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Ground emitting control device of solid-liquid powered aircraft

A ground control and launch control technology, applied in space navigation ground equipment, transportation and packaging, space navigation equipment, etc., can solve the problem of lack of solid-liquid powered aircraft, and achieve simple and convenient modification, high reliability, and good portability Effect

Active Publication Date: 2012-09-26
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Solid-liquid powered aircraft integrates the characteristics of solid and liquid aircraft, but there are few relevant literatures on the research on the ground launch control device of solid-liquid powered aircraft

Method used

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  • Ground emitting control device of solid-liquid powered aircraft
  • Ground emitting control device of solid-liquid powered aircraft
  • Ground emitting control device of solid-liquid powered aircraft

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Embodiment Construction

[0062] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0063] A ground launch control device for a solid-liquid powered aircraft, such as Figure 1 to Figure 6 As shown, it includes a main control computer 1, a remote control box 2 and a ground control box 3.

[0064] The main control computer 1 and the ground control box 3 are connected with the communication port 43 of the ground control box with a 9-core standard D-type serial port. The communication line itself has the function of converting the 232 communication protocol to the 485 communication protocol. Therefore, it can realize long-distance Communication and control between main control computer 1 and ground control box 3;

[0065] The remote control box 2 includes a remote control box main switch 41, a program enabling switch 33, a mode selection switch 34, an aircraft circuit forced emergency power-off switch 35, a start valve output emergency power-o...

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Abstract

The invention discloses a ground emitting control device of a solid-liquid powered aircraft; the ground emitting control device consists of a front end device and a rear end device. The front end device is a ground control box, wherein the output port of the front end device is connected with the solid-liquid powered aircraft; the rear end device comprises a host computer and a remote control box, and the remote control on the solid-powered liquid-powered aircraft is realized. The ground emitting control device of the solid-liquid powered aircraft mainly finishes two functions; the first function is the igniting emitting function which relates to pressure increase of storage boxes, ignition of igniter and opening of liquid-path electromagnetic valve, and the other function is emitting safety ensuring function which relates to high-pressure gas release of high-pressure bottles, pressure release of storage boxes and oxidant discharge of storage boxes. The ground emitting control device solves problems of complicated system, poor portability and high cost of traditional ground emitting control devices, the precise control of igniting emitting timing sequence aiming at the characteristics of solid-powered liquid-powered aircraft is realized, and the programming can be carried out in an on-line manner so as to modify igniting emitting timing sequence simply and conveniently.

Description

technical field [0001] The invention belongs to the technical field of ground measurement and launch control, and in particular relates to a ground launch control device for a solid-liquid powered aircraft. Background technique [0002] Aircraft ground ignition has the characteristics of high cost and high risk, which requires the ground ignition control device to have high reliability and safety to ensure the success of aircraft ground ignition and the personal safety of operators. The test and launch control system introduced in the document Missile and Space Launch Technology-2004-1 (34) "Manned Space Launch Vehicle Ground Test Launch Control System" has a complex structure, large volume, and is not easy to move, so it cannot adapt to the conditions of field mobile launch. The portable rocket engine ground test measurement and control system introduced in the patent publication No. CN102042122A "Portable Rocket Engine Ground Test Measurement and Control System" is mainly ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G5/00
Inventor 宋佳蔡国飙孔德帅陈辰唐振宇
Owner BEIHANG UNIV
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