Solid-liquid power air vehicle ground test and launch control system of 422 bus

A technology of ground measurement, launch and control and aircraft, applied in electrical testing/monitoring and other directions, can solve the problems of solid-liquid powered aircraft launch, scarcity of safety control, etc., and achieve safe and efficient ground test launch control, easy operation, and good portability.

Active Publication Date: 2014-02-05
BEIHANG UNIV
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Problems solved by technology

[0004] The solid-liquid powered aircraft integrates the characteristics of the liquid-powered aircraft and the solid-powered aircraft, but there are few relevant literatures on the ground measurement and control s

Method used

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  • Solid-liquid power air vehicle ground test and launch control system of 422 bus
  • Solid-liquid power air vehicle ground test and launch control system of 422 bus
  • Solid-liquid power air vehicle ground test and launch control system of 422 bus

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Embodiment Construction

[0026] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0027] A 422-bus solid-liquid powered aircraft ground measurement and launch control system proposed by the present invention takes the RS422 bus instrument as the core and adopts a front-end and back-end distributed layout, such as figure 1 As shown, it specifically includes a ground integrated console 1 , a conditioning control case 2 , a flight control computer 3 and a telemetry / remote control system 4 . Wherein, the conditioning control cabinet 2 is located under the launching stand, and the integrated ground console 1 is located outside a safe distance. The solid-liquid powered aircraft in the embodiment of the present invention is a solid-liquid powered sounding rocket 5 . The flight control computer 3 and the telemetry / remote control system 4 are installed on the solid-liquid powered sounding rocket 5, such as figure ...

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Abstract

The invention relates to a solid-liquid power air vehicle ground test and launch control system of a 422 bus. The system comprises a ground integrated console, an adjusting control machine box, a flying control computer and a telemetering/telecontrol system. A main control computer of the ground integrated console uses a human-computer interaction interface, a CP-134U-I/DB9M board card of MOXA is used as a 422 node, orders are received and sent, and state information is displayed. The adjusting control machine box carries out ground and missile-borne power supply and distribution, signal forwarding, signal state monitoring and testing. The flying control computer receives orders sent by the main control computer and feeds the state information of an air vehicle back to the ground. According to the system, ground testing of the whole system, missile-borne system self detecting, result back transmitting, flying control data stapling, important parameter real-time detecting and system information back reading can be completed, and comprehensive monitoring of bus information, data real-time storage and displaying and safe protecting integration design are achieved.

Description

technical field [0001] The invention belongs to the technical field of ground measurement, launch and control, and in particular relates to a ground measurement, launch and control system of a 422-bus solid-liquid power aircraft. Background technique [0002] The solid-liquid power aircraft is a new type of aircraft that uses a solid-liquid power engine as a power device and has the characteristics of adjustable thrust and multiple starts. Compared with solid-powered engines, solid-liquid powered engines can achieve thrust adjustment, long-term work, and multiple starts, and the combustion products do not pollute the environment; compared with liquid-powered engines, solid-liquid powered engines have simple structure, convenient operation, and low cost . Therefore, in the development of a new generation of aircraft power system, the solid-liquid power engine has a greater advantage. [0003] However, the ground test, ignition launch, and safety control of the aircraft have...

Claims

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Application Information

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IPC IPC(8): G05B23/02
Inventor 宋佳蔡国飙李小川王伦施文杰
Owner BEIHANG UNIV
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