The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled ...The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.展开更多
In-orbit pointing accuracy and pointing stability are two of the most important technical indicators for ensuring the effective operation of the payload.Traditionally,these two indicators are guaranteed by the attitud...In-orbit pointing accuracy and pointing stability are two of the most important technical indicators for ensuring the effective operation of the payload.Traditionally,these two indicators are guaranteed by the attitude control system of the support module.The ever-increasing demands of space missions,along with the flexibility of spacecraft and the presence of both internal and external disturbances,make it a challenge to enhance the accuracy and stability of the attitude control system in the overall design.The Disturbance-Free Payload architecture,which separates the payload module from the support module to provide natural vibration isolation,has been developed and promoted.This article provides an overview of its modeling and control methods,introducing general dynamic equations and advanced motion control techniques.In addition,this article presents the performance verification methods,including the numerical simulation logic,the ground verification platform setup,and the in-orbit model.Written in a tutorial style to familiarize researchers with the essentials,this paper serves as a reference for the design and practice of Disturbance-Free Payload high-performance spacecraft.展开更多
基金supported by the National Natural Science Foundation of China (Nos. 11502086 and 11502087)
文摘The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.
基金National Natural Science Foundation of China under Grants U24B20157 and 62473023Fundamental Research Funds for the Central Universities+1 种基金National Natural Science Foundation of China under Grant 62303132Beijing Natural Science Foundation under Grant 4242043。
文摘In-orbit pointing accuracy and pointing stability are two of the most important technical indicators for ensuring the effective operation of the payload.Traditionally,these two indicators are guaranteed by the attitude control system of the support module.The ever-increasing demands of space missions,along with the flexibility of spacecraft and the presence of both internal and external disturbances,make it a challenge to enhance the accuracy and stability of the attitude control system in the overall design.The Disturbance-Free Payload architecture,which separates the payload module from the support module to provide natural vibration isolation,has been developed and promoted.This article provides an overview of its modeling and control methods,introducing general dynamic equations and advanced motion control techniques.In addition,this article presents the performance verification methods,including the numerical simulation logic,the ground verification platform setup,and the in-orbit model.Written in a tutorial style to familiarize researchers with the essentials,this paper serves as a reference for the design and practice of Disturbance-Free Payload high-performance spacecraft.
