A loadable multi-pulse solid rocket motor
A solid rocket and multi-pulse technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of pulse unit ignition difficulties, unreliable work, increase the size and quality of the combustion chamber structure, and achieve multiple pulses Reliable, reliable ignition, flexible change effect
Inactive Publication Date: 2020-06-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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- Application Information
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Problems solved by technology
The traditional way to increase the number of pulses is to add more pulse units in the combustion chamber, but this will inevitably increase the structural size and quality of the combustion chamber. At the same time, due to the increase in free volume, it will also cause difficulty in ignition of the pulse units and unreliable work.
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[0036] specific implementation plan
[0037] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.
[0038] A loadable multi-pulse solid rocket motor, such as figure 1 As shown, including: drug storage device 1 and improved combustion chamber 2;
[0039] The improved combustor 2 is that the combustor front chamber cover 3 in the multi-pulse solid rocket motor has a through hole 4 for filling the charge 5; and five ignition devices 6 are fixedly installed on the outside of the front chamber cover 3; The transmission device 7 of dodge door and shaft is installed at the center position of chamber cover 3; Drug receiving device 8 is placed in the combustion chamber; The cartridges 10 are respectively fixedly connected to the first rotating shaft 9;
[0040] The transmission device 7 of the dodge door and the shaft is as Image 6 As shown, it includes: a shaft 11, a shaft sleeve 12, a bolt 13, a connecting rod 14, a...
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The invention relates to a loading type multi-pulse solid rocket engine, and belongs to the field of solid rocket propulsion. According to the loading type multi-pulse solid rocket engine, propellant storage and a combustion chamber are separated from each other, propellants are automatically loaded when needed, a plurality of times of pulses are realized, the ignition is reliable, and the number of loaded propellants and pushing force can be adjusted. No less than 5 pulses can be realized. Advantages like energy management of a pulse engine, the expansion of the firing range, maneuvering reinforcement of the tail end of an aircraft and the like are more obvious. The size of the combustion chamber is not increased by a device, and ignition is more reliable. In addition, the pushing force can be flexibly adjusted by controlling the number of the loaded propellants.
Description
technical field [0001] The invention relates to a loadable multi-pulse solid rocket motor, which belongs to the field of solid rocket propulsion. Background technique [0002] Solid rocket motors are simple in structure, easy to use, good in safety, and high in reliability. They have played an important role in strategic and tactical missiles and in the aerospace field. However, compared with liquid rocket motors, solid rocket motors lack flexibility in controllability, which affects its use and development. For this reason, the United States, Japan and other countries have carried out comprehensive and systematic research and development on multi-pulse solid rocket engines that can start multiple times and provide intermittent thrust since the 1970s. [0003] The aircraft with multi-pulse solid rocket motor as the power system can flexibly distribute the energy of the solid rocket motor to make the aircraft fly a longer distance; at the same time, for various ranges from n...
Claims
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IPC IPC(8): F02K9/34F02K9/32F02K9/24
CPCF02K9/24F02K9/32F02K9/34
Inventor 夏定国魏志军章玮奇张璐佳孙烨真
Owner BEIJING INSTITUTE OF TECHNOLOGYGY