High total impulse solid cool gas micro propulsion unit

A technology of micro-propulsion and cold air thrust, which is applied in jet propulsion devices, propulsion system devices of space navigation vehicles, rocket engine devices, etc., can solve the problems of difficult control of gas cleanliness, low efficiency and ignition reliability, and generation of residues, etc. Achieve the effect of multi-degree-of-freedom control, plug-and-play, and improved air tightness

Active Publication Date: 2016-12-21
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

However, the total gas production provided by the module is limited due to the use of granular charges
Ignition adopts the method of direct heating by hot wire, which has low efficiency and ignition reliability. Nanjing University of Science and Tec...

Method used

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  • High total impulse solid cool gas micro propulsion unit
  • High total impulse solid cool gas micro propulsion unit
  • High total impulse solid cool gas micro propulsion unit

Examples

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Embodiment Construction

[0025] Such as Figure 1 to Figure 6 As shown, a high total charge solid cold air micro propulsion device includes an air chamber 1, an air chamber end cover 2, a control drive module 3, a cabin penetration terminal board 4, a temperature sensor 5, a pressure sensor 6, a cold air generator 7, and a Exhaust plug 8, multiple miniature cold air thrusters 10, thruster mounting base 11, installation support plate 12; plug and play can be realized. When attitude control is required, the cold air generator 7 is driven by the control drive module 3 to ignite, and the required nitrogen gas is injected into the air chamber 1 of the module. The driving module 3 drives the working pulse width of the miniature electromagnetic valve of the miniature air-conditioning thruster 10 assembly to realize the output of force and torque. At the same time, the pressure sensor 6 and the temperature sensor 5 collect the pressure and temperature parameters in the air chamber 1 in real time. , to determ...

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Abstract

A high total impulse solid cool gas micro propulsion unit includes a gas chamber (1); the gas chamber (1) is a cylindrical housing with an opening at one end of the cylindrical housing; nozzles of all the micro cool gas propulsion devices (10) are arranged on the center of an end surface of the gas chamber (1) and side walls of the gas chamber (1) respectively; a gas chamber end cover (2) seals the opening end of the gas chamber (1); a temperature sensor (5), a pressure sensor (6) and a cool gas generator (7) are fixed in the gas chamber (1); the pressure sensor (6) and the temperature sensor (5) can acquire pressure parameters and temperature parameters in real time and send the parameter values to a control drive module (3); the control drive module (3) drives the cool gas generator (7) to generate gas to be injected into the gas chamber (1) according to the received pressure parameter values and the received temperature parameter values; and the control drive module (3) drives and controls the work pulse width of the micro cool gas propulsion devices (10). The high total impulse solid cool gas micro propulsion unit can improve the total impulse of the propulsion module, can improve the whole sealing performance, and can achieve multi-degree of freedom control.

Description

technical field [0001] The invention relates to a propulsion device. Background technique [0002] Due to its low cost, light weight, and flexible launch form, micro-nano satellites have begun to attract the attention of the international aerospace community and have developed rapidly. According to the assessment of SpaceWorks Consulting Company, it is estimated that the annual market demand for micro-nano satellites below 50kg will exceed 400 pieces. Construct a distributed space system through formation networking, etc., which can be used for mainstream aerospace services such as space environment detection, tactical reconnaissance, and communication enhancement. High-quality micro-nano satellites also have high application value. Due to the requirements of future space missions for orbit control, as well as the requirements of modular design and rapid assembly, it is necessary to develop modular and prepackaged micro-propulsion technology. [0003] Due to its safety, l...

Claims

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Application Information

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IPC IPC(8): F02K9/42B64G1/40
CPCB64G1/40F02K9/42
Inventor 刘旭辉陈君龙军高晨光周怡秋沈岩宋新河官长斌张志伟席红敏李永平张良李恒建王焕春周磊王永钢王文平王健李长维
Owner BEIJING INST OF CONTROL ENG
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