support member by the viscoelastic member so as to provide relative movement between the support member and the reactive member that generates shear forces at an interface between the viscoelastic member and the support member and at another interface between the viscoelastic member and ...

MEASUREMENT DEVICE WITH SINGLE CONTROL CIRCUIT

A measurement device can be attached to an outer wall of a movable object or of a stationary object arranged in a flow of air in order to measure physical quantities. The measurement device includes a mounting which has recesses having an opening leading to the outside in which sensors are provided. The mounting comprises a cavity in which a flexible printed circuit is housed, on which a single circuit for controlling the sensors is provided. The device has multiple advantages, in particular that of providing a simple measurement device which offers a system for control and interconnection of sensors that is accessible and less complex while offering numerous advantages. 1. A measurement device comprising:a support having recesses provided with openings leading toward the outside; sensors provided in the recesses; anda first flexible printed circuit for the sensors,wherein the support comprises a cavity in which the flexible printed circuit is housed.2. The measurement device as claimed in claim 1 , wherein the circuit is crossed by a first plurality of tracks joining the linking ends of the circuit.3. The measurement device as claimed in claim 2 , wherein the sensors are positioned on a same row or a number of rows offset relative to the first plurality of tracks.4. The measurement device as claimed in of claim 1 , further comprising a second plurality of tracks for linking each of the sensors to the control circuit.5. The measurement device as claimed in of claim 1 , wherein the circuit comprises at least two printed circuit layers separated by an insulating layer.6. The measurement device as claimed in claim 2 , wherein the first and second plurality of tracks and are located on one or other of the printed circuit layers.7. The measurement device as claimed in claim 2 , wherein one of the first plurality of tracks is reserved for supplying power to the sensors.8. A measurement system comprising at least one measurement device comprising:a support having recesses ...

FORCE AND MOMEMENT BALANCE AND SUPPORT THEREFOR

This invention relates to a force and moment balance () including a support () therefor and more specifically, but not exclusively, to a force and moment balance () and a support () therefor for a wind tunnel. Force and moment balances are known in the art and are typically used in wind tunnels to measure the force and moment loads on a model in the wind tunnel. A problem with current balances is that there is inherent vertical movement associated with horizontal force. According to the invention, the balance () has a fixed end () and a movable end () with a number of supports () between the fixed end () and the movable end (). Each support () includes compensation means to compensate for resultant movements caused by lateral movement of the movable end () relative to the fixed end (). 1. A support for a force and moment balance comprising:a first end and a second end; anda support structure between the ends; a first support member extending from the first end;', 'a second support member extending from the second end;', 'an intermediate member between the first and second members; and', 'biasing means for biasing the members such that lateral movement of the second end causes relative movement between the members and neutralizes relative longitudinal movement between the second end and the first end., 'the support structure including2. The support of wherein the first end is fixed and the second end is movable.3. (canceled)4. The support of wherein the relative movement between the members is opposite and equal.5. The support of wherein the members are integrally formed and the relative movement between the members and biasing between the members are caused by flexing of the members.6. The support of wherein the members and ends are integrally formed.7. The support of wherein the members are shaped and sized such that lateral movement of the second end causes flexing of the members and the flexing of the members causes proportionally opposing longitudinal movement ...

Verfahren und Vorrichtung zum numerischen Messen mindestens einer strömungsbezogenen Eigenschaft

The invention relates to a method for the numerical measurement of at least one flow-related characteristic of a profile section of a rotating profile body, around which fluid can flow, by means of a numerical flow simulation which is executed on a data-processing system and which calculates a fluid-based flow around the profile section by means of multi-dimensional computational meshes, wherein the method comprises the following steps: providing a numerical flow simulation which can be executed on a data-processing system and which is configured such that the flow velocity of the far field of the numerical flow simulation is set to zero and, instead, a lattice movement of the multi-dimensional computational mesh is performed with a translational velocity in the profile section plane, such that the relative velocity yields the incident-flow velocity of the profile section at a given angle of attack, the symmetry boundary conditions for the edges of the multi-dimensional computational mesh are set to a translationally periodic boundary condition, and the velocity component, resulting from the velocity field of the rotational movement on the edge of the profile section, in the normal direction with respect to the profile section plane are taken into consideration in the inertial terms of the balance equations of the numerical flow simulation, executing the numerical flow simulation as provided above in order to numerically measure and obtain the at least one flow-related characteristic of the profile section.

METHOD FOR ADAPTIVELY CANCELLING IN REAL TIME ELASTIC MODES IN DISCRETE-TIME SIGNALS

A method of aeroservoelastic coupling suppression, and particularly, the field of real time adaptive cancellation of elastic modes in discrete-time signals which measure the dynamics of a flexible structure. The flexible structure comprises a structure with elastic variable characteristics, and more particularly, a structure with non-linear aerodynamics. A method is disclosed for adaptively cancelling, in real time, N elastic modes in discrete-time signals which measure the dynamics of the flexible structure. Also disclosed is a computer program implemented on a computing device, a system and an aircraft implementing the mentioned method. 6. A non-transitory computer-readable medium having computer-executable program instructions stored thereon claim 1 , comprising instructions for the implementation claim 1 , by a processor of a computing device claim 1 , of the method according to claim 1 , when said program is executed by said processor.7. A system comprising:a flexible structure and N elastic modes to be cancelled in real time in discrete-time signals which measure the dynamics of the flexible structure, and{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'a computer device, the computer device being configured to apply a method for adaptively cancelling in real time N elastic modes in said discrete-time signals according to .'}8. An aircraft comprising a system according to . This application claims the benefit of the European patent application No. 16382445.1 filed on Sep. 25, 2017, the entire disclosures of which are incorporated herein by way of reference.The present invention belongs to the field of aeroservoelastic coupling suppression, and particularly, it belongs to the field of real time adaptive cancellation of elastic modes in discrete-time signals which measure the dynamics of a flexible structure.In particular, the flexible structure is a structure with elastic variable characteristics, and more particularly, a structure with non-linear ...

AERODYNAMIC SYSTEM AND METHOD FOR DIAGNOSING THE AERODYNAMIC SYSTEM AND VERIFY DOWNFORCE ESTIMATION BASED ON ELECTRIC MOTOR CURRENT

A method can be executed to diagnose an aerodynamic system and includes the following steps: (a) determining, via a controller, a first expected downforce acting on an aerodynamic element of a vehicle based, at least in part, on a current position of the aerodynamic element relative to a vehicle body of the vehicle, wherein an electric motor is operatively coupled to the aerodynamic element; (b) determining, via the controller, a second expected downforce acting on the aerodynamic element of the vehicle based, at least in part, on an electrical current used to move the electric motor in order to move the aerodynamic element from the current position to another position; (c) determining a deviation, via the controller, based on the first expected downforce and the second expected downforce; and (d) controlling, via the controller, the aerodynamic element based, at least in part, on the deviation. 1. A method , comprising:determining, via a controller, a first expected downforce acting on an aerodynamic element of a vehicle based, at least in part, on a current position of the aerodynamic element relative to a vehicle body of a vehicle, wherein an actuation mechanism comprising an electric motor is operatively coupled to the aerodynamic element;determining, via the controller, a second expected downforce acting on the aerodynamic element of the vehicle based, at least in part, on an electrical current used to move the electric motor in order to move the aerodynamic element from the current position to another position;determining a deviation, via the controller, based, at least in part, on the first expected downforce and the second expected downforce; andcontrolling, via the controller, the aerodynamic element based, at least in part, on the deviation.2. The method of claim 1 , further comprising determining a motor force used to move the electric motor based on the electrical current used to move the electric motor in order to move the aerodynamic element from the ...

SYSTEM AND METHOD FOR FLEXIBLE SOLAR TRACKER AND TESTING

Disclosed herein is a technique of configuring flexible photovoltaic tracker systems with high damping and low angle stow positions. Under dynamic environmental loads implementing a high amount of damping (e.g., greater than 25% of critical damping, greater than 50% of critical damping) or a very high amount of damping (e.g., 100% or greater of critical damping, infinite damping) enables the flexible tracker system to prevent problematic aeroelastic behaviors while positioned in a low stow angle. The disclosed technique is further applied to a prototyping process during wind tunnel testing. 1. A flexible solar tracker system comprising:an actuator configured to set a position of a set of photovoltaic (PV) panels in a row, the actuator having a configuration with respect to the set of PV panels wherein the solar tracker system is subject to aeroelastic consideration due to wind deflection and few points of fixity per row;dampers corresponding to the set of PV panels and having a total system damping ratio against row rotation greater than 25% of the critical damping when measured under peak design wind loading; anda controller configured to cause the actuator to set a low angle stow position of the set of PV panels.2. The system of claim 1 , wherein the low angle stow position is less than 20 degrees from horizontal plane.3. The system of claim 1 , wherein total system damping ratio of the flexible solar tracker system is based on any of:a pluck test;a predictive model; orprevious wind tunnel tests.4. The system of claim 1 , wherein the total system damping ratio is critically damped.5. The system of claim 1 , wherein total system damping ratio is overdamped.6. The system of claim 1 , wherein the flexible solar tracker system includes non-functional claim 1 , substitute panels configured for wind tunnel testing.7. The system of claim 1 , wherein the set of PV panels in the row contains multiple strings of PV panels.8. The system of claim 1 , wherein the dampers have ...

AERODYNAMIC DRAG MONITORING SYSTEM AND METHOD

Described are various embodiments of an aerodynamic drag monitoring system and method. In one embodiment, a system is described to comprise a motion sensor and an aerodynamic sensor operable to acquire respective sensor values each associated with a respective sensor noise variance, a digital data storage medium having stored thereon a digital motion dynamic model and preset initialization parameters, and a digital data processor operable to iteratively process measured sensor values against the model to output a predicted value for a predicted aerodynamic drag variable over time while accounting for each sensor noise variance. 1. A system for monitoring aerodynamic drag variations in line with a user's path of motion , the system comprising:a motion sensor and an aerodynamic sensor fixedly mountable in relation to the user and operable to each measure a respective sensor value representative of a motion of the user and a local airflow over time, wherein each said sensor value is associated with a respective sensor noise variance; a digital motion dynamic model for the user in motion, wherein said model defines respective measured input variables associated with each said sensor value and a predicted aerodynamic drag variable at least partially predictable from said respective measured input variables via said model; and', 'preset initialization parameters representative of the system and at least comprising a stored value representative of each said respective sensor noise variance;, 'a digital data storage medium having stored thereona digital data processor operable to iteratively process each said measured sensor value against said model to output a predicted value for said predicted aerodynamic drag variable over time while accounting for each said respective sensor noise variance.2. The system of claim 1 , wherein said digital processor is operable to iteratively process said measured sensor value by implementing an Extended Kalman Filter.3. The system of ...

Apparatus and method for calculating wind load

Provided is an apparatus and method for calculating a wind load. The apparatus for calculating a wind load includes an information collecting unit collecting heights of a plurality of points in a region, a frequency distribution calculating unit calculating a frequency distribution for the heights of the plurality of points, and a parameter calculating unit allocating ground surface roughness for ranks in the frequency distribution and calculating parameters for the region by applying weights on the basis of the frequency distribution to parameters set for each ground surface roughness for calculating the wind load.

WIND TUNNEL TEST EQUIPMENT USING WIND FORCE INTEGRATION

A wind tunnel test equipment using wind force integration includes: a structural model whose interior is empty; an internal support disposed inside the structural model; and load sensors disposed outside the internal support and coming into close contact with the inner surfaces of the structural model to measure aerodynamic forces applied to the structural model. 1. Wind tunnel test equipment using wind force integration , comprising:{'b': '2', 'a structural model () whose interior is empty;'}{'b': 3', '2, 'an internal support () disposed inside the structural model (); and'}{'b': 4', '3', '2', '2, 'load sensors () disposed outside the internal support () and coming into close contact with the inner surfaces of the structural model () to measure aerodynamic forces applied to the structural model ().'}2221. The wind tunnel test equipment according to claim 1 , wherein the structural model () has a plurality of segments () formed dividedly on the external walls thereof.32122. The wind tunnel test equipment according to claim 2 , wherein the neighboring segments () have a sealing material () disposed therebetween.43. The wind tunnel test equipment according to claim 1 , wherein the internal support () is a rigid core.53. The wind tunnel test equipment according to claim 1 , wherein the internal support () is an equivalent dynamic model of a structural system of a structure. The present invention relates to wind tunnel test equipment using wind force integration that is capable of directly measuring aerodynamic forces applied to a structural model as reaction forces through load sensors disposed between the external walls of the structural model and an internal support, so that wind loads applied to a given height can be measured with accurate values, not with approximate values, and capable of measuring local loads applied to external wall segments of the structural model to accurately design exterior materials and to calculate accurate load distributions to base ...

Platform Balance

In one aspect, a platform balance includes a frame support, and at least three spaced-apart transducer bodies coupled to the frame support. Each transducer body includes a support having clevis halves. The sensor body includes a generally rigid peripheral member disposed about a spaced-apart central hub joined to each of the clevis halves. At least three flexure components couple the peripheral member to the hub. The flexure components are spaced-apart from each other at generally equal angle intervals about the hub; the sensor body further including a flexure assembly for some flexure components joining the flexure component to at least one of the hub and the peripheral member, the flexure assembly being compliant for forces in a radial direction from the hub to the peripheral member. Each flexure assembly is configured such that forces transferred concentrate strain at a midpoint along the length of each corresponding flexure component.

METHOD FOR DETECTING A PHYSICAL STATUS OF A FLEXIBLE STRUCTURE

A method in the field of flight control laws (CLAWs) used to control a flexible structure, for example an air to air refueling flying boom system, the method detecting the physical status determined by exogenous boundary conditions acting on the flexible structure. A computer program is provided which carries out the method for detecting the physical status of a flexible structure. A system and aircraft comprising such a flexible structure are also provided. 1. A method for detecting a physical status of a flexible structure , said status being either free-movement or restricted-movement , the flexible structure having time-varying elastic characteristics , with a total number N∈ of elastic modes , being i a generic elastic mode , i∈:i∈[1 , N] , and the flexible structure being controlled by flight control laws (CLAWs) , these CLAWs comprising specific filtering modes for free-movement or restricted-movement status , the method comprising the following steps:{'sup': A', 'B', 'A', 'B', 'th', 'th', '+, 'sub': n', 'n, 'img': {'@id': 'CUSTOM-CHARACTER-00016', '@he': '3.22mm', '@wi': '2.12mm', '@file': 'US20220297849A1-20220922-P00001.TIF', '@alt': 'custom-character', '@img-content': 'character', '@img-format': 'tif'}, 'a) sampling a first and a second discrete-time scalar signal yand ycontaining measured dynamics of the flexible structure, being yand yan nsample of the respective signal provided by a first (A) and second (B) active measurement source, this sampling being performed with a sample time Δt, and the nsample of a signal being n∈:n∈[1, ∞),'}{'sub': n', 'n, 'sup': A', 'B, 'claim-text': [{'sub': 'n', 'sup': 'F', 'first elastic mode (i=1) estimated activity signal {circumflex over (γ)}in free-movement status,'}, {'sub': 'n', 'sup': 1', {'sub2': 'R'}], 'first elastic mode (i=1) estimated activity signal γin restricted-movement status,'}], 'b) obtaining from the first and second yand ysampled signals the following signals{'sub': n', 'n', 'n', 'n', 'n', 'n, 'sup': 1 ...

SYSTEM AND METHOD FOR MULTIPLEXED AND BUFFERED MINIATURIZED SENSOR ARRAYS

A miniature pressure scanning system includes a plurality of miniature pressure sensors where each pressure sensors includes at least one sensor output for providing an analog output signal indicative of a detected pressure on a body, and each pressure sensor output has an associated output impedance; a plurality of buffers, each buffer electrically connected to the output port of a corresponding one of the pressure sensors, and configured to reduce the associated output impedance of the corresponding sensor output coupled thereto, and further configured to provide at an output of the buffer the analog output pressure signal from the pressure sensor; and a multiplexer coupled downstream of the plurality of buffers and configured to multiplex the buffered analog output pressure signals to output a multiplexed analog signal representing the detected pressures.

METHOD FOR DETERMINING THE AERODYNAMIC MOMENT OF RESISTANCE OF A WHEEL

A method for determining the aerodynamic moment of resistance Mof a wheel by calculating the variation with respect to time, of the product of the rotational speed of at least one wheel set in rotation about an axis and of the inertia of the said wheel about the said axis, the wheel being equipped with a device for picking off and recording the numerical values of its rotational speed. The wheel is protected by a removable cap and in is subjected to a flow of air. 2. The method according to claim 1 , wherein the flow of air has a main direction substantially parallel to that of the wheel.3. The method according to claim 1 , wherein the flow of air has a main direction forming an angle of between −40° and +40° with respect to that of the wheel.4. The method according to claim 1 , wherein the axis of the wheel remains fixed relative to the ground.5. The method according to claim 1 , wherein the flow of air has a speed equal to that of the rolling road.6. The method according to claim 1 , wherein the flow of air has a speed different from that of the rolling road.7. The method according to claim 1 , wherein the wheel comprises at least one means of holding the wheel suspension. This application is a 371 national phase entry of PCT/EP2013/062695, filed 19 Jun. 2013, which claims benefit of French Patent Application Serial No. 1256123, filed 27 Jun. 2012, the entire contents of which are incorporated herein by reference for all purposes.1. FieldThe disclosure relates to a method for determining precisely the aerodynamic moment of resistance of a wheel. This method applies to land transport vehicles.2. Description of Related ArtIt will be recalled that a wheel is defined as being made up of a rim, of a wheel disc and of a tire. The tire, also referred to as the casing, is mounted on the rim to form a wheel.Regulatory measures of fuel consumption and pollution are currently made on light cars and light utility vehicles in numerous countries. Unfortunately, these ...

Determining at least one characteristic of a boundary layer of a wind turbine rotor blade

Provided is a method for determining at least one characteristic of a boundary layer a wind turbine rotor blade, including capturing at least one movement of at least one flexible element of at least one sensor being attached to or being part of a surface of the rotor blade, determining the at least one characteristic of the boundary layer based on the at least one captured movement of the at least one flexible element. Further, a sensor device, a wind turbine and a device as well as a computer program product and a computer readable medium are suggested for performing the method.

SENSING AND CONTROL OF FLOWS OVER MEMBRANE WINGS

A method includes simultaneously controlling and sensing aerodynamic loading of a membrane wing using a capacitance of the membrane, the membrane wing stretching under aerodynamic load, leading to thinning of a membrane thickness and increased capacitance, and using knowledge of the membrane's elastic and dielectric material properties to determine an amount of steady aerodynamic lift being generated 1. A method comprising:providing an extensible membrane wing;performing integrated camber sensing, a camber measured via capacitance of a dielectric elastomer membrane that is sandwiched between two compliant electrodes, wherein a relationship between capacitance and camber is defined; andestimating a load on the extensible membrane wing using the camber.2. The method of wherein the relationship is geometric.3. The method of wherein the geometric relationship is a spherical cap.4. The method of wherein the capacitance is measured using a recursive least squares (RLS) adaptive algorithm.5. A method comprising:simultaneously controlling and sensing aerodynamic loading of a membrane wing using a capacitance of the membrane, the membrane wing stretching under aerodynamic load, leading to thinning of a membrane thickness and increased capacitance; andusing knowledge of the membrane's elastic and dielectric material properties to determine an amount of steady aerodynamic lift being generated and time-dependent properties.6. The method of wherein the time-dependent properties include time-dependent capacitance.7. The method of wherein the time-dependent properties are related to a vortex shedding frequency and amplitude.8. The method of wherein a relationship between capacitance and camber of the membrane is used to infer a chamber.9. The method of wherein a lift is inferred from the chamber.10. The method of wherein the camber is measured by a capacitance of the dielectric elastomer membrane.11. The method of wherein a mean aerodynamic load is captured by applying an ...

METHOD FOR DETERMINING THE AERODYNAMIC MOMENT OF RESISTANCE OF A WHEEL

A method for determining the aerodynamic moment of resistance Mof a wheel arranged on an axis, by measuring the value of the mechanical power Pto be applied to the wheel in order to maintain it in rotation at a constant speed ω, the said wheel being equipped with a rotational-drive means and with a device for picking off and/or recording the numerical values of the said mechanical power and those of the rotational speed. The wheel is protected by a removable cap and is subjected to a flow of air. 2. The method according to claim 1 , wherein the flow of air has a main direction substantially parallel to that of the wheel.3. The method according to claim 1 , wherein the flow of air has a main direction at an angle of between −40° and +40° with respect to that of the wheel.4. The method according to claim 1 , wherein the axis of the wheel remains fixed relative to the ground.5. The method according to claim 1 , wherein the flow of air has a speed identical to that of the rotational-drive means.6. The method according to claim 1 , wherein the flow of air has a speed different from that of the rotational-drive means.7. The method according to claim 1 , wherein the wheel comprises at least one means of holding the wheel suspension. This application is a 371 national phase entry of PCT/EP2013/062696, filed 19 Jun. 2013, which claims benefit of French Patent Application No. 1256260, filed 29 Jun. 2012, the entire contents of which are incorporated herein by reference for all purposes.1. FieldThe disclosure relates to a method for determining precisely the aerodynamic moment of resistance of a wheel. This method applies to land transport vehicles.2. Description of Related ArtIt will be recalled that a wheel is defined as being made up of a rim, of a wheel disc and of a tire. The tire, also referred to as the casing, is mounted on the rim to form a wheel.Regulatory measures of fuel consumption and pollution are currently made on light cars and light utility vehicles in ...

WIND TUNNEL BALANCE FOR MULTIPLE CONFIGURATION

A test bench, in particular a convertible wind channel balance, including a lifting frame for lifting at least one wheel belt unit, wherein the wheel belt unit has at least one belt which is looped around at least two rollers, a weighing platform, which is mounted so as to be relatively movable in relation to a test bench frame, at least one force sensing member arranged between the weighing platform and the test bench frame in order to sense forces between the weighing platform and the test bench frame, wherein at least one self-centering docking member is provided between an auxiliary frame and the weighing platform. 1. A test bench , in particular a convertible wind tunnel balance , comprisinga lifting frame for lifting at least one wheel belt unit, the wheel belt unit having at least one belt which is looped around at least two rollers,a weighing platform which is mounted so as to be relatively movable in relation to a test bench frame,at least one force sensing member arranged between the weighing platform and the test bench frame for sensing forces between the weighing platform and the test bench frame,whereinat least one self-centering docking member is provided between an auxiliary frame and the weighing platform.2. The test bench according to claim 1 , wherein the at least one docking member contains a first docking device and a second docking device.3. The test bench according to claim 2 , wherein the first docking device is provided on the auxiliary frame and the second docking device is provided on the weighing platform claim 2 , wherein the first and second docking devices engage in one another in a self-centering manner when the lifting frame is lowered.4. The test bench according to claim 1 , wherein the at least one docking member is designed as a truncated cone with a counterpart.5. The test bench according to claim 1 , wherein the at least one docking member is designed as a cutting pan claim 1 , wherein a first docking device is provided in the ...

Method and device for analyzing fluid around rotating body

A method for analyzing fluid around a rotating body includes: a step (S 100 ) in which a spatial model having a rotating computational mesh cell group A and a stationary computational mesh cell group B is acquired; a step (S 101 ) in which a storage computational mesh cell group C is established; a step (S 102 ) in which arithmetic operations for fluid analysis are performed; a step (S 103 ) in which the physical quantity at the computational mesh cell making up the rotating computational mesh cell group A calculated as a result of arithmetic operations for fluid analysis is copied to a corresponding computational mesh cell at the storage computational mesh cell group C; and a step (S 104 ) in which averages over time are calculated for the physical quantities at the storage computational mesh cell group C and the stationary computational mesh cell group B.

LARGE-AMPLITUDE VERTICAL-TORSIONAL COUPLED FREE VIBRATION DEVICE FOR WIND TUNNEL TEST

A large-amplitude vertical-torsional coupled free vibration testing device for wind tunnel test. The large-amplitude vertical-torsional coupled free vibration device for wind tunnel test includes rigid deck model, lightweight rigid rods, lightweight rigid circular aluminium hubs, the first thin strings, linear tensile vertical springs, and the second lightweight strings. Large-amplitude vertical-torsional coupled free vibrations of rigid deck models can be realized by using this device, in which the springs vertically deform without any tilt. In the traditional free vibration device, the spring may obviously tilt, and the linear torsional stiffness cannot be ensured. The device can be conveniently installed and the initial angle of attack can be easily adjusted. The extreme low and stable mechanical damping ratio required for large-amplitude vibrations can be readily guaranteed, owing to the invocation of the negligible rolling friction between the thin strings and the hub. 1. A large-amplitude vertical-torsional coupled free vibration device for wind tunnel test , wherein the device includes rigid deck model , lightweight rigid rods , lightweight rigid circular aluminium hubs , the first thin strings , linear tensile vertical springs , and the second lightweight strings; The rigid rods are fixed at both ends of the rigid model; the rigid rods are perpendicularly passed through the center of the hubs and fixed by screws to ensure that the torsional center line of the model is concentric with those of the rigid rods and the hubs; the lower half of hub is surrounded and supported by the first thin string , one end of the first string is fixed at the bottom of the hub , and the other end is connected with the lower end of the vertical spring; during the vertical-torsional coupled free vibration of both model and hubs , hubs rotate along the first strings , the second strings restrict the lateral vibration of rigid model , the first strings and the springs moving up and ...

FLUTTER DETECTION SENSOR

Systems and methods for monitoring aerostructures are provided. In various embodiments, a method for monitoring an aerostructure may include: receiving a signal from a pressure sensor, the pressure sensor located downstream from the aerostructure; performing a time frequency analysis on the signal to calculate a power level over a range of frequencies; monitoring the power level over the range of frequencies; and determining a susceptibility to a flutter condition based on the monitoring the power level. 1. A method for monitoring an aerostructure comprising:receiving, by a controller, a signal from a pressure sensor, the pressure sensor located downstream from the aerostructure;performing, by the controller, a time frequency analysis on the signal to calculate a power level over a range of frequencies;monitoring, by the controller, the power level over the range of frequencies; anddetermining, by the controller, a susceptibility to a flutter condition based on the monitoring the power level.2. The method of claim 1 , wherein the pressure sensor is capable of measuring a dynamic frequency with a Nyquist frequency greater than at least a third fundamental frequency of the aerostructure.3. The method of claim 1 , wherein the performing the time frequency analysis includes at least one of performing a Fourier transform claim 1 , a wavelet transform claim 1 , a bilinear time frequency distribution claim 1 , or a modified Wigner distribution function.4. The method of claim 1 , wherein the monitoring the power level includes determining a shift in the power level from a lower frequency to a higher frequency.5. The method of claim 1 , wherein the monitoring the power level includes calculating a change in the power level over the range of frequencies.6. The method of claim 5 , wherein the monitoring the power level includes calculating the change in the power level at a pre-determined frequency.7. The method of claim 1 , wherein the determining the susceptibility to the ...

Test bench for generating dynamic loads on an actuator and method for performing tests on an actuator using said test bench

A test bench for generating aerodynamic loads on an actuator to be tested includes a force actuator configured to generate at least one dynamic load, the test bench being configured to transmit the dynamic load produced by the force actuator to the actuator to be tested, and a controller for controlling the dynamic load generated by the force actuator depending on a pressure, measured by a pressure sensor, inside one of the chambers of the force actuator.

MODEL MOTION SYSTEM FOR A VEHICLE MODEL

A model motion system for providing controlled motion of a vehicle model with wheels on is provided. The model motion system includes a pitch system coupled to the vehicle model with wheels on to control a pitch range of motion of the vehicle; a roll system coupled to the vehicle model with wheels on to control a roll range of motion of the vehicle; and a yaw system coupled to the vehicle model with wheels on to control a yaw range of motion of the vehicle. The pitch system, the roll system, and the yaw system control the respective ranges of motion of the vehicle model with wheels on. 1. A model motion system for providing controlled motion of a vehicle model with wheels on comprising:a pitch system coupled to the vehicle model with wheels on to control a pitch range of motion of the vehicle;a roll system coupled to the vehicle model with wheels on to control a roll range of motion of the vehicle; anda yaw system coupled to the vehicle model with wheels on to control a yaw range of motion of the vehicle, wherein the pitch system, the roll system, and the yaw system control respective ranges of motion of the vehicle model with wheels on.2. The model motion system of further comprising a control system electronically coupled to the yaw system claim 1 , the pitch system claim 1 , and the roll system.3. The model motion system of claim 1 , wherein the pitch system further comprises a pitch drive.4. The model motion system of claim 1 , wherein the roll system further comprises a roll drive.5. The model motion system of claim 1 , wherein the yaw system further comprises a yaw drive.6. The model motion system of claim 1 , wherein the respective ranges of motion are achieved at least one of independently or in combination.7. The model motion system of claim 1 , wherein forces generated on any of the pitch system claim 1 , the roll system claim 1 , or the yaw system during testing limit an amount of deflection of the pitch system claim 1 , the roll system claim 1 , and the ...

REMOTELY CONTROLLED METHODS AND SYSTEMS FOR ACTUATING BOUNDARY LAYER TRANSITION DEVICES IN A WIND TUNNEL MODEL

A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states. 1. A system for reproducing aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions , the system comprising:a test component disposed in the wind tunnel test environment and defining an exterior surface;at least one trip dot mounted on the test component and having a first state, in which a distal surface of the at least one trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the at least one trip dot is at a second elevation relative to the exterior surface of the test component;an actuator operably coupled to the at least one trip dot and configured to transition the at least one trip dot between first and second states;a controller in communication with the actuator and configured to remotely cause the actuator to transition the at least one trip dot between the first and second states.2. The system of claim 1 , in which the actuator comprises a shape memory alloy wire mechanically coupled to the at least one trip dot and a heat source thermally coupled to the shape memory alloy wire.3. The ...

Balance for Air Resistance Testing

This disclosure provides a balance for air resistance testing, compromising 2N dual-hole beam sensors and an upper plate; wherein, the 2N dual-hole beam sensors are arranged beneath the upper plate and fixed to the upper plate; each said dual-hole beam sensor comprises a beam, an upper hole and a lower hole, the upper hole and the lower hole are arranged along the longitudinal direction of the beam, the upper hole is arranged at the upper part of the beam, and the lower hole is arranged at the lower part of the beam. 1. A balance for air resistance testing , characterized in that , it comprises: dual-hole beam sensors and an upper plate , whereinthe dual-hole beam sensors are arranged beneath the upper plate and fixed to the upper plate;the dual-hole beam sensor comprises a beam, an upper hole and a lower hole, wherein the upper hole and the lower hole are arranged along the longitudinal direction of the beam, the upper hole is arranged at the upper part of the beam, and the lower hole is arranged at the lower part of the beam;the dual-hole beam sensor further comprises a first strain gauge, a second strain gauge, a third strain gauge and a fourth strain gauge, wherein the first strain gauge and the third strain gauge are arranged on the outer side of the lower part of the beam, and the first strain gauge and the third strain gauge are arranged symmetrically with respect to the lower hole; the second strain gauge and the fourth strain gauge are arranged on the outer side of the upper part of the beam, and the second strain gauge and the fourth gauge are arranged symmetrically with respect to the upper hole.2. The balance for air resistance testing according to claim 1 , characterized in that claim 1 , the beam has a cuboid shape.3. The balance for air resistance testing according to claim 1 , characterized in that claim 1 , the upper hole and the lower hole are both circular holes.4. The balance for air resistance testing according to claim 1 , characterized in that ...

APPARATUS AND METHOD FOR NON-INTRUSIVE OFF-BODY MEASUREMENTS IN HYPERSONIC FLIGHT EXPERIMENTS

An “air-data probe” system measures at least one component of freestream velocity by tracking the motion of a laser-induced breakdown (“LIB”) spark created in a freestream flow. Neutral density filters are positioned or deployed so that the brightness of the initial LIB spark doesn't over saturate the LIB sensor system. This allows for more consistent tracking of the LIB spark throughout the duration of the LIB spark, including the later stages where the LIB spark is not nearly as bright as the initial LIB spark, thereby allowing all or substantially all of the light generated by the LIB spark to reach the sensors. This provides for enhanced visibility and more accurate detection of the LIB spark over time and as air density changes. 1. A method of measuring at least one component of freestream velocity for a vehicle comprising the steps of:providing at least one laser;providing a plurality of cameras;generating a laser-induced breakdown spark from the at least one laser at a point away from the vehicle;positioning at least one neutral density filter between the cameras and the laser-induced breakdown spark;using the plurality of cameras to monitor and capture a plurality of physical characteristics associated with the laser-induced breakdown spark over time; andcalculating at least one component of freestream velocity by using the monitored plurality of physical characteristics associated with the laser-induced breakdown spark.2. The method of wherein the step of positioning the at least one neutral density filter between the cameras and the laser-induced breakdown spark comprises the steps of:positioning a plurality of neutral density filters between the cameras and the laser-induced breakdown spark; andselectively altering which of the plurality of neutral density filters is positioned between the cameras and the laser-induced breakdown spark based on at least one of: passage of time; or changes in air density surrounding the laser-induced breakdown spark.3. The ...

SYSTEM AND METHOD FOR TESTING AERODYNAMIC CHARACTERISTIC OF HIGH-SPEED MOVING VEHICLE-BRIDGE SYSTEM AND SUBSIDIARY FACILITIES THEREOF UNDER CROSSWIND

A system for testing aerodynamic characteristics of a high-speed moving vehicle-bridge system and subsidiary facilities thereof under a crosswind includes a vehicle model, a starting mechanism, a buffer mechanism, a wind tunnel test section and guide rails. The guide rails pass through the wind tunnel test section; the starting mechanism and the buffer mechanism are separately located at both ends of the guide rails. The guide rails include an acceleration section and a deceleration section. The starting mechanism is located in the acceleration section, and the buffer mechanism is located in the deceleration section; the vehicle model starts to run at the starting mechanism and stops at the buffer mechanism; an instantaneous speed of the vehicle model in the acceleration section is not less than 100 km/h. The present invention carries out simulation tests on various infrastructures, their subsidiary facilities and trains through scale models. 1. A system for testing aerodynamic characteristics of the high-speed moving vehicle-bridge system and subsidiary facilities of the high-speed moving vehicle-bridge system under the crosswind , comprising a vehicle model , a starting mechanism , a buffer mechanism , a wind tunnel test section and guide rails , whereinthe guide rails pass through the wind tunnel test section; the starting mechanism and the buffer mechanism are separately located at both ends of the guide rails;the guide rails comprise an acceleration section and a deceleration section; the starting mechanism is located in the acceleration section, and the buffer mechanism is located in the deceleration section; the vehicle model starts to run at the starting mechanism and stops at the buffer mechanism; andan instantaneous speed of the vehicle model in the acceleration section is not less than 100 km/h.2. The system according to claim 1 , wherein the starting mechanism comprises the high-speed servo motor claim 1 , rotating pulleys claim 1 , an external toothed ...

SYSTEM AND METHOD FOR MULTIPLEXED AND BUFFERED SENSOR ARRAYS

A miniature pressure scanning system may comprise: a plurality of miniature pressure sensors including a plurality of sensor outputs, each of the miniature pressure sensors including at least one sensor output for providing an analog output signal and each at least one sensor output having an associated output impedance; a plurality of buffers, each buffer of said plurality of buffers being electrically coupled to one sensor output of the plurality of sensor outputs, and each said buffer being operative to reduce a settling time constant associated with multiplexer voltage spikes and reduce the associated output impedance of the one sensor output coupled to it; and at least one multiplexer electrically coupled to the plurality of sensor outputs, said at least one multiplexer being operative to be switched between each of the plurality of sensor outputs. 1. A miniature pressure scanning system comprising:a plurality of miniature pressure sensors including a plurality of sensor outputs, each of the plurality of miniature pressure sensors including at least one sensor output for providing an analog output signal indicative of a detected pressure on a body, and each at least one sensor output having an associated output impedance;a plurality of buffers, each buffer comprising a buffer transistor and a bias resistor electrically connected to the sensor output of a corresponding one of said miniature pressure sensors, and configured to (1) reduce a settling time constant associated with multiplexer voltage spikes, (2) reduce the associated output impedance of the sensor output of the corresponding miniature pressure sensor coupled thereto, and (3) provide at a buffered output of said buffer the analog output signal indicative of the detected pressure on the body from the miniature pressure sensor; anda multiplexer coupled downstream of the plurality of buffers and configured to multiplex the buffered analog output signals indicative of the detected pressure on the body to ...

Method for Providing Simulated Smoke and a Smoke Generator Apparatus Therefor

An apparatus is provided for providing simulated smoke. The apparatus comprises a reservoir including a reservoir port, and a bladder disposed in the reservoir. The bladder can be deflated to cause a fluid substance to flow through the reservoir port into the reservoir to fill the reservoir with the fluid substance to generate smoke. The bladder can be inflated to cause smoke to flow out of the reservoir through the reservoir port to provide simulated smoke. 1. A method for providing simulated smoke , the method comprising:filling a reservoir with smoke of a predetermined density; andreleasing smoke of the predetermined density from the reservoir at a rate such that the density of the released smoke is relatively consistent.2. The method according to wherein filling a reservoir with smoke of a predetermined density includes:filling the reservoir with smoke of an optical obscuration density.3. The method according to wherein filling the reservoir with smoke of an optical obscuration density includes:filling the reservoir with smoke of an optical obscuration density between about 600 percent obscuration per foot and about 50 percent obscuration per foot.4. The method according to wherein releasing smoke of the predetermined density from the reservoir at a rate such that the density of the released smoke is relatively consistent includes:releasing smoke of the predetermined density from the reservoir at a rate between about 0.5 cubic feet per minute and about 10 cubic feet per minute.5. The method according to wherein releasing smoke of the predetermined density from the reservoir at a rate such that the density of the released smoke is relatively consistent includes:releasing smoke of the predetermined density from the reservoir at a rate such that the density of the released smoke is relatively consistent between about 600 percent obscuration per foot and about 50 percent obscuration per foot.6. The method according to wherein releasing smoke of the predetermined ...

TEST FIXTURE TO MEASURE THE AVERAGE SKIN FRICTION OF ANISOTROPIC SURFACES

A test fixture for measuring the skin friction of anisotropic surface finish on a material is described. The test fixture can be utilized in a wind tunnel. The test fixture can include a plate having a cavity configured to receive a circular specimen disk. A motor can be coupled to the plate to rotate the circular specimen disk. During a test, a fluid can flow over the plate in a particular direction and the motor can rotate the circular specimen disk to determine the effect of the flow angle on the average skin friction coefficient of a surface finish of a material. The circular specimen disk can easily be attached and detached from the test fixture to allow circular specimen disks with different surface finishes to be tested. 1. A test fixture for measuring skin friction of a surface finish on a material comprising:a plate including a circular cavity configured to receive a circular specimen disk having the surface finish wherein the surface finish is aligned with a top surface of the plate when the circular specimen disk is placed in the circular cavity and wherein during operation of the test fixture a fluid flows over the plate and the circular specimen disk;a motor assembly, coupled to plate, configured to rotate the circular specimen disk through a plurality of angles relative to a direction of a fluid flow during operation of the test fixture;a first pressure rake, coupled to the plate, positioned upstream of the circular specimen disk, configured to measure first total pressures throughout a height of an upstream boundary layer;a second pressure rake, coupled to the plate, positioned downstream of the circular specimen disk, configured to measure second total pressures throughout a height of a downstream boundary layer; anda plurality of static pressure taps in a top surface of the plate for measuring static pressures on the top surface of the plate wherein the first total pressures, the second total pressures and the static pressures are used to determine ...

SYSTEM AND METHOD FOR OPTIMIZING PASSIVE CONTROL STRATEGIES OF OSCILLATORY INSTABILITIES IN TURBULENT SYSTEMS USING FINITE-TIME LYAPUNOV EXPONENTS

A system and method for optimizing passive control strategies of oscillatory instabilities in turbulent systems using finite-time Lyapunov exponents are disclosed. The method includes receiving data from one or more measuring devices connected to the turbulent flow system incorporating a control strategy in the flow field. One or more flow characteristics are determined from the data obtained from the measuring devices. The method involves computing critical dynamics from backward time finite-time Lyapunov exponent (FTLE) field based on the one or more flow characteristics. Next, one or more regions of critical dynamics associated with impending oscillatory instabilities in the turbulent flow system are identified. The identified region of critical dynamics is disrupted the control the onset of oscillatory instabilities in the turbulent flow system. 1. A computer implemented method of controlling onset of oscillatory instabilities in a turbulent flow system , the method comprising:receiving data from one or more measuring devices connected to the turbulent flow system incorporating a control strategy in the flow field;determining one or more flow characteristics from the data obtained from the measuring devices;computing critical dynamics from backward time finite-time Lyapunov exponent (FTLE) fields based on the one or more flow characteristics;identifying one or more regions of critical dynamics associated with impending oscillatory instabilities in the turbulent flow system; anddisrupting the identified region of critical dynamics to control the onset of oscillatory instabilities in the turbulent flow system.2. The method as claimed in claim 1 , wherein the data is received using Particle Image Velocimetry (PIV) technique or Computational Fluid Dynamics (CFD) methods comprising Direct Numerical Simulations (DNS) and Large Eddy Simulation (LES) claim 1 , and a photomultiplier tube and high speed cameras.3. The method as claimed in claim 1 , comprising performing ...

Method and device for increasing measurement accuracy in wind tunnel, which enable to take account of effect of model suspension device

FIELD: physics. ^ SUBSTANCE: method involves mounting a model aircraft in a wind tunnel using a suspension device which has several wires, whereby each wire has at least one cladding which increases diametre of the wire, taking at least two measurements for similar configurations of the model for at least one external diametre and for diametre of the wire of the suspension device so as to determine at least two rough values of the measured quantity, and determination of the final corrected measurement result for the model based on at least two rough values of the measured quantity. The final measured value of the drag coefficient, which is corrected in order to exclude the effect of the suspension device and interaction of the model and the suspension device, can be determined based on the rough measured values through interpolation. In accordance with another version, correction is carried out by determining the difference between only two rough measured values, where one of the rough measured values is determined for the diametre of the wires of the suspension device (without cladding). The method is suitable for correcting aerodynamic parametres which can be measured in a wind tunnel. A device in which the said method is realised has a suspension device made from several wires, where each wire has at least one cladding which increases the diametre of the wire. ^ EFFECT: higher measurement accuracy. ^ 19 cl, 2 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 399 895 (13) C2 (51) МПК G01M 9/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21), (22) Заявка: 2007127641/28, 22.12.2005 (24) Дата начала отсчета срока действия патента: 22.12.2005 (72) Автор(ы): МЭЙ Питер (DE), ШВЕТЦЛЕР Дитлев (DE) (43) Дата публикации заявки: 27.01.2009 2 3 9 9 8 9 5 (45) Опубликовано: 20.09.2010 Бюл. № 26 (56) Список документов, цитированных в отчете о поиске: US 3276251 А 04.10.1966. JP 7301578 A 14.11.1995. US ...

Method and apparatus for simulating microburst windshears

A method and apparatus for simulating a windshear. A vortex is modelled in terms of a family of concentric streamlines and the position of an aircraft is defined with respect to the vortex as the aircraft traverses a reference plane. Four or more vortices are used to generate streamlines which match those encountered in an actual microburst. Each vortex placed above the simulated ground level is matched by a vortex of equal strength but opposite rotation placed below the simulated ground level at a distance equal but opposite to the height of the vortex above the ground. Strengths, distance from the vortex center, and height of the vortex may be programmed by the user. The high degree of flexibility permits accurate reproduction of the winds generated by actual microbursts for testing and developing microburst detection devices. The use of an algorithm which may be dynamically varied as a function of aircraft position obviates the need for simulating by discrete windshear magnitude as in conventional predetermined windshear tables and minimizes data storage requirements.

Stand for measurement of loads influencing on the object of aviation equipment

FIELD: aircraft engineering. SUBSTANCE: invention relates to devices designed for aerodynamic testing, and can be used in aircraft building. Stand includes a dynamometer platform, designed to fix the object, installed by means of at least four variable hardness plates on a fixed support platform with the possibility of moving the dynamometer platform along three orthogonal axes, each plate being formed with a flexible portion, coupled with hard parts, and is equipped with a load measuring element, and is characterized in that it comprises a sensor, registering the longitudinal movements of the dynamometer platform and designed to measure the longitudinal load, and the load measuring element is made in the form of two pairs of identical strain gage sensors, intended for measuring vertical and lateral loads, installed on at least one flexible section of each plate at the same level relative to the fixed support platform, sensors of each pair are mounted on opposite wide sides of the plate, wherein the vertical symmetry axes of the sensing elements of the sensors of one pair are oriented along the vertical axis of symmetry of the wide side of the plate, and the vertical axis of symmetry of the sensing elements of the sensors of the other pair are parallel to it, sensors are connected in one arm of separate measuring bridges, and the sensors of each pair are connected in series. EFFECT: technical result consists in the possibility of increasing the accuracy of simulating the conditions of a supersonic flight of an aircraft. 1 cl, 12 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 651 627 C1 (51) МПК G01M 9/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01M 9/06 (2006.01) (21)(22) Заявка: 2017110035, 27.03.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: 23.04.2018 (45) Опубликовано: 23.04.2018 Бюл. № 12 2 6 5 1 6 2 7 R U (56) Список документов, цитированных в отчете о поиске: RU 127464 ...

Aerometric pressure sensor

FIELD: measuring equipment.SUBSTANCE: device relates to an instrumentation technique and can be used to measure the height and speed of flight of aircraft based on the use of the aerometric method. Device comprises a housing with two openings, two main membranes, tightly attached along the perimeter to the housing and forming a gap by spacing in height, the holes communicating with the measured medium are placed above and below the gap, mounted on the rack a radiation source and, in addition, the upper and lower curtains with slots. Device also contains two photodetector bars, with the geometric centers of the upper and lower main membranes containing openings that are blocked on the outer sides of the membranes with respect to the gap by additional upper and lower membranes, tightly attached along the perimeter to the outer sides of the main membranes, with the photo-receiving lines attached to the upper and lower additional membranes respectively and facing the slots of the upper and lower curtains.EFFECT: increasing the sensitivity and accuracy of pressure measurement both in altitude and in flight speed of the aircraft.1 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 684 683 C1 (51) МПК G01L 7/08 (2006.01) G01L 11/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01L 7/08 (2018.08); G01L 11/02 (2018.08); G01M 9/06 (2018.08) (21) (22) Заявка: 2017139645, 14.11.2017 (24) Дата начала отсчета срока действия патента: 14.11.2017 11.04.2019 Приоритет(ы): (22) Дата подачи заявки: 14.11.2017 (45) Опубликовано: 11.04.2019 Бюл. № 11 1076787 A1, 28.02.1984. US 4787396 A1, 29.11.1988. SU 1500889 A1, 15.08.1989. (54) ДАТЧИК АЭРОМЕТРИЧЕСКИХ ДАВЛЕНИЙ (57) Реферат: Устройство относится к контрольноизмерительной технике и может быть применено для измерения высоты и скорости полета воздушных судов на основании использования аэрометрического метода. Устройство содержит корпус с двумя отверстиями, две основные ...

一种气浮式应变天平

本发明公开了一种气浮式应变天平，该天平为组合式天平，包括芯轴、轴向力组件、五分量组件、保护套，所述芯轴包括锥形连接段和等直段，所述芯轴与轴向力组件配合安装，轴向力组件与五分量组件配合安装，轴向力组件固定端与芯轴固定，其活动端与五分量组件固定端固定，五分量组件活动端与被测模型固定。所述轴、轴向力组件和五分量组件同轴。压缩气体从芯轴固定端充入，通过芯轴前端的气孔使轴向力组件活动端与芯轴之间因充满压缩气体而形成气浮轴承，可使轴向力组件与芯轴之间的摩擦阻力忽略不计，提高了轴向力的测量灵敏度和精度。

一种用于高超声速风洞滚转强迫振动动导数试验装置

一种用于高超声速风洞滚转强迫振动动导数试验装置，油缸的后端和中轴的前端连接，支杆的后端和油缸的前端连接；油缸驱动杆沿着轴向做前后方向简谐运动；推杆随着油缸驱动杆沿着轴向做前后方向简谐运动；推轮杆沿着与轴向垂直的方向连接在推杆的前端，推轮杆的两端分别连接一个推轮，使得推轮沿着轴向做前后方向简谐运动；滚转铰链设置在支杆的前端，力矩梁转轴沿着与轴向垂直的方向连接在滚转铰链的后端，滚转力矩梁的前端与滚转铰链的前端连接，力矩梁转轴与滚转力矩梁连接，滚转力矩梁将推轮前后方向简谐运动转换为滚转力矩梁围绕力矩梁转轴的旋转简谐运动，并使得滚转铰链围绕力矩梁转轴做旋转简谐运动。

一种测量亚音速二维流场的四孔探针

本发明属于叶轮机械测试技术领域，公开了一种测量亚音速二维流场的四孔探针，包括探针支杆1、探针头部2、过渡段3、引压管4和温度传感器线缆5，所述探针支杆1和探针头部2均为圆柱形，探针头部2通过过渡段3安装在探针支杆1上，探针头部2的圆柱面开有三个压力感受孔和一个温度感受孔，三个压力感受孔分别与探针头部2内封装的引压管连通，温度感受孔9同探针内部的温度传感器相连，引压管4和温度传感器线缆5通过探针支杆1内通道引出探针尾部。与现有的探针相比，本发明经过校准标定，可同时测量二维亚音速流场的总温、总压、流速、流动方向等参数，可以实现精确测量。

一种平板边界层流动显示实验示踪粒子播撒装置

本发明公开了一种平板边界层流动显示实验示踪粒子播撒装置，属于边界层近壁区流动测量领域。该装置包括示踪粒子发生器、储烟箱、壁面粒子散布箱；烟油经示踪粒子发生器中微型泵加压流入加热管加热气化，从喷嘴喷出形成示踪粒子；通过导烟管进入储烟箱，储烟箱壁面安装有轴流风机调整箱内粒子流动速度，再通过导烟管进入壁面粒子播散箱的空腔，经整流板整流，从薄壁盖板上设置的播散狭缝喷出，狭缝出口与实验平板呈15°夹角，在常用实验风速15‑30m/s下，可将示踪粒子均匀播散在在平板边界层近壁区域。该装置结构简单，解决了从风洞实验段入口播撒示踪粒子无法进入平板边界层内部的问题，为开展平板边界层流动显示实验及机理研究提供了良好的技术支持。

一种结冰风洞试验冰形测量方法

本发明公开了一种结冰风洞试验冰形测量方法，利用一块设置有与机翼翼型一致缺口的金属片，沿着水平方向推动金属片，使得机翼沿着金属片的缺口处卡入缺口内，当金属片与机翼完全接触后，抽出金属片，机翼表面的冰层上沿着机翼的翼型留下一个切面，用一块与金属片形状一致的测绘板插入冰层的切面内，沿着冰层表面在测绘板上画出一条曲线；将测绘板抽出，通过测量观察板上的曲线可以得出冰层的厚度和形状；本发明因为本方案的测量金属片是不固定的，因此通过对其进行加热的处理可以使得切割冰层快速，不会出现传统技术中的切割金属片被冰卡住的问题，因为不会因为抖动金属片从而破坏冰层的问题。

一种冰形测量辅助装置及方法

本发明适用于结冰风洞结冰试验的冰形测量技术领域，提供了一种冰形测量辅助装置，包括：主框架，所述主框架整体上沿竖直方向分布；热刀框组件，所述热刀框组件可沿所述主框架竖向移动；位置测量组件，所述位置测量组件用于用测量所述热刀框组件在所述主框架上的位置；所述热刀框组件包括主框件和副框件，所述主框件与所述副框件滑动连接，所述副框件可沿所述主框件水平移动。本发明的冰形测量辅助装置中，热刀框组件在所述主框架上的位置可调，因此，可以适用于不同的模型，克服了现有技术中需要重新设计新的辅助测量装置的缺陷，因此，本发明的冰形测量辅助装置对模型的适应性较好。

一种测量亚音二维非定常流场的三孔动态压力探针

本发明属于叶轮机械测试技术领域，公开了一种测量亚音二维非定常流场的三孔动态压力探针，包括探针支杆1、探针头部2、过渡段3和压力传感器线缆4，所述的探针支杆1和探针头部2均为圆柱形，探针头部2通过过渡段3安装在探针支杆1上，探针头部2的圆柱面开设有三个压力感受孔，三个压力感受孔分别与探针头部2内部封装的三个压力传感器相连，压力传感器线缆通过探针支杆1内通道引出探针尾部。与现有的探针测试技术相比，本发明经过校准标定，可进行二维亚音速流场总压、马赫数和流动方向的测量，可以用于叶轮机械试验测试。

A kind of schlieren edge of a knife accurate positioning device based on image

本发明涉及纹影刀口精确定位技术领域，具体涉及一种基于图像的纹影刀口精确定位装置。包括：光源、纹影镜、刀口、轴向平移台、切割平移台、运动控制器、相机、镜头、计算机、支架。光源经纹影镜成像于焦面；安装纹影刀口精确定位装置时，将刀口大致安装在焦面上，并切割一部分光源像；镜头4将实验区域的纹影图像成像在相机上；计算机内安装有运行软件，用于控制相机和运动控制器；运动控制器通过接收运行软件指令控制轴向平移台和切割平移台移动。本发明设计的装置通过将纹影图像分析和电动平移台相结合，可将纹影仪的刀口自动精确定位在焦面内、并可定量控制刀口的切割量，进而提高实验质量和效率。

Compound large-resistance wind-tunnel strain balance

本发明公开了一种复合式大阻力风洞应变天平，包括复合式回路天平和支杆，所述复合式回路天平包括自由端过渡段、2号支撑段、1号支撑段、固定端过渡段、支杆连接段；所述支杆包括锥形连接段和等直段；所述自由端过渡段通过位于左右两侧的四柱梁(即侧力、俯仰力矩和滚转力矩测量元件)与2号支撑段连接；所述固定端过渡段通过位于上下两侧的两柱梁(即升力和偏航力矩测量元件)与1号支撑段连接；1号支撑段与2号支撑段通过位于内侧的四柱梁(即阻力测量元件)连接；所述支杆连接段与支杆的锥形连接段连接。本发明缩短了天平长度，增大了天平直径，提高了天平承载能力，提高了试验的安全性，延长了天平使用寿命。

Rotating shaft balance for propeller power influence wind tunnel test

本发明公开了一种螺旋桨动力影响风洞试验用旋转轴天平，其特征在于，包括电路设计、结构设计和可靠性设计，所述电路设计包括放大电路设计、滤波电路设计和测温电路设计，所述结构设计包括PCB结构和接插件，本发明涉及一种螺旋桨动力影响风洞试验用旋转轴天平，利用仪表放大器和精密运放实现增益调节和差分输入输出，通过RC低通滤波滤除高频干扰，通过仪表运算放大器来实现200倍的增益放大，具有鲁棒的输入过压保护，确保其稳定性，并且不牺牲噪声性能，具有高ESD抑制能力和针对来自相反供电轨、高达40V的连续电压输入保护，通过一个电阻可将增益设置为1至1000，基准引脚可用来向输出电压施加精确失调，提高测量精度和稳定性。

A kind of supersonic flow field total pressure measure apparatus and measurement method

本发明涉及一种超声速流场总压测量装置及测量方法，总压测量装置包括总压管，冷水加压装置和压力测量装置；总压管包括第一空腔以及环绕在第一空腔外部的水冷夹层；所述第一空腔为测压孔，顶端为气流入口，尾端为气流出口；所述水冷夹层的侧壁环绕第一空腔的侧壁，形成第二空腔，并裸露出气流入口和气流出口；水冷夹层的前端面连接侧壁的顶端，水冷夹层的后端具有注水开口，水冷夹层前端面和侧壁前端分别具有均布的小孔，小孔的直径不大于0.5mm。本发明的总压测量装置与常规总压测量相比，降低了总压管的尺寸，更能够适用于高温条件下超声速流场的总压的测试，可以承受长时间气动加热条件。

Aqua-aerodynamic pipe

FIELD: test equipment. SUBSTANCE: invention relates to devices for conducting aerodynamic tests. In the aqua-aerodynamic pipe tests are carried out by immersing the test object in aqueous medium. In this case, additional liquid may be used to visualize the flow, collected after flowing round test object in collection chamber, and/or a dye that dissolves in aqueous medium and/or retained by filters in the flow path. When testing objects in aqueous medium, correction index can be used, taking into account density of test object, external pressure on scales and possible floatability. EFFECT: technical result is to improve quality of the tests. 1 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 652 137 C1 (51) МПК G01M 10/00 (2006.01) G01M 9/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ На основании пункта 1 статьи 1366 части четвертой Гражданского кодекса Российской Федерации патентообладатель обязуется заключить договор об отчуждении патента на условиях, соответствующих установившейся практике, с любым гражданином Российской Федерации или российским юридическим лицом, кто первым изъявил такое желание и уведомил об этом патентообладателя и федеральный орган исполнительной власти по интеллектуальной собственности. (52) СПК (21)(22) Заявка: 2016148153, 08.12.2016 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Перфильев Вячеслав Сергеевич (RU) Дата регистрации: 25.04.2018 (56) Список документов, цитированных в отчете о поиске: RU 2561829 C2, 10.09.2015. RU Приоритет(ы): (22) Дата подачи заявки: 08.12.2016 2561829 C2, 10.09.2015. SU 715953 A1, 15.02.1980. SU 557279 A1, 05.05.1977. RU 102257 U1, 20.02.2011. SU 1545128 A1, 23.02.1990. RU 2453820 C2, 20.06.2012. US 3835703 A, 17.09.1974. (54) Аквааэродинамическая труба (57) Реферат: Изобретение относится к устройствам для проведения аэродинамических испытаний. В аквааэродинамической трубе испытания проводятся путем погружения испытуемого ...

一种滚转角度调节装置

本发明提供了一种滚转角度调节装置，所述装置使用螺纹环、顶螺母和底螺母实现天平滚转角度的调节，结构简单易用，保证了天平校准时的安装的滚转角度与风洞试验时安装的滚转角度误差小于等于1′。

Compact wind tunnel instrument

PURPOSE: A compact wind tunnel is provided to create various controlled distributions of wind environments in low costs. CONSTITUTION: A compact wind tunnel capable of creating various distributions of wind environments comprises: a blowing unit(200) which generates a wind by a plurality of blowers(210) which are installed in coplanar and the number of the blower per square increased by downward; a testing unit(100) which is located at the front of the blower units and includes a sensing unit(700) which measures a wind distribution; and a control unit(600) which controls a discrete operation of blowers to generate intended wind distribution.

Wind power measuring equipment and method for power transmission iron tower model

本发明涉及一种输电铁塔模型的风力测量设备及其测量方法，风力测量设备，其包括用于放置输电铁塔模型的测量筒、粘贴在测量筒筒壁上的应变片和与应变片连接的应变分析仪；测量时，测量筒纵向放置，使测量筒的一端朝上，将输电铁塔模型放置在该端上，应变分析仪采集应变片的应变值数据，根据模型受力与应变片的应变值的对应关系以及施加风力前后的应变片的应变值的变化，获得模型受到的风力的大小。本发明主要是通过测量筒上的应变片来测量输电铁塔模型受到的风力，测量筒可以根据输电铁塔模型的具体形状设计大小，适用于体积大、质量重的复杂输电铁塔模型的风力测量，而且测量过程简单，易于实现。

A kind of freely-supported type air tunnel testing device for growing thin component resistance coefficient

本发明公开了一种长细构件阻力系数的简支型风洞测试装置。在建筑风洞的试验段左右对称布置有结构相同的测力段；两支座上方分别固定有测力天平，测力天平上方分别固定有卡座，两支座固定于试验段地面，两卡座的开口朝向吹风方向。两卡座后侧面开口的导向面底部布置有弧形橡胶片，长细构件的试件两端圆杆的尺寸要求小于弧形橡胶片的直径；将试件的两端圆杆经导向面放置于两卡座的弧形橡胶片上，以形成简支型测力体系；将两二维流隔离箱分别罩于各自的测力段上，以形成二维流效应，通过两侧测力天平获得试件的阻力，从而获得试件的阻力系数。本发明测试长细杆件的阻力系数，克服传统测试装置的不足，为长细构件阻力系数的风洞测力试验提供新的途径。

A kind of carrier aircraft support prepared for captive trajectory testing ground

本发明属于航空气动力风洞试验技术领域，涉及一种用于捕获轨迹试验地面准备的载机支架。其特征在于：它包括门形支撑架、平移机构和导杆摇块机构；平移机构包括螺旋升降机5、直线导轨6、滑块安装板7和后支架9；导杆摇块机构包括伺服电动缸1、电动缸支架2、俯仰支臂4、后支架9、第1铰链组件10、第2铰链组件11和第3铰链组件12。本发明提出了一种用于捕获轨迹试验地面准备的载机支架，解决了捕获轨迹试验地面准备时载机无法支撑的难题，缩短了进行捕获轨迹试验状态的准备和检查占用的试验时间，提高了风洞的使用效率。

Wind tunnel test system

풍력 시험부의 턴테이블 하부에 별도의 밸런스 챔버를 구성하여 상기 풍력 시험부와 밸런스 챔버 내부의 공기압 차이를 제거하여 실차 공력 풍동 시험시, 휠 패드에 작용하는 양력을 소멸시켜 정확한 실차 공력 풍동 시험에 의한 차체의 공력 특성을 산출할 수 있도록 하는 실차 공력 풍동 시험용 시스템을 제공할 목적으로, A separate balance chamber is formed in the lower part of the turntable of the wind test part to remove the air pressure difference between the wind test part and the balance chamber, thereby eliminating the lift force acting on the wheel pads. In order to provide a system for testing aerodynamic wind tunnel of a real vehicle that can calculate the aerodynamic characteristics of 외부와 차단된 풍동 시험부의 전방에는 풍동 노즐부가 구성되고, 그 후방에는 확산부가 구성되며, 상기 풍동 시험부 내부에는 그 바닥면에 차체의 타이어가 얹혀지도록 4개의 휠 패드를 구성한 턴테이블이 구성되며, 상기 턴테이블의 하부에는 상기 4개의 휠 패드와 아암을 통하여 밸런스 시스템이 연결되어 상기 휠 패드로부터 전달되는 힘을 전달받아 밸런스 신호를 출력하도록 구성되는 실차 공력 풍동 시험용 시스템에서, A wind tunnel nozzle unit is formed at the front of the wind tunnel test unit, which is blocked from the outside, and a diffusion unit is formed at the rear of the wind tunnel test unit. A turntable including four wheel pads is configured to place a tire of the vehicle body on the bottom surface of the wind tunnel test unit. In the lower part of the turntable, a balance system is connected through the four wheel pads and the arms, and receives a force transmitted from the wheel pads and outputs a balance signal. 상기 밸런스 시스템을 내부에 포함하도록, 상기 풍동 시험부의 바닥면 턴테니블 하부에 외부와 기밀이 유지되도록 설치되는 밸런스 챔버와; 상기 풍동 시험부 내부의 휠 패드 일측과 밸런스 챔버 내부의 공기압 차이를 검출하여 밸런스 챔버 내부의 공기압을 조절하여 상기 공기압 차이를 제거하도록, 상기 밸런스 챔버에 구성되는 압력제어수단을 포함하는 것을 특징으로 하는 실차 공력 풍동 시험용 시스템을 제공한다. A balance chamber installed to keep the outside and airtight under the bottom turntable of the wind tunnel test part to include the balance system therein; And a pressure control means configured in the balance chamber to detect the difference in air pressure between one side of the wheel pad inside the wind tunnel test unit and the balance chamber to adjust the air pressure inside the balance chamber to remove the difference in air pressure. Provides a real vehicle ...

PRESSURE RECEIVER

1. Приемник воздушных давлений, содержащий головную часть с расположенными на ней приемными отверстиями, соединенными пневмоканалами со штуцерами, и присоединенную к ней с тыльной стороны державку, отличающийся тем, что на поверхности головной части для осуществления сверхкритического обтекания и устранения влияния числа Re расположены турбулизаторы потока.2. Приемник воздушных давлений по п.1, отличающийся тем, что турбулизаторы потока выполнены в виде ребер, образованных в результате сопряжения элементов поверхностей под углом ξ≠0 с кривизной, лежащей в пределахи габаритными размерами в пределах 0.01Н÷0.4Н, где Н - минимальный габаритный размер головной части.3. Приемник воздушных давлений по п.2, отличающийся тем, что головная часть имеет форму выпуклого многогранника с числом плоских граней, лежащих в пределах 10÷1000.4. Приемник воздушных давлений по п.3, отличающийся тем, что головная часть имеет форму икосаэдра.5. Приемник воздушных давлений по п.3, отличающийся тем, что головная часть имеет форму додекаэдра.6. Приемник воздушных давлений по п.5, отличающийся тем, что головная часть имеет форму 192-гранника.7. Приемник воздушных давлений по п.3, отличающийся тем, что приемные отверстия расположены на гранях.8. Приемник воздушных давлений по п.1, отличающийся тем, что, турбулизаторы потока выполнены в виде выемок глубиной a≤0.1H и шириной b≤0.1Н или выступов высотой а≤0.1Н и шириной b≤0.1Н.9. Приемник воздушных давлений по п.1, отличающийся тем, что поверхность державки является гладкой или частично гладкой.10. Приемник воздушных давлений по п.9, отличающийся тем, что державка выполнена в виде многогранного цилиндра с диаметром РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК G01M 9/06 (13) 2013 140 011 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2013140011/28, 29.08.2013 Приоритет(ы): (22) Дата подачи заявки: 29.08.2013 (43) Дата публикации заявки: 10.03.2015 Бюл. № 7 A R U (57) Формула изобретения 1. ...

Single-vector loading method for wind tunnel mechanical balance

本发明公开了一种风洞机械天平单矢量加载方法，机械天平单矢量加载由力传递系统、力发生系统和控制系统三部分组成，力传递系统通过钢线将力源产生的力传递到加载点，加载点所受的力方向与X、Y、Z方向各有固定夹角，加载力可分解到三个方向分别对应天平的阻力、升力、侧力，加载点与天平坐标中心的偏移量决定了施加在天平上的力矩，该方案通过一个加载点可同时获得六个分量的加载载荷；本发明通过计算机控制技术实现力的精确控制，实现了自动加载，提高了加载的自动化水平，根据机械天平的特点选取合适的加载点，实现了矢量加载，及通过一个加载点，实现六个分量的同时加载，提高了加载效率。

Wind load real-time measuring room capable of changing roof form

本发明涉及一种可改变屋盖形式的风载荷实测房，属于建筑试验技术领域，包括屋盖，所述屋盖由若干矩形盖板阵列而成，相邻两个矩形盖板之间通过密封结构连接，每一矩形盖板的下方设置有用于控制所述矩形盖板单独进行驱动变换的驱动装置，若干矩形盖板共同变换实现了整个屋盖形式的变换，X向驱动装置带动矩形盖板绕其X向转动，所述Y向驱动装置带动X向驱动装置和矩形盖板同时绕矩形盖板的Y向转动，所述Z向驱动装置带动X向驱动装置、Y向驱动装置以及矩形盖板同时沿矩形盖板的Z向移动。本发明实测房屋可对屋盖形式进行变换，置于现场进行试验，可研究不同屋盖形式的气动构造特性对当地房屋风载荷的影响，从而能指导房屋的建设。

Method for testing the strength of the fairings made of brittle materials

FIELD: test equipment. SUBSTANCE: invention relates to a testing technique and can be used in testing the strength of shells of antenna fairings made of brittle materials, primarily ceramic, in static tests. Fairing is loaded by a control load in the form of a transverse force, or in the form of a longitudinal force, or in the form of a bending moment, or in the form of inertial forces on the acceleration stand, or in the form of an internal excess pressure, or in the form of forces from vibrational loads, or as a distributed pressure on the outer surface, or as a distributed pressure on the inner surface, or as a combination thereof, and then determine, by calculation, the tensile stress along the entire volume of the fairing and the probability of their destruction from the action of the operational and control loads, wherein the value of the magnitude of the reference force is determined from the condition that the fairness of the fairing is equal to the effect of the control and operational loads, and for the operational load, the maximum value of the fracture probability is selected from all calculated loading cases of the fairing in real flight. EFFECT: increase of the accuracy of the tests. 4 cl, 2 tbl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 654 320 C1 (51) МПК G01M 9/06 (2006.01) G01N 3/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01M 9/06 (2006.01); G01N 3/12 (2006.01) (21)(22) Заявка: 2017118861, 30.05.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: 17.05.2018 (45) Опубликовано: 17.05.2018 Бюл. № 14 2 6 5 4 3 2 0 R U (56) Список документов, цитированных в отчете о поиске: RU 2580265 C1, 10.04.2016. RU 2620782 C1, 29.05.2017. RU 2637176 C1, 30.11.2017. CN 102721612 B, 29.01.2014. (54) Способ испытания на прочность обтекателей из хрупких материалов (57) Реферат: Изобретение относится к испытательной их комбинации, а затем определяют расчетным технике и может ...

Fan yawing test mechanism and fan set testing bench

本发明公开一种风机偏航试验机构，包括：机舱支架，下端部固定在偏航基础上，上端部固定风机的机舱；塔筒工装，通过传动机构与塔筒工装驱动装置连接，在塔筒工装驱动装置作用下绕塔筒工装轴线旋转；上回转支承，安装在机舱的底架下部，用于实现塔筒工装相对于机舱运动；下回转支承，安装在偏航基础上，用于实现塔筒工装相对于偏航基础运动；偏航摩擦盘，夹设于上回转支承与塔筒工装上端部之间。在风机偏航试验时，塔筒工装旋转，而机舱固定不动；一方面，在风机拖动试验时可同步进行偏航试验，节省试验时间，提高试验效率，方便试验操作；另一方面，偏航试验时无需机舱偏转，可节省试验用空间，并方便安装。在此基础上，本发明还公开一种风机整机试验台。

One kind yawing forced vibration dynamic derivative experimental rig for hypersonic wind tunnel pitching

一种用于高超声速风洞俯仰偏航强迫振动动导数试验装置，油缸的后端和中轴的前端连接，支杆的后端和油缸的前端连接；油缸驱动杆沿着轴向做前后方向简谐运动；推杆随着油缸驱动杆沿着轴向做前后方向简谐运动；推轮杆沿着与轴向垂直的方向连接在推杆的前端，推轮杆的两端分别连接一个推轮，使得推轮沿着轴向做前后方向简谐运动；俯仰偏航铰链设置在支杆的前端，力矩梁转轴沿着与轴向垂直的方向连接在俯仰偏航铰链的后端，俯仰偏航力矩梁的前端与俯仰偏航铰链的前端连接，力矩梁转轴与俯仰偏航力矩梁连接，俯仰偏航力矩梁将推轮前后方向简谐运动转换为俯仰偏航力矩梁围绕力矩梁转轴的旋转简谐运动，并使得俯仰偏航铰链围绕力矩梁转轴做旋转简谐运动。

A kind of floating frame-type wind-tunnel balance

本发明公开了一种浮动框型风洞应变天平，解决了在某些大载荷测量试验时，现有常规天平承载能力弱、刚性差以及专用天平研制成本高、加工复杂、测量效果不佳的问题。该浮动框型大载荷容量风洞应变天平，包括第一内轴、浮动框体、第二内轴。浮动框体的前、后固定段分别与第一内轴及第二内轴刚性固定连接；第一内轴还和第二内轴刚性固定连接，并通过定位销固定，最终使第一内轴、浮动框体和第二内轴形成一个整体结构。浮动框体的弹性测量元件组和模型端的内径大于内轴沿轴向与之对应部分的外径，即浮动框体的浮动部分可沿轴向、周向和滚转方向自由变形移动。本发明结构简单、载荷容量大、刚度和测量精准度高、成本低、通用性好。

Coal mine transfer point induced airflow and dust measurement simulation experiment system

本发明涉及一种煤矿转载点诱导气流及粉尘测定模拟实验系统，预先在给料装置内装入煤料，下料高差不变的情况下，通过设定不同的溜槽倾角和不同的皮带速度，研究不同下料量对诱导气流和粉尘浓度影响；皮带速度不同的情况下，通过设定不同的下料量和溜槽倾角，研究不同下料高差对诱导气流和粉尘浓度影响；设定不同的溜槽倾角和不同的皮带速度，皮带速度设定为开启和运行两种状态，研究皮带启停对诱导气流和粉尘扩散的影响；溜槽倾角不变的情况下，通过设定不同的皮带速度和不同的下料量，研究皮带速度对诱导气流的影响。通过上述整个实验模拟系统，可以对煤矿井下转运点降尘提供理论支持。

Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance

本发明涉及一种同轴并联式轴向载荷测量的高精度风洞测力天平，属于风洞天平设计领域；包括前锥、径向四分量载荷测量元件、轴向载荷测量元件、等直段和后锥；径向四分量载荷测量元件包括两组结构相同的三柱梁，两组三柱梁分别设置在所述轴向载荷测量元件的轴向两端，组成六分量测量元件；前锥、六分量测量元件、等直段和后锥同轴依次连接，组成测力天平；轴向载荷测量元件包括外壳、阻力支撑片梁组、阻力测量梁、滚转力矩测量梁、中间壳体、支撑内轴和滚转力矩支撑片梁组；本发明确保了天平整体刚度较大的情况下，实现轴向载荷测量解耦、避免其他分量对轴向分量的测量干扰，提高测量精度。

High-precision resistance measuring method and device for wind tunnel experiment

一种风洞实验高精度阻力测量方法及装置，所述的装置包括花键母、花键轴、风洞天平；花键轴一端与天平支杆连接，另一端与风洞天平锥端连接；风洞天平的平端面与飞行器模型内部垂直飞行器模型中心线的一平面接触并固定，至少两个花键母与飞行器模型内壁固连，用于支撑飞行器模型且能够在花键轴上滑动，保证花键母与花键轴之间只有一个轴向移动自由度。

Coating for bench testing unit for transport aerodynamic measurements

FIELD: test equipment. SUBSTANCE: coating is used in the bench testing unit for transport aerodynamic measurements with at least one band conveyer, which passes at least in the area of the transport front and rear wheels subfloor. Upon that, the coating comprises a set of reference elements that can be covered by the plastic material. EFFECT: strength enhancement, repair simplification and pollution resistance. 6 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 640 116 C2 (51) МПК G01M 9/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01M 9/04 (2006.01) (21)(22) Заявка: 2015154135, 16.12.2015 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): ДР. ИНГ. Х.Ц.Ф. ПОРШЕ АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) Дата регистрации: 26.12.2017 (56) Список документов, цитированных в отчете о поиске: DE 102008036315 A1, 14.01.2010. 17.12.2014 DE 102014118866.7 (43) Дата публикации заявки: 19.06.2017 Бюл. № 17 DE 7224770 U, 26.10.1972. RU 2134761 C1, 20.08.1999. (45) Опубликовано: 26.12.2017 Бюл. № 36 2 6 4 0 1 1 6 R U (54) Покрытие для испытательного стенда для аэродинамических измерений транспортных средств (57) Реферат: Изобретение относится к испытательной в области черного пола у передних и задних колес технике, в частности к испытательным стендам транспортного средства. При этом покрытие для аэродинамических испытаний транспортных содержит множество опорных элементов, средств, а именно к покрытиям стендов. которые могут быть покрыты пластиковым Покрытие используется в испытательном стенде материалом. Технический результат заключается для аэродинамических измерений транспортных в повышении прочности, упрощении ремонта и средств с, по меньшей мере, одним ленточным стойкости к загрязнениям. 5 з.п. ф-лы, 3 ил. транспортером, проходящим, по меньшей мере, Стр.: 1 C 2 C 2 Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, стр. 3, ООО "Юридическая фирма Городисский и Партнеры" 2 6 4 0 1 1 6 Приоритет(ы ...

Testing method for discoloration by diffusion of gas

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

Restraint system for vehicles

본 발명에 따른 테스트 시스템(10)은 플랫폼(16) 및 가동 무단 벨트(22)를 갖춘 풍동을 포함한다. 구속부(9)는 테스트 물품, 예컨대 차량(13)을 가동 무단 벨트(22)에 대해 선택되는 수직방향 위치에 구속하도록 구성된다. 구속부(9)는 적어도 한 쌍의 축방향 강성 지지부(30)를 포함하며, 적어도 하나의 상기 강성 지지부는 가동 무단 벨트(22)의 각 측부 상에 마련되고, 그 단부는 테스트 물품(13)에 고정되도록 구성되며, 각각의 지지부(30)는 벨트(22)에 대해 플랫폼(16)의 고정부로부터 가동 무단 벨트(22)의 적어도 일부 위로 연장된다. The test system 10 according to the present invention comprises a wind tunnel with a platform 16 and a movable endless belt 22. The restraining portion 9 is configured to restrain the test article, e.g., the vehicle 13, in a vertical position selected with respect to the movable endless belt 22. [ The restricting portion 9 includes at least one pair of axially rigid supports 30 and at least one of the rigid supports is provided on each side of the movable endless belt 22, And each support portion 30 extends over at least a portion of the movable endless belt 22 from the fixed portion of the platform 16 relative to the belt 22. [

HYDROGEN GAS DIFFUSIBILITY and FLAMMABILITY TEST APPARATUS

본 발명은 수소 확산성 및 연소성 실험장치에 관한 것으로서, 수소를 연료로 사용하는 연료전지 자동차 및 수소 내연기관 자동차의 안전성을 평가하기 위해 누출된 수소의 확산성 및 연소성 등을 파악할 수 있는 수소 확산성 및 연소성 실험장치를 제공하는 것이다. 이와 같은 목적을 실시하기 위한 본 발명에 따른 수소 확산성 및 연소성 실험장치는 수소가스의 확산 및 연소성을 측정하기 위한 수소 확산성 및 연소성 실험장치로서, 주변이 밀폐된 계를 형성하는 챔버와, 상기 챔버에 연결되어 수소가스를 공급하는 공급부와, 상기 챔버에 설치되며 공급된 상기 수소가스를 점화시키는 점화플러그와, 상기 챔버 내의 온도 및 압력을 측정하는 온도센서 및 압력센서와, 상기 공급부 또는 상기 점화플러그의 점화를 제어하는 제어부를 포함한다. The present invention relates to an apparatus for experimenting hydrogen diffusivity and combustibility, the hydrogen diffusivity capable of grasping the diffusivity and combustibility of leaked hydrogen to evaluate the safety of fuel cell vehicles and hydrogen internal combustion engine vehicles using hydrogen as fuel. And it provides a combustion experiment apparatus. The hydrogen diffusivity and combustibility experiment apparatus according to the present invention for achieving the above object is a hydrogen diffusivity and combustibility experiment apparatus for measuring the diffusion and combustibility of hydrogen gas, the chamber forming a closed system surrounding the above, and A supply unit connected to the chamber for supplying hydrogen gas, an ignition plug installed in the chamber to ignite the supplied hydrogen gas, a temperature sensor and a pressure sensor for measuring temperature and pressure in the chamber, the supply unit or the ignition And a control unit for controlling the ignition of the plug. 수소, 자동차, 주차장, 밀폐, 챔버, 확산, 연소, 폭발 Hydrogen, car, parking lot, sealed, chamber, diffusion, combustion, explosion

Method of determining ballistic coefficient of object

FIELD: ballistics. SUBSTANCE: method of determining ballistic coefficient of an object based on results of trajectory measurements of parameters of its movement at the atmospheric section of passive flight. It is used for determining values of ballistic coefficients of objects of different aerodynamic shapes, that can be claimed in space engineering and other industries studying motion of objects in gaseous media. EFFECT: higher accuracy of determining ballistic coefficient of an object based on results of trajectory measurements at the atmospheric section of its passive flight. 1 cl РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК G01M 9/08 (13) 2 600 515 C1 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2015126150/28, 30.06.2015 (24) Дата начала отсчета срока действия патента: 30.06.2015 (45) Опубликовано: 20.10.2016 Бюл. № 29 C 1 2 6 0 0 5 1 5 R U (54) СПОСОБ ОПРЕДЕЛЕНИЯ БАЛЛИСТИЧЕСКОГО КОЭФФИЦИЕНТА ОБЪЕКТА (57) Реферат: Способ определения баллистического областях техники, занимающихся изучением коэффициента объекта по результатам движения объектов в газообразных средах. внешнетраекторных измерений параметров его Технический результат - повышение точности движения на атмосферном участке пассивного определения баллистического коэффициента полета. Используется для определения значений объекта по результатам внешнетраекторных баллистических коэффициентов объектов измерений на атмосферном участке его различной аэродинамической формы, что может пассивного полета. быть востребовано в ракетостроении и других Стр.: 1 C 1 Адрес для переписки: 141091, Московская обл., г. Королёв, мкр. Юбилейный, ул. М.К. Тихонравова, 29, ФГБУ "4 ЦНИИ" Министерства обороны Российской Федерации 2 6 0 0 5 1 5 (56) Список документов, цитированных в отчете о поиске: 2008132202 04.08.2008. ТЕОРЕТИЧЕСКИЕ ОСНОВЫ БАЛЛИСТИКО-НАВИГАЦИОННОГО ОБЕСПЕЧЕНИЯ КОСМИЧЕСКИХ ПОЛЕТОВ / Л. Н. ЛЫСЕНКО, В. В. БЕТАНОВ, Ф. В. ЗВЯГИН; —? М.: ИЗД-ВО МГТУ ИМ ...

Flow field data measuring method and measurement control system

本发明公开了一种流场数据测量方法和测量控制系统。流场数据测量装置包括控制与驱动系统和流场测试系统；所述控制与驱动系统用于按照测试时序，将测试信号发送给流场测试系统，以启动或者停止不同的测试任务，并收集测试数据；所述流场测试系统，用于根据控制与驱动系统发送的测试信号，执行不同的测试任务。根据本发明的流场数据测量装置、测量方法和测量控制系统，通过简易的控制逻辑在风洞试验中联合使用多种测试技术实现对多个流场物理量的同步、异步测量，并且实现测试站位准确便捷更换，利于物理量之间的时空相关分析。

Vertical torsion two-degree-of-freedom segment model wind tunnel test system

本发明涉及一种竖直扭转两自由度的节段模型风洞试验系统，包括结构相同且对称设置于两端的两组悬挂支撑装置，每组悬挂支撑装置分别包括刚性支撑、风攻角调节板、支撑框架、竖直颤振测量组件和扭转颤振测量组件，刚性支撑立于地面，风攻角调节板安装于刚性支撑上，支撑框架通过竖直颤振测量组件安装于风攻角调节板上，能够沿竖直方向运动，扭转颤振测量组件安装于支撑框架上，且与节段试验模型连接，能够与节段试验模型共同做扭转运动，竖直颤振测量组件通过竖向弹簧提供节段试验模型竖直方向的刚度，扭转颤振测量组件通过横向弹簧提供节段试验模型扭转方向的刚度，与现有技术相比，本发明具有测量精度高、稳定可靠等优点。

Six-component high-precision micro rolling torque measuring device and measuring method

本发明公开了一种六分量高精度微量滚转力矩测量装置，涉及航空航天风洞测力试验技术领域，能同时测量作用在试验模型上载荷极其悬殊的六个气动力分量，具体方案为：包括主天平元件、轴承、模型连接套、天平支杆、进气管和排气管；主天平元件包括分别位于两端的支杆端和主天平元件模型端，支杆端与天平支杆连接，主天平元件模型端与轴承的定子连接，轴承的转子与模型连接套连接；主天平元件外围环设有滚转‑阻力元件，滚转‑阻力元件包括固定端和滚转‑阻力元件模型端，固定端与主天平元件模型端连接；本发明提供的六分量高精度微量滚转力矩测量装置能避免相同试验状态的重复试验，提高了试验数据精度，同时减少了试验车次，降低了试验成本。

A kind of embedded horizontal tail aerodynamics force measurement device

本发明公开了一种内嵌式平尾气动力测量装置,包括固定端和平尾安装端，所述固定端包括连接杆和固定平板，连接杆与固定平板之间设置有剪切凹槽，所述固定端和平尾安装端为一个整体钢结构，固定平板与平尾安装端之间通过加工形成弹形梁，所述弹形梁上和剪切凹槽内设置有若干应变片。本发明电桥测量全部采用剪切应变敏感型电阻应变片，减小了气动力作用下测量装置的变形幅度，保证了测量装置与模型的连接间隙；采用剪切凹槽测量滚转力矩，克服了片式测量装置滚转力矩分量灵敏度输出不足，提高了该分量测量的准确度。同时，该测量装置可根据需要，快速、方便、准确更换调整平尾安装角度。

The method indirectly measuring electromotor effective push

本发明提供一种间接测量发动机有效推力的方法，用于测量吸气式一体化飞行器的发动机的有效推力，所述的飞行器为通流模型，带动力飞行器在风洞中开展推阻特性测量试验，风洞试验同时满足气动和发动机试验的模拟准则要求，试验中发动机点火燃烧，风洞天平测得飞行器总推力F 天平总推力 ，并与计算或者测量得到的机体阻力D 外阻 相加，得到发动机有效推力；本发明的方法避免计算冷态内阻，而是通过热态试验测得的总推力加上流道之外的机体阻力得到发动机有效推力，提高了吸气式一体化飞行器的发动机有效推力测量的准确性。

Electromagnetic weighing element

Large-scale low-speed wind tunnel pulsating pressure test data processing method and equipment

本发明公开一种大型低速风洞脉动压力试验数据处理方法及设备，属于风动试验领域。方法如下：在风洞试验现场采集试验前风洞静压、试验中风洞静压、试验前脉动压力和试验中脉动压力；将试验中脉动压力减去试验前脉动压力加上试验前风洞静压减去试验中风洞静压得到试验中真实压力；对试验中真实压力求平均得到当地静压；将试验中真实压力减去当地静压得到当地脉动压力；将当地脉动压力均方根除以试验中风洞速压得到脉动压力系数均方根；对当地脉动压力进行傅里叶变换计算脉动压力功率谱密度，为风洞试验数据分析提供依据。本发明提高了试验效率，对风洞静压、速压等数据实时采集，计算的当地脉动压力准确度高。

A kind of three hole dynamic pressure probes for measuring subsonics Two Dimensional Unsteady flow field

本发明属于叶轮机械测试技术领域，公开了一种测量亚音二维非定常流场的三孔动态压力探针，包括探针支杆1、探针头部2、过渡段3和压力传感器线缆4，所述的探针支杆1和探针头部2均为圆柱形，探针头部2通过过渡段3安装在探针支杆1上，探针头部2的圆柱面开设有三个压力感受孔，三个压力感受孔分别与探针头部2内部封装的三个压力传感器相连，压力传感器线缆通过探针支杆1内通道引出探针尾部。与现有的探针测试技术相比，本发明经过校准标定，可进行二维亚音速流场总压、马赫数和流动方向的测量，可以用于叶轮机械试验测试。

Coupling elastic modal unsteady aerodynamic force measuring device and method

本发明提供了一种耦合弹性模态非定常气动力测量装置及方法，包括包括天平、位移元件、应变测量单元和加速度测量单元组成，位移元件采用弹性梁设计方法，用来记录模型振动时的位置信息，位移元件为空心圆柱形，一端为圆环状的天平连接圈，用以与天平的等直段固连，另一端为切线挖槽的卸载固定端，中间段为弹性梁，由沿圆周均匀分布的弹性梁片组成，应变测量单元粘贴在弹性梁上，加速度测量单元安装在试验件上，对试验件进行风洞试验，获得天平施加给试验件的受力、位移和加速度信息；建立试验件的动力学模型，获得非定常气动力的计算公式,并计算试验件的气动力。本发明的装置和方法可以精确的测量试验件受到的非定常气动力。

Method for thermal loading of rocket fairings

FIELD: test technology. SUBSTANCE: invention relates to methods of thermal testing of aircraft elements, in particular ceramic fairings of rockets. Proposed method of thermal loading of rocket fairings from nonmetallic materials includes zone radiant heating of the fairing and temperature measurement. Heating of the fairing local area is performed through a metal screen installed near its surface, at that temperature of the surface of the fairing local area is corrected by application of the coating with the required degree of blackness on the internal and external surfaces of the metal screen. Introduction of proposed method allows to expand technical capabilities of test equipment for ground development of new structures of rocket equipment due to higher accuracy of setting thermal conditions. EFFECT: high accuracy of setting temperature field in local areas of tested articles. 1 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 696 939 C1 (51) МПК G01N 25/72 (2006.01) G01M 9/00 (2006.01) G01M 9/06 (2006.01) G01J 5/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01N 25/72 (2019.05); G01M 9/00 (2019.05); G01M 9/06 (2019.05); G01J 5/00 (2019.05) (21)(22) Заявка: 2018133372, 20.09.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: 07.08.2019 (45) Опубликовано: 07.08.2019 Бюл. № 22 2 6 9 6 9 3 9 R U (54) Способ теплового нагружения обтекателей ракет (57) Реферат: Изобретение относится к способам тепловых испытаний элементов летательных аппаратов (ЛА), в частности керамических обтекателей ракет. Заявленный способ теплового нагружения обтекателей ракет из неметаллических материалов включает зонный радиационный нагрев обтекателя и измерение температуры. Нагрев локальной зоны обтекателя осуществляют через металлический экран, установленный вблизи его поверхности, при этом температуру поверхности локальной зоны обтекателя корректируют Стр.: 1 (56) Список документов, цитированных в отчете ...

Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance

本发明涉及一种同轴并联式轴向载荷测量的高精度风洞测力天平，属于风洞天平设计领域；包括前锥、径向四分量载荷测量元件、轴向载荷测量元件、等直段和后锥；径向四分量载荷测量元件包括两组结构相同的三柱梁，两组三柱梁分别设置在所述轴向载荷测量元件的轴向两端，组成六分量测量元件；前锥、六分量测量元件、等直段和后锥同轴依次连接，组成测力天平；轴向载荷测量元件包括外壳、阻力支撑片梁组、阻力测量梁、滚转力矩测量梁、中间壳体、支撑内轴和滚转力矩支撑片梁组；本发明确保了天平整体刚度较大的情况下，实现轴向载荷测量解耦、避免其他分量对轴向分量的测量干扰，提高测量精度。

Bicycle wind tunnel experiment table device

本发明公开了一种自行车风洞实验台装置，双层实验台装置分为上下两层，下层结构装有控制电机，而控制电机通过连接装置将其旋转运动转换为摆动架的上下运动，并通过上层结构的运动传递作用实现最上层台面上下摆动。自行车固定装置在固定架和车轮之间安装有轴承，风速测量装置在水平方向导轨和垂直方向导轨内置丝杠、外置旋钮。本发明不仅可实现自行车上下坡或各侧面承受风力的模拟，而且还能保持自行车车轮的旋转运动，以达到更好模拟自行车在行进过程的真实状态。此外，该装置可用于各种类型的自行车风洞实验研究，也可用于自行车某一部分与空气阻力的关系研究。

Three-hole pressure probe comb

本发明属于压力测试技术领域，公开了一种三孔压力探针梳，包含探头、支杆、引压管，探头数量根据测量要求确定，至少3个，几何形状相同，呈扁平、梯形体，分别固定在支杆不同展向测量位置，每个探头的迎风面开有3个压力感受孔，3个感受孔分别与封装在探头内的3根引压管连通，支杆内部开有通道，引压管的另一端经支杆内的通道，由探针尾部引出。本发明经过校准风洞标定，能同时测得多个空间位置来流的总压、静压、偏转角和马赫数，适用于测量叶轮机械叶片排进口、出口、级间二维流场来流参数沿叶片高度方向的分布。与现有的测量二维流场的三孔压力探针相比，能同时测得多个空间位置来流参数，最大程度地缩短测量时间，降低试验成本。