Polymerization type on-orbit structure-varying micro-nano satellite turn control method

Abstract

The invention discloses a polymerization type on-orbit structure-varying micro-nano satellite turn control method, and relates to the field of micro-nano satellite design. The polymerization type on-orbit structure-varying micro-nano satellite turn control method comprises the following steps that S1, momentum wheels are arranged inside module satellites, and magnetic hinges and magnetic locking devices are arranged on the side edges; S2, in the initial state, the magnetic hinges are electrified, and the four magnetic locking devices corresponding to contact surfaces of the two module satellites are locked; S3, in the starting stage, the magnetic locking devices are unlocked, the momentum wheels push the module satellites to turn by taking relatively fixed edges as axes; S4, in a constant-speed turn stage, the turn module satellites turn at a constant speed; S5, in a speed reduction turn stage, the momentum wheels drive the turn module satellites to perform speed reduction turn; S6, the magnetic locking devices are locked, the two module satellites are relatively fixed, and the magnetic hinges are powered off. The polymerization type on-orbit structure-varying micro-nano satelliteturn control method has the advantages that quite high flexibility and expandability are achieved, structure vary of among all the components can be more conveniently performed, and requirements of elastic high-dynamic disaster reduction remote sensing application, large-scale space-based system construction and on-orbit maintenance service application and the like can be quite well achieved.

Description

technical field [0001] The invention relates to the field of micro-nano-satellite design, in particular to a method for controlling flipping of micro-nano-satellites with on-orbit variable configuration. Background technique [0002] Micro-nano satellites have the advantages of large number, small size, and flexibility. However, in the application of disaster reduction and rescue in some areas in the future, remote sensing satellite systems are required to meet the task requirements of more dynamic, flexible, and fast response; on-orbit maintenance and service applications Among them, it has diverse and flexible on-orbit services and efficient space survivability; in the application of star surface detection in unknown environments, it has the detection requirements that can change its configuration to adapt to different environmental conditions. The micro-nano-satellite system in these applications currently has the following problems: [0003] (1) In the current disaster ...

AI Technical Summary

Problems solved by technology

[0003] (1) In the current disaster reduction and rescue applications, small satellites and microsatellite systems are mostly used for observation, which has good timeliness and can quickly revisit disaster situations. Observation capability is limited and affected by weather conditions

[0004] (2) In the current on-orbit maintenance and service applications, the space on-orbit service system can only provide one service at a time, and it does not have the ability to concurrently serve multiple places or multiple spacecraft on the same large spacecraft at the same time in an emergency ability

[0005] (3) In the current application of star surface detection, the ability to change the detection configuration is limited, and a single shape will limit the ability of the detector to adapt to multiple complex environments in an unknown environment

Images