In-orbit autonomous shutdown control method of spacecraft propulsion system

A propulsion system and shutdown control technology, applied in the field of aerospace propulsion theory and engineering research, can solve problems such as no shutdown methods, and achieve the effects of improving reliability and safety, light weight and small size

Inactive Publication Date: 2009-08-19
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, there is no domestic spacecraft that adopts a new type of liquefied gas propulsion system to successfully implement orbit control.

Method used

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  • In-orbit autonomous shutdown control method of spacecraft propulsion system
  • In-orbit autonomous shutdown control method of spacecraft propulsion system
  • In-orbit autonomous shutdown control method of spacecraft propulsion system

Examples

Experimental program
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Embodiment 1

[0035] Please refer to figure 1 , which adopts the closed-loop control method of heaven and earth. The ground calculates the orbit control strategy based on the orbit measurement data, and then formulates the corresponding orbit control instructions according to the orbit control strategy. The satellite enters the country and injects the orbit control instructions into the satellite. The satellite coordinates the work of various functional modules according to the orbit control instructions, including completing the reception of the orbit change instruction, controlling the propulsion system to execute the power on and off according to the predetermined strategy, controlling the orientation and attitude stability of the orbit change, and controlling the temperature environment of the storage tank, etc. Accurate control of propulsion system switch is a key issue.

[0036] For the new self-pressurized liquefied gas propulsion system, in this embodiment, the shutdown control met...

Embodiment 2

[0076] The difference between this embodiment and Embodiment 1 is that in this embodiment, the shutdown control method of the present invention only includes a "pressure-velocity" control mode, and the specific process is the same as that of Embodiment 1.

Embodiment 3

[0078] The difference between this embodiment and Embodiment 1 is that in this embodiment, the shutdown control method of the present invention only includes a "temperature-time" control method, and the specific process is the same as that of Embodiment 1.

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Abstract

The invention discloses a method for controlling the in-orbit autonomous shutdown of a spacecraft propulsion system, which comprises a pressure-speed shutdown control mode: in the process of performing orbit control, measuring the storage tank pressure P by a pressure sensor; determining the thrusting force coefficient k through an in-orbit calibration on the ground; calculating the speed increment delta-v generated in each software cycle delta-T for the propulsion system when a satellite receives an orbit control command sent from the ground, wherein delta-v=(F.delta-T)/m=(k.P.delta-T)/m; and accumulating the delta-v, and comparing the same with the 'speed increment' v in the ground orbit control command, wherein if the accumulated result of the delta-v is more than or equal to the 'speed increment' v in the ground orbit control command, the propulsion system is controlled to perform shutdown. The method uses two shutdown control modes of temperature-time and pressure-speed to solve the key problem of accurately performing starting up and shutdown by a novel self-pressurization liquefied gas propulsion system.

Description

technical field [0001] The invention belongs to the field of aerospace propulsion theory and engineering research, and relates to a shutdown control method, in particular to a spacecraft propulsion system on-orbit autonomous shutdown control method. Background technique [0002] The development trend of the aerospace field requires that the future spacecraft must have a strong attitude, orbital maneuverability and high safety. The new self-pressurized liquefied gas propulsion system belongs to the cold gas propulsion, which has the advantages of simplicity, reliability and high safety. Field attention, it will have broad application prospects on future spacecraft, especially micro-satellite platforms. The switch control method is the core technology of the new self-pressurized liquefied gas propulsion system applied to the actual aerospace engineering. Its main task is to accurately control the switch time of the propulsion system by inputting the predetermined control strat...

Claims

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Application Information

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IPC IPC(8): B64G1/24
Inventor 余勇陈宏宇张锐朱振才魏青徐文明左霖吴会英李永策
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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