Carrier rocket electrical system based on FC-AE-1553 high-speed bus

A launch vehicle and high-speed bus technology, applied in the general control system, electrical test/monitoring, control/regulation system, etc., can solve the problem of launch vehicle function upgrade, maintenance, test inconvenience, low bus throughput, low degree of integration, etc. problems, to achieve the effects of reducing the probability of bus anomalies, clear system architecture, and simple stand-alone interface

Active Publication Date: 2020-12-25
SHANGHAI AEROSPACE SYST ENG INST
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AI Technical Summary

Problems solved by technology

Traditional launch vehicle electrical systems are large in scale and complex in structure, low in integration, complex in bus types, and low in bus throughput, which seriously affect the carrying capacity. Facing the demand for rocket fault diagnosis and health monitoring functions under the new situation, due to the high power output and high dynami...

Method used

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  • Carrier rocket electrical system based on FC-AE-1553 high-speed bus
  • Carrier rocket electrical system based on FC-AE-1553 high-speed bus
  • Carrier rocket electrical system based on FC-AE-1553 high-speed bus

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Embodiment

[0061] Taking the two-stage rocket as an example, the electrical system of the launch vehicle based on the FC-AE-1553 high-speed bus adopts a switching structure. Drive mechanism (level 2), data management center, rocket level 1 including integrated actuator (level 1), servo controller and drive mechanism (level 1), telemetry acquisition and editing equipment (level 1); ground equipment includes ground host. like Figure 1~3 shown.

[0062] The integrated control computer 201, the inertial measurement equipment 202, the integrated actuator (secondary) 203, the servo controller and the driving mechanism (secondary) 204, the data management center 205, access the dual redundant optical fiber through optical fiber The switch 206, the optical fiber drawn from the comprehensive actuator (level one) 101, the servo controller and the drive mechanism (level one) 102 is connected to the dual redundant fiber optic switch 206 through the fiber separation plug, and the ground host 104 is...

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Abstract

The invention discloses a test method of a carrier rocket electrical system based on an FC AE 1553 high-speed bus. The method comprises the following steps that S1, a test program starts, a ground host is initialized to be a network controller of the FC-AE-1553 high-speed bus, and other devices of the electrical system are initialized to be network terminal devices of the FC-AE-1553 high-speed bus; S2, after test indexes of each device of a rocket and the ground are qualified, a ground host delivers a control right to a comprehensive control computer; S3, the ground host sends a primary engineignition instruction to a comprehensive actuator, and the comprehensive control computer globally broadcasts a takeoff moment to the FC-AE-1553 high-speed bus after receiving takeoff and enters navigation guidance and rocket attitude control; and S4, a data management center collects measurement data of a carrier rocket, then evaluates a health degree of the rocket and sends an evaluation resultto the comprehensive control computer.

Description

technical field [0001] The invention relates to a launch vehicle electrical system based on FC-AE-1553 high-speed bus, in particular to a launch vehicle electrical system based on high-speed bus information interaction, belonging to the technical field of launch vehicle electrical system design. Background technique [0002] At present, the competition in the field of space launch is becoming increasingly fierce. All major aerospace countries are launching or developing low-cost launch vehicles. These rockets have a high degree of automation, a short development cycle, and strong versatility. The use of advanced intelligent development and production models greatly reduces the launch cycle and cost of rockets. , Compared with my country's traditional launch vehicle research and development model, it has great advantages. As one of the most important systems of the launch vehicle, the electrical system can achieve high reliability, health management, and rapid test launch beco...

Claims

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Application Information

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IPC IPC(8): G05B23/02G06N3/04
CPCG05B23/0213G05B23/0254G06N3/049G06N3/045
Inventor 张元明顾寒烈蔡益飞吴佳林谢立高耸
Owner SHANGHAI AEROSPACE SYST ENG INST
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