launch vehicle
A technology for launching rockets and payloads, which is applied in the direction of rocket engine devices, offensive equipment, projectiles, etc., can solve the problems of insufficient control ability of the attitude control system, and achieve the effect of solving the insufficient control ability and increasing the distance
Active Publication Date: 2022-08-09
CHINA ACAD OF LAUNCH VEHICLE TECH
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Problems solved by technology
[0005] The embodiment of this application provides a launch vehicle, which is mainly used to solve the problem of insufficient control capability of the attitude control system in the related art
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[0038] In order to make the technical solutions and advantages of the embodiments of the present application more clear, the exemplary embodiments of the present application will be described in further detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, and Not all embodiments are exhaustive. It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict.
[0039] image 3 Shown in is a structural diagram of a launch vehicle provided by an embodiment of the present application; please refer to image 3 .
[0040] This embodiment provides a launch vehicle 200, including a head cover 210, a satellite cabin 220, a final repair cabin 230, and a plurality of lower-stage engine compartments 240 other than the final repair cabin, wherein the final repair cabin 230 is located betw...
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The launch vehicle of the embodiment of the present application includes a head cover, a terminal repair cabin, an attitude control system, a final stage engine, and a satellite cabin; the head cover is used to protect the launch vehicle; the terminal repair cabin is connected to the rear end of the head cover, and the There is an injection outlet on the bulkhead; the attitude control system is arranged in the final repair cabin, and the attitude control system includes an attitude control engine; wherein, the nozzle of the attitude control engine is installed at the injection outlet, and the nozzle of the attitude control engine is sprayed out. The heat flow is ejected from the jet outlet to adjust the attitude of the launch vehicle; the final stage engine provides power for the rocket's final stage flight; the satellite capsule is connected to the tail end of the final stage engine. In the embodiment of the present application, the final repair cabin with the attitude control system is arranged between the hood and the satellite cabin, and the attitude control system is located at the head of the entire launch vehicle, thereby increasing the distance between the attitude control system and the center of mass of the rocket in each flight state , the attitude control system can provide a longer control arm for each engine compartment, thus solving the problem of insufficient control ability of the attitude control system in the related art.
Description
technical field [0001] The present application relates to the technical field of launch vehicles, and in particular, to a launch vehicle. Background technique [0002] A launch vehicle is a vehicle that pushes various human-made spacecraft (such as artificial earth satellites, manned spacecraft, space stations or interplanetary probes) to predetermined orbits in space. [0003] figure 1 Shown in is the structural diagram of the launch vehicle in the related art; figure 2 Shown in the related art is the structure diagram of the final stage nacelle and satellite; please refer to Figure 1-Figure 2 . In the solution of the related art, the launch vehicle 100 can generally be divided into multiple stages, including a fairing 110 at the front end and a multi-stage nacelle connected to the fairing 110 . The satellite 111 is disposed in the fairing 110 , and the engine compartment near the fairing 110 is the final engine compartment 120 . A final stage engine 121 and an attit...
Claims
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IPC IPC(8): F42B15/00F42B15/01F42B10/66F02K9/97
CPCF42B15/00F42B15/01F42B10/663F02K9/97
Inventor 张意国龚旻高峰罗波赵长见马奥家蔡强黄建友曾伟曾鲁张帆谭杰李炳蔚宋志国韩敬永刘博周国哲冯铁山潘建业于贺张子骏佟泽友葛悦张东任新宇年永尚张晓赛齐麟杨瑜
Owner CHINA ACAD OF LAUNCH VEHICLE TECH