Настройки

Укажите год
-

Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

Подробнее
-

Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 6. Отображено 6.
07-10-2009 дата публикации

Satellite orbit motion ground simulation system and method

Номер: CN0101551301A
Автор: ZHANG SHIJIE, CAO XIBIN, CHEN YINXIN, SUN ZHAOWEI, SHIJIE ZHANG, XIBIN CAO, YINXIN CHEN, ZHAOWEI SUN
Принадлежит:

The invention relates to a satellite orbit motion ground simulation system based on air-flotation theory, comprising an air-flotation stage, an air foot on the air-flotation stage, a high-pressure air source connected with the air foot and a center gravitation simulator, wherein the center gravitation simulator comprises a first center axle, vertically mounted in the middle of the air-flotation stage; a first magnet, horizontally mounted on the first center axle; a second center axle, vertically mounted on the air foot; a second magnet, horizontally mounted on the second center axle wherein the magnetometric resultant force line of the first magnet and the second magnet passes through the connection line of the first, second center axle. The method using the said system comprises the following steps: cutting over the high-pressure air source; making a satellite simulator float by a layer of air membrane generated between the air foot and air-flotation stage; providing a movement velocity ...

Подробнее
Номер записи: 1
13-04-2021 дата публикации

Small satellite thruster support

Номер: CN212951194U
Автор: SHAN TILEI, ZHANG XIAOJUN, WANG RUIXIAN, LI TENGFEI, CHEN YINXIN, MA LINGXI, LIU JIANG, 单悌磊, 张晓俊, 王瑞显, 李腾飞, 陈寅昕, 马灵犀, 刘江
Принадлежит: AEROSPACE DONGFANGHONG SATELLITE CO LTD, AEROSPACE DONGFANGHONG SATELLITE CO., LTD., 航天东方红卫星有限公司

The utility model relates to a small satellite thruster support which is mainly composed of six characteristic bodies, the first characteristic body, the second characteristic body, the third characteristic body and the fourth characteristic body jointly provide a support and a satellite structure installation face, and the sixth characteristic body structure provides a thruster installation face. And the first feature body, the second feature body, the third feature body, the fourth feature body and the sixth feature body are connected into a whole through the fifth feature body. The small satellite thruster support is simple in structure, large in rigidity, light in weight and large in pipeline connection operation space, has good adaptability to the situation that the thickness of a satellite side plate is large, and can guarantee installation reliability and structural stability of a 10mN thruster.

Подробнее
Номер записи: 2
26-08-2015 дата публикации

Integrally-designed satellite-rocket separation mechanism

Номер: CN104859870A
Автор: CHEN YINXIN, XIN QIANG, XU YUNFEI, GAO YONGXIN
Принадлежит:

The invention provides an integrally-designed satellite-rocket separation mechanism. The integrally-designed satellite-rocket separation mechanism comprises a satellite end separation base, a carrier end separation base, a release spring and a pyrotechnic separation nut, wherein the satellite end separation base is connected with a satellite bottom plate; the carrier end separation base is connected with a carrier; the release spring is accommodated in inner space of the carrier end separation base to provide elasticity between the satellite end separation base and the carrier end separation base; a connection screw rod of the pyrotechnic separation nut penetrates through insides of the carrier end separation base and the release spring to be connected with the satellite end separation base, and a nut body of the pyrotechnic separation nut is connected with the carrier end separation base. A satellite-rocket connection mechanism, the satellite-rocket separation mechanism and a satellite-rocket ...

Подробнее
Номер записи: 3
24-09-2014 дата публикации

Recycling and fixing mechanism for pull-off plug outside satellite

Номер: CN104064933A
Автор: CHEN YINXIN, BAO JINZHONG, XU YUNFEI
Принадлежит:

The invention provides a recycling and fixing mechanism for a pull-off plug outside a satellite. The recycling and fixing mechanism comprises a pull-off plug support outside the satellite, an upper support swing arm and a lower support arm, wherein the pull-off plug outside the satellite is fixedly connected onto the pull-off plug support outside the satellite; the pull-off plug support outside the satellite is connected onto the first connecting end of the upper support swing arm, and the second connecting end of the upper support swing arm can be rotationally connected to the lower support arm, so that the pull-off plug support outside the satellite with the pull-off plug outside the satellite can be rotated to a position far away from the satellite body under the action of the force when the pull-off plug outside the satellite is separated from a the pull-off plug support inside the satellite electronically; and the lower support arm is fixed to a carrier adaptor. According to the recycling ...

Подробнее
Номер записи: 4
26-08-2015 дата публикации

Integrated mounting bracket for star sensors

Номер: CN104859866A
Автор: XU YUNFEI, DI GUODONG, GE YIMIN, CHEN YINXIN
Принадлежит:

The invention provides an integrated mounting bracket for star sensors. The mounting bracket comprises a mounting bottom plate, an overall support platform, a plurality of support barrels and mounting flanges, wherein the mounting bottom plate is fixedly connected with a satellite platform; the overall support platform is fixedly connected with the mounting bottom plate; the plurality of support barrels are connected with the overall support platform respectively; the mounting flanges are arranged at the top ends of the support tubes and used for mounting the star sensors. According to the integrated mounting bracket for the star sensors, integrated mounting of three star sensors is realized according to a satellite attitude and orbit control subsystem scheme and the mounting requirements of the star sensors, and conditions of non-uniform bracket forms, complicated design and processing procedures and longer period occurring when the star sensors are separately mounted are avoided.

Подробнее
Номер записи: 5
11-06-2014 дата публикации

Increasing efficiency of a radio receiver with an adaptive tuner

Номер: CN103858353A
Автор: XIE WEIMING, FERNANDES BRIAN, CHEN YINXIN, LI MINGDA, YUAN YE, BAKHRI SYAIFUL
Принадлежит:

The application provides a mobile radio receiver for a vehicle. The mobile radio receiver comprises a tuner front-end section, a location data port, a sensor port, a tuner front-end section parameter server port, and a data processing unit. In use, the location data port is provided for receiving tuner location data. The sensor port is provided for receiving at least one sensor signal measurement data. The tuner front-end section parameter server port is provided for sending the tuner location data and the at least one sensor signal measurement data and for receiving a set of tuner front-end section parameter data. The data processing unit is operably connected with the tuner front-end section, with the location data port, with the sensor port, and with the tuner front-end section parameter server port. The mobile radio receiver provides an operational mode, a checking mode, a tuner parameter retrieval mode, and a tuner parameter application mode.

Подробнее
Номер записи: 6