A measurement and control system and method suitable for high dynamic uncontrolled return of aircraft separation body

A technology of measurement and control system and aircraft, applied in the direction of weapon types, offensive equipment, projectiles, etc., can solve problems such as environmental pollution, personnel injury, and large spread of booster landing points, so as to reduce the range of landing areas and improve safety Effect

Active Publication Date: 2021-10-01
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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AI Technical Summary

Problems solved by technology

At present, the booster generally adopts an uncontrolled reentry return method. Due to the influence of various random disturbances, the drop points of the booster are widely scattered.
When the landing area is located on land, the large area of ​​the landing area will bring about the evacuation of personnel and property and safety issues. At the same time, the remaining toxic propellant in the booster tank will pollute the environment and cause harm to personnel.

Method used

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  • A measurement and control system and method suitable for high dynamic uncontrolled return of aircraft separation body
  • A measurement and control system and method suitable for high dynamic uncontrolled return of aircraft separation body
  • A measurement and control system and method suitable for high dynamic uncontrolled return of aircraft separation body

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Embodiment Construction

[0060] Such as figure 1 As shown, the specific components of the measurement and control system include power supply module, MEMS inertial measurement module, satellite navigation receiving module, control module, radio frequency transmission module, image measurement module, data storage module, digital input and output module, and switch input and output module. Partial composition. The specific implementation is:

[0061] 1) Complete the parameter collection and information fusion of the MEMS inertial measurement module and the satellite navigation receiving module during the flight;

[0062] 2) Receive status information such as take-off signals and aircraft separation signals, and control the power supply module to supply power to the separation pyrotechnics according to the predetermined time;

[0063] 3) Complete the function of collecting and storing digital image signals;

[0064] 4) Send positioning and attitude information to other subsystems through RS-485 or RS...

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Abstract

The present invention is a measurement and control system and method suitable for high dynamic and uncontrolled return of an aircraft separation body. Quantity input and output module and switching quantity input and output module; the system can calculate the position, speed and attitude information of the separated body in real time during the high dynamic uncontrolled return process of the aircraft, and send the above information to the ground handheld in real time through the wireless link. The terminal provides the information of the falling trajectory and the location of the falling point for the recovery of the separated body.

Description

technical field [0001] The invention belongs to navigation guidance and control, and relates to a measurement and control system and method suitable for high dynamic uncontrolled return of aircraft separation bodies. Background technique [0002] All major aerospace countries and private aerospace companies in the world are actively carrying out the development and flight verification of reusable launch vehicles. With breakthroughs in key technologies such as rocket recovery structure, power, and control, development and flight risks and economic costs have been greatly reduced. The recovery and reuse of launch vehicles can not only greatly reduce launch costs, but also effectively control the flight debris to avoid loss of life and property. The separation body of the traditional launch vehicle falls to the ground uncontrollably after the work is over, and the wreckage weighing several tons falls from the air to the ground, which has great destructive power. It is urgent t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/36F42B15/01
CPCF42B15/01F42B15/36
Inventor 张亦朴任月慧陈彬刘洋高晨
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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