Relative Position Control Method of Satellite Formation Payload Based on Linear Momentum Exchange

Abstract

The invention discloses a satellite formation payload relative position control method based on line momentum exchange. The method mainly includes three-level formation control processes. The first-level formation control uses an inter-satellite baseline as a controlled object, a thruster is selected and used as an execution structure, an initial deviation is eliminated, and the control precision reaches the m level; the second-level formation control uses the inter-satellite baseline as a controlled object, a second-level pneumatic plate is used for controlling, atmospheric perturbation is eliminated, the control precision reaches the dm level; the third-level formation control uses a line momentum exchange device for control, gravitational perturbation is eliminated, the control precision reaches the mm level, and precise control over the satellite formation payload relative position is achieved. The control accuracy is high, the engineering feasibility is strong, fuel consumption can be reduced, and the control is high pertinence.

Description

technical field [0001] The invention relates to the field of formation satellites, in particular to a method for controlling the relative position of satellite formation payloads based on linear momentum exchange. Background technique [0002] With the demonstration of the German TanDEM-X formation mission, the Swedish Prisma formation mission in orbit and the demonstration of the TanDEM-L formation mission, it can be seen that: [0003] (1) The formation satellite collaborative work system has extensive and good application prospects and requirements in global three-dimensional surveying and mapping, moving target monitoring, and astronomical observation; [0004] (2) The combination of formation satellite system system and multi-band, multi-aperture and different orbit heights will be built into a large system similar to GPS and BD-2 navigation system. [0005] Therefore, with the diversification of formation satellite application requirements and the complexity of workin...

AI Technical Summary

Problems solved by technology

[0007] (1) The relative position maintenance accuracy of formation satellites is insufficient;

[0008] The relative control accuracy of the formation satellites in the existing control scheme can reach the highest level of 10m, which is quite different from the precision formation requirements of mm level precision

[0009] (2) The existing scheme has insufficient improvement potential;

[0010] On the basis of the existing scheme, by improving the accuracy of the relative measurement sensor and selecting the micro-propulsion method, the relative position control accuracy of the formation satellites can be improved to a certain extent (from the 10m level to the m level), but in order to achieve mm-level precision precision The formation will put forward requirements on the satellite platform’s performance by 2 to 3 orders of magnitude higher in terms of propulsion device installation accuracy, satellite platform attitude control accuracy, propulsion device switching characteristics, and inter-satellite surface-to-mass ratio differences. The engineering feasibility is insufficient. Even if the satellite platform can achieve the aforementioned indicators, it will bring limitations such as a significant increase in formation control time, huge fuel consumption, and a serious drop in payload efficiency.

[0011] (3) Insufficient control pertinence;

[0014] Moreover, the difference in fuel consumption between satellites not only affects the service life of formation satellites, but also affects the stability of formation configuration (the spatial relative relationship between formation satellites) and the accuracy of formation control by intensifying the perturbation effect of atmospheric drag.

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