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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

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Мониторинг СМИ

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

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Применить Всего найдено 3. Отображено 3.
10-02-2022 дата публикации

Hybrid Rocket Motor

Номер: US20220042479A1
Автор: Heiner Mark C., Whitmore Stephen A.
Принадлежит:

A rocket motor is disclosed that can include a combustion chamber containing a solid fuel that is operable to burn during operation of the rocket motor to generate combustion gas and unburned gaseous fuel. The rocket motor can also include a propellant supply containing an energy-rich oxidizer with a decomposition energy greater than or equal to 1.0 MJ/kg. In addition, the rocket motor can include a thrust augmented nozzle (TAN) operably coupled to the combustion chamber to receive the combustion gas from the combustion chamber and direct a flow of the combustion gas through the TAN. The TAN can have a divergent portion downstream of a throat, and a propellant injection port associated with the divergent portion and in communication with the propellant supply to inject the energy-rich oxidizer into the divergent portion. Only the energy-rich oxidizer, independent of another propellant, may be introduced into the flow of the combustion gas and the unburned gaseous fuel for secondary combustion of the unburned gaseous fuel and thermal decomposition of the energy-rich oxidizer within the divergent portion. 1. A rocket motor , comprising:a combustion chamber containing a solid fuel that is operable to burn during operation of the rocket motor to generate combustion gas and unburned gaseous fuel;a propellant supply containing an energy-rich oxidizer with a decomposition energy greater than or equal to 1 MJ/kg; anda thrust augmented nozzle (TAN) operably coupled to the combustion chamber to receive the combustion gas from the combustion chamber and direct a flow of the combustion gas through the TAN, the TAN having a divergent portion downstream of a throat, and a propellant injection port associated with the divergent portion and in communication with the propellant supply to inject the energy-rich oxidizer into the divergent portion,wherein only the energy-rich oxidizer, independent of another propellant, is introduced into the flow of the combustion gas and the ...

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Номер записи: 1
07-07-2016 дата публикации

SOLID GRAIN STRUCTURES, SYSTEMS, AND METHODS OF FORMING THE SAME

Номер: US20160194256A1
Автор: Mathias Spencer, Merkley Daniel P., Sobbi Mansour, Walker Sean D., Whitmore Stephen A.
Принадлежит: Utah State University

Devices, methods, and systems for providing a solid grain fuel for a hybrid rocket. In one embodiment, the solid grain fuel includes a housing having a length extending between a first side and a second side. The housing defines a central axis and a bore extending from the first side to the second side. The bore of the housing extends with a helical configuration along the length of the housing. Further, the housing includes multiple segments configured to interlock together to form the bore along the length of the housing. 1. A solid grain fuel for a hybrid rocket , comprising:a housing having a length extending between a first side and a second side, the housing defining a central axis and a bore extending from the first side to the second side, the bore extending with a helical configuration along the length of the housing, the housing including multiple segments configured to interlock together to form the bore along the length of the housing.2. The solid grain fuel of claim 1 , wherein:each of the multiple segments comprises multiple flat layers and each flat layer defines a plane that is transverse relative to the central axis of the housing, andthe bore extends through each of the multiple flat layers3. The solid grain fuel of claim 1 , wherein the housing is formed of acrylonitrile butadiene styrene (ABS).4. The solid grain fuel of claim 1 , wherein the bore comprises a circular cross-section.5. The solid grain fuel of claim 1 , wherein the multiple segments include opposite ends claim 1 , at least one of the opposite ends including an orientation feature configured to couple to an end of another one of the multiple segments so that the bore in each of the multiple segments collectively defines the helical configuration within the coupled multiple segments.6. A solid grain fuel for a hybrid rocket claim 1 , comprising:a housing having a length extending between a first side and a second side, the housing defining a central axis and a bore extending from the ...

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Номер записи: 2
12-11-2015 дата публикации

Restartable Ignition Devices, Systems, and Methods Thereof

Номер: US20150322892A1
Автор: Inkley Nathan, Merkley Daniel P., Whitmore Stephen A.
Принадлежит: Utah State University

Devices, methods, and systems for providing a restartable ignition system for a hybrid rocket system. In one embodiment, an ignition device includes a housing and at least two electrodes. The housing includes a first side and a second side and defines a bore with an axis extending therethrough between the first and second sides, the bore defining an internal surface of the housing. The at least two electrodes extend through the housing to the internal surface. The at least two electrodes are configured to be spaced apart so as to provide an electrical potential field along the internal surface between the at least two electrodes. Such housing is formed with and includes multiple flat layers such that the multiple flat layers provide ridges along the internal surface. With this arrangement, the internal surface with the ridges are configured to concentrate an electrical charge upon being subjected to the electrical potential field. 1. An ignition device , comprising:a housing having a first side and a second side, the housing defining a bore with an axis extending therethrough between the first and second sides, the bore defined by an internal surface of the housing; andat least two electrodes extending through the housing to the internal surface, the at least two electrodes configured to be spaced apart so as to provide an electrical potential field along the internal surface between the at least two electrodes;the housing having multiple flat layers, the multiple flat layers providing ridges along the internal surface configured to concentrate an electrical charge upon being subjected to the electrical potential field.2. The ignition device of claim 1 , wherein the ridges are configured to act as miniature electrodes when exposed to the electrical potential field.3. The ignition device of claim 1 , wherein the internal surface comprises grooves claim 1 , each groove extending between two adjacently extending ridges.4. The ignition device of claim 1 , wherein each ...

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Номер записи: 3