Spacecraft quality characteristic balancing method

Abstract

The invention provides a spacecraft quality characteristic balancing method. The method comprises the following steps that discretization treatment is performed on a balancing region, a spacecraft balancing layout optimization mathematical model is built, and an optimization algorithm is used for performing preliminary design of a balancing scheme; a spacecraft cabin balancing layout three-dimensional model is constructed, computed results of two balancing design schemes of the optimization mathematical model and the three-dimensional model are compared in real time, a multi-software multi-platform calibrates and corrects parameters of the optimization mathematical model in real time; on the basis of the quality characteristic obtained before balancing of the aircraft, the corrected optimization mathematical model is used for performing preliminary balancing design work on the spacecraft, then, balancing is performed, and actual measurement of the quality characteristic is performed; according to the actual measurement value, some parameters of the optimization mathematical model are secondarily corrected; the optimization mathematical model obtained after secondary parameter correction is used for performing the quality characteristic balancing design work on the spacecraft. The method can rapidly provide optimized balancing weight selection and installation schemes and meet the requirement for the high-precision quality characteristic of the spacecraft.

Description

technical field [0001] The invention relates to a method for trim design of mass characteristics of spacecraft, and belongs to the technical field of trim design of mass characteristics of spacecraft. Background technique [0002] The mass characteristics of the spacecraft are important factors affecting the attitude and trajectory of the spacecraft during flight and re-entry. The equipment layout of the spacecraft is restricted by multiple conditions such as space, field of view, and equipment operability. Generally, the spacecraft needs to be installed on the spacecraft during the manufacturing stage according to the expected mass distribution of the spacecraft launch / reentry state Counterweights to ensure that their quality characteristics meet the design requirements. The quality characteristics of the spacecraft require three parameters: the position of the center of mass, the moment of inertia, and the product of inertia. Due to the coupling of the above parameters, ...

AI Technical Summary

Problems solved by technology

The traditional manual calculation method is cumbersome, the workload is heavy, and there is a possibility that an effective trimming scheme cannot be obtained

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