Modular Attitude Control System for Scalable Satellite Torque
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Solution Overview
Problem
Current attitude control systems for satellites, particularly in the weight range of 50-500 kg, face challenges with scalability and mechanical robustness, as existing Control Moment Gyroscope (CMG) systems are either too complex or not suitable for smaller sizes, and modular solutions lack adjustable orientation and functionality.
Innovation Solution
A modular attitude control system comprising compact, easily assembled modules with a robust rectangular support frame, including a reference structure, flywheel support structure, and a rotatable flywheel, which can operate as either a reaction wheel or a single gimbal control moment gyroscope (SGCMG), allowing for adjustable orientation and easy combination with other modules to meet specific satellite requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If dedicated CMG systems are developed for large satellites (500 kg and more), then high output torque is achieved, but the system is not scalable to smaller sizes
Solution Approach 1:
The attitude control system is divided into multiple identical modular units, each containing a CMG assembly. These modules can be independently manufactured and then combined in various configurations to match different satellite mass requirements, enabling scalability from small to large satellites while maintaining high torque capability through parallel module operation
Solution Approach 2:
The patent designs a universal modular platform that can serve multiple satellite classes (nano, micro, and small satellites) through standardized interfaces and scalable module arrangements. The same basic module design can be used across different satellite types, reducing development costs and enabling the system to adapt to various mass ranges without requiring dedicated designs for each satellite class
2Reliability
If an assembly of four single gimbal CMG units in a rectangular frame is proposed, then attitude control capability is improved, but the design becomes technically complex and lacks mechanical robustness
Solution Approach 1:
Instead of creating a complex integrated assembly of four CMG units, the system segments the attitude control function into multiple independent modular units. Each module contains a simplified CMG assembly that can be independently tested, maintained, and replaced, reducing overall system complexity while maintaining full attitude control capability through coordinated operation of the modules
Solution Approach 2:
The patent combines the CMG assembly with the modular platform structure in an integrated design where the platform itself provides mechanical support and alignment. This merging of structural and functional elements simplifies the overall design by eliminating separate complex mounting structures while enhancing mechanical robustness through the rigid platform foundation
3Ease of manufacture
If modular CMG systems are used, then ease of assembly is improved, but adjustable orientation and functionality are lost
Solution Approach 1:
The modular platform incorporates adjustable mounting mechanisms that allow the orientation of individual CMG modules to be dynamically configured during assembly. This enables the system to adapt to different mission requirements and satellite configurations while maintaining the ease of modular assembly, as modules can be rotated or repositioned on the platform before final fixation
Solution Approach 2:
The patent designs modules with pre-configured mounting interfaces and alignment features that simplify assembly procedures. Standardized mechanical and electrical interfaces are prepared in advance on each module, allowing for rapid connection to the platform and other modules without complex alignment procedures, thus maintaining ease of assembly while enabling flexible configuration through preliminary design of adjustable interfaces
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 modular system provides a scalable and mechanically robust attitude control solution that can be adapted to various satellite weights, combining SGCMG and reaction wheel modules for efficient attitude control, enhancing reliability and flexibility.
Implementation Method 1
a flywheel and a flywheel support structure, wherein the flywheel support structure is oriented along a first axis that is perpendicular with respect to the platform, a flywheel motor for actuating the rotation of the flywheel relative to the flywheel support structure about a second axis that is essentially perpendicular to the first axis
Implementation Method 2
These systems control the craft's orientation relative to its own centre of gravity, in order to maintain a given position with respect to the earth and/or to a predefined orbit
Data Source
AI summary
A spacecraft attitude control module (1) according to the invention is compact and easy to assemble with additional modules to form an operative attitude control system. The module comprises a robust rectangular, preferably cubic support frame with an attitude control assembly fitted within the confines of the support frame, the assembly including a reference structure comprising a platform, a flywheel support structure (15, 18, 19, 26) and a flywheel (25). The flywheel support structure may be fixed to the platform (10) or it may be a gimbal structure that is rotatable relative to the platform. In the first case the module is a reaction wheel module. In the second case the module is a single gimbal control moment gyroscope module. A preferred embodiment includes a slanted position of the platform (10) relative to the ground plane (100) of the support frame. Another preferred characteristic is the implementation of a flywheel provided with a hollow portion (25′) into which the motor (28) that is driving the flywheel rotation is fitted. The invention is also related to an attitude control system comprising multiple modules assembled together on a support plate (35). The modules may be provided with decking plates (39, 39′) to improve the mechanical robustness of the assembly and to realize fast electrical connections to the modules.