Carrier rocket sub-stage falling area range control system

A carrier rocket and control system technology, applied to projectiles, self-propelled bombs, offensive equipment, etc., can solve the problem of lack of carrier rocket sub-stage landing zone control capabilities, achieve reasonable and reliable flight timing design, small weight increase, The effect of reducing the loss of carrying capacity

Active Publication Date: 2019-08-23
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

my country currently does not have the ability to con

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  • Carrier rocket sub-stage falling area range control system
  • Carrier rocket sub-stage falling area range control system
  • Carrier rocket sub-stage falling area range control system

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Embodiment Construction

[0064] In order to describe the present invention in detail more clearly, the present invention will be further described below in conjunction with the accompanying drawings.

[0065] figure 1 and figure 2 The main structure and grid rudder structure system of the sub-stage body of the launch vehicle are shown. Such as figure 1 As shown in (a), the first-stage interstage section 101 is located at the top of the sub-stage rocket body, the box-interval section 102 is located in the middle of the sub-stage rocket body, and the engine 103 is located at the tail of the sub-stage rocket body. The control unit 300 in the grid rudder control system, the timing controller 301, the battery 302 and the telemetry unit 400 in the grid rudder telemetry system are installed in the sub-level box section 102, such as figure 1 (c) shown. A grid rudder structure system and a servo mechanism 303 are installed on the interstage section 101, figure 1 (b) The middle grid rudder surface is in t...

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Abstract

The invention discloses a carrier rocket sub-stage falling area range control system. The carrier rocket sub-stage falling area range control system comprises a grid fin structure system, a grid fin control system, a grid fin telemetering system and a ground information receiving system. Under the condition that a control unit resolves the measurement information such as the posture, the positionand the speed, a servo mechanism is controlled to deflect the fin surface by sending an instruction, so that the posture of a sub-stage of a carrier rocket is stabilized, and the sub-stage is guided to fly to the target falling area for flying landing; and the telemetering system and the ground information receiving system are used for measuring and receiving the sub-stage reentry flight information, and the sub-stage state information is monitored in real time. According to the system, the flight control time sequence and procedures are integrated, so that the sysrem has the advantages that the modification amount of the carrier rocket is small, the loss of the carrying capacity is small, the flight safety of a main task of the carrier rocket is not affected, the sub-stage falling area range of the carrier rocket can be greatly reduced, and the sub-stage return information can be monitored in real time.

Description

technical field [0001] The invention relates to a control system for the range of the sub-stage landing area of ​​a launch vehicle. Background technique [0002] The sub-stage landing area of ​​my country's launch vehicle is generally 30 kilometers wide and 50-70 kilometers long. At present, more than 20-30 high-density space launch missions are carried out every year, and tens of thousands of people need to be evacuated each time, and the sub-stage wreckage smashes houses High-voltage lines, farmland, highways and other civil facilities pollute water sources, causing serious harm to the lives and property of people in the landing area. Frequent and large-scale evacuations have seriously disrupted the normal life and production order of the people in the landing area and seriously affected China's aerospace industry. positive image. [0003] With the development of the drop zone economy, the population density continues to increase, and the uncertainty of the distribution of ...

Claims

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Application Information

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IPC IPC(8): F42B10/14F42B10/48F42B10/62F42B15/00F42B15/01
CPCF42B10/143F42B10/48F42B10/62F42B15/00F42B15/01
Inventor 陈雪巍金益辉修观夏俊力李瑞鸿郝钏钏朱亮聪古艳峰梁艳迁李鑫徐腾王吉飞
Owner SHANGHAI AEROSPACE SYST ENG INST
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