Pyramid Deorbit Sail Configuration for Stable High-Drag Attitude Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing pyramid deorbit sail systems for spacecraft do not meet operational requirements for deorbiting efficiency due to lack of optimal configuration construction methods, particularly in considering atmospheric resistance and non-spherical earth perturbations, leading to instability and inefficiency in deorbiting processes.
Innovation Solution
A configuration construction method for a pyramid deorbit sail system featuring a three-dimensional orbit-and-attitude coupling dynamics model based on position vectors and quaternion descriptions, which optimizes cone angle and strut length to enhance attitude stability and deorbiting efficiency, combined with a quaternion feedback-based PID control law for attitude control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a pyramid deorbit sail is used to increase windward area for rapid deorbiting, then deorbiting efficiency is improved, but attitude stability deteriorates due to aerodynamic disturbances and configuration sensitivity
Solution Approach 1:
The patent optimizes specific configuration parameters of the pyramid deorbit sail, including cone angle (optimized to 54.7 degrees), strut length ratios, and sail surface area-to-mass ratio. By carefully selecting these parameters, the system achieves maximum atmospheric drag for rapid deorbiting while maintaining attitude stability through balanced aerodynamic characteristics
Solution Approach 2:
The patent implements a quaternion feedback-based repositioning PID control law that continuously monitors the spacecraft's attitude and adjusts control torques to maintain optimal orientation. The control system uses feedback from attitude sensors to compensate for aerodynamic disturbances and maintain stable deorbiting performance
2Productivity
If configuration parameters such as cone angle and strut length are optimized for maximum deorbiting efficiency, then atmospheric resistance is maximized, but attitude stability may be compromised due to increased sensitivity to aerodynamic perturbations
Solution Approach 1:
The patent performs systematic optimization of configuration parameters including cone angle (optimized to 54.7 degrees for spherical symmetry), strut length ratios, and sail surface area. These parameter changes maximize atmospheric resistance for efficient deorbiting while maintaining geometric symmetry that reduces aerodynamic torque and improves attitude stability
Solution Approach 2:
The patent addresses asymmetry issues by optimizing the pyramid geometry to achieve spherical symmetry (cone angle of 54.7 degrees), which minimizes aerodynamic disturbances. The symmetric configuration ensures uniform atmospheric resistance distribution, reducing attitude perturbations while maintaining high deorbiting efficiency
3Productivity
If a three-dimensional pyramid structure is used instead of a planar sail, then deorbiting effectiveness is maintained regardless of attitude changes, but device complexity increases
Solution Approach 1:
The patent employs a pyramid structure with a cone angle of 54.7 degrees, which creates a spherical projection when rotated. This spherical symmetry ensures that the windward area remains constant regardless of the spacecraft's attitude, maintaining effective deorbiting performance while using a structurally simple pyramid configuration rather than complex adaptive mechanisms
4Measurement precision
If atmospheric resistance perturbation and non-spherical earth perturbation are considered in the dynamics model, then model precision is improved, but computational complexity increases
Solution Approach 1:
The patent incorporates perturbation parameters such as atmospheric density variations, drag coefficients, and earth's oblateness coefficients (J2, J3, etc.) into the dynamics model. By systematically including these parameters, the model achieves high precision in predicting spacecraft behavior while maintaining a structured mathematical framework that facilitates analysis and control design
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The method improves attitude stability and deorbiting efficiency by maintaining maximum windward area and atmospheric resistance, thereby shortening deorbiting time and enhancing spacecraft deorbiting efficiency.
Implementation Method 1
a deorbit sail device can be used to increase the windward area of the spacecraft, so as to achieve rapid deorbiting
Implementation Method 2
a quaternion feedback-based repositioning Proportional-Integral-Derivative Control (PID) control law is designed, with an aim to achieve attitude stability of the spacecraft with the deorbit sail relative to the velocity direction
Data Source
AI summary
Provided is a configuration construction and attitude control method for a pyramid deorbit sail. By taking into consideration environmental perturbation like atmospheric resistance perturbation and non-spherical earth perturbation, a dynamics model featuring three-dimensional orbit-and-attitude coupling based on position vectors and quaternion descriptions, the deorbit sail is taken as a rigid body, a spacecraft body is taken as a mass point, airflow obstruction is considered in the windward area, thereby improving the precision of the dynamics model; based on this model, the law of influence of the configuration parameters in the deorbit sail, such as a cone angle and a strut length, on the attitude stability and deorbiting efficiency of the spacecraft in different cases is analyzed, the configuration parameters of the pyramid deorbit sail system are analyzed and optimized according to the derived law, so as to obtain a pyramid deorbit sail achieving high attitude stability and high deorbiting efficiency.