Spacecraft flight control method, system and device

A flight control and spacecraft technology, applied in the field of spacecraft, can solve the problems of high cost and design complexity, and achieve the effect of reducing design complexity and cost

Pending Publication Date: 2019-06-18
宁波天擎航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The embodiment of the present invention provides a spacecraft flight control method, aiming to solve the

Method used

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  • Spacecraft flight control method, system and device
  • Spacecraft flight control method, system and device
  • Spacecraft flight control method, system and device

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Embodiment 1

[0041] Each of the following embodiments can be applied to figure 1 Illustrated in spacecraft 10, where, figure 1 It is a structural diagram of a spacecraft 10 in an embodiment of the present invention, and the spacecraft 10 shown in the figure includes an orbit control propulsion system 11 and two attitude control propulsion systems 12 that are independent of each other.

[0042] Wherein, the orbit control propulsion system 11 is arranged at the bottom of the main structure of the spacecraft 10 to ensure that the thrust axis of the engine passes through the center of gravity of the spacecraft, and it is mainly responsible for orbital maneuvering of the spacecraft; the two attitude control propulsion systems 12 are symmetrical Distributed on both sides of the upper part of the main structure of the spacecraft 10, it is ensured that only control torque is generated and no disturbance force is generated. It mainly provides pitching moment, yaw moment, rolling moment and reverse ...

Embodiment 2

[0049] see Figure 4 , shows the spacecraft flight control method in the first embodiment of the present invention, the spacecraft includes a plurality of separate propulsion systems, and each of the propulsion systems controls at least one flight parameter of the spacecraft, so The spacecraft flight control method includes steps S01 to S03.

[0050] Step S01, acquiring the current flight parameters of the spacecraft.

[0051] In this embodiment, the flight parameters of the spacecraft include pitch angle, yaw angle, roll angle, flight speed and flight trajectory. In this step S01, the acquired current flight parameters may be one or more of pitch angle, yaw angle, roll angle, flight speed and flight trajectory. But the present invention is not limited thereto. In other embodiments, the flight parameters of the spacecraft may also include more or fewer flight parameters, for example, may also include pitch angle change rate, yaw angle change rate, ascending node eccentric Wai...

Embodiment 3

[0075] On the other hand, the present invention also proposes a spacecraft flight control system, please refer to Figure 5 , shows the spacecraft flight control system of the third embodiment of the present invention, the spacecraft includes a plurality of separate propulsion systems, and each of the propulsion systems controls at least one flight parameter of the spacecraft, so Said spacecraft flight control system includes:

[0076] A parameter acquisition module 141, configured to acquire the current flight parameters of the spacecraft;

[0077] A correction amount calculation module 142, configured to calculate the correction amount of the current flight parameter according to predetermined flight parameters;

[0078] The parameter correction module 143 is configured to control the corresponding propulsion system to perform parameter correction on the spacecraft according to the correction amount.

[0079] Wherein, the flight parameters include any one of pitch angle, y...

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Abstract

The invention is suitable for the technical field of a spacecraft and provides a spacecraft flight control method, system and device. The spacecraft includes multiple separate propulsion systems, wherein each propulsion system correspondingly controls at least one flight parameter of the spacecraft. The method comprises steps that current flight parameters of the spacecraft are obtained; the correction amount of the current flight parameters is calculated based on predetermined flight parameters; according to the correction amount, the corresponding propulsion system is controlled for performing parameter correction of the spacecraft. The method is advantaged in that the correction amount of the current flight parameters is calculated based on the current flight parameters of the spacecraft and the predetermined flight parameters, the corresponding propulsion system is controlled for performing parameter correction of the spacecraft, the multiple separately distributed propulsion systems can together complete power requirements of the entire spacecraft, design complexity and cost of the propulsion systems are reduced, moreover, each propulsion system can achieve the optimal conditions.

Description

technical field [0001] The invention belongs to the technical field of spacecraft, and in particular relates to a flight control method, system and device of a spacecraft. Background technique [0002] With the continuous development of aerospace technology, and in order to meet more and more demands, spacecraft are becoming larger and more complex, and the mission mode is becoming more and more complex. Especially for manned spacecraft that need to be combined in orbit, such as space stations, their propulsion The system is becoming more and more complex, and more and more functions need to be completed. [0003] The propulsion system is a power system used to provide power to the spacecraft, and is mainly used to realize functions such as orbit control, pitch, yaw, roll, and reverse thrust of the spacecraft. By controlling the operating parameters of the propulsion system, the flight parameters of the spacecraft can be precisely controlled. [0004] Among the existing te...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 谌忠庭胡向柏张汉秀杨敬贤杨威李海涛王彬平张海涛朱勇
Owner 宁波天擎航天科技有限公司
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