Control Moment Gyroscope Spatial Reconfiguration
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Solution Overview
Problem
Control moment gyroscopes (CMGs) face challenges in efficiently utilizing available space within spacecraft due to fixed geometrical constraints, limiting their ability to change spatial configurations and optimize volume usage during operation.
Innovation Solution
A CMG design that selectively alternates between a first spatial configuration, where no part projects beyond a predetermined boundary, and a second configuration, where parts project beyond, allowing for variable volume and external envelope adjustments, enabling compact configurations and maximizing payload envelope utilization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the CMG operates in a fixed spatial configuration within the payload envelope, then it maintains compactness and fits within spacecraft constraints, but it cannot optimize volume usage or project outward during operation
Solution Approach 1:
The CMG is designed with dynamic spatial reconfiguration capability, allowing it to transition between different spatial configurations during operation. The rotor assembly can be positioned in multiple locations relative to the gimbal assembly, enabling the CMG to adapt its volume and external envelope based on operational requirements while maintaining compatibility with spacecraft payload envelope constraints
2Adaptability or versatility
If the CMG projects beyond the payload envelope during operation, then it can optimize spatial configuration and enhance attitude control capabilities, but it cannot remain compact within the spacecraft constraints
Solution Approach 1:
The CMG employs dynamic spatial reconfiguration where the rotor assembly can be selectively positioned to project beyond the payload envelope when needed for optimal attitude control performance, while being capable of retracting to a compact configuration within the envelope when space constraints require. This dynamic adaptability resolves the contradiction between projecting outward for performance and remaining compact for spacecraft integration
3Power
If the CMG uses a variable speed rotor, then it can enhance control authority and maneuverability, but it increases device complexity and energy consumption
Solution Approach 1:
The CMG utilizes variable rotor speed as a controllable parameter to enhance control authority and maneuverability. By adjusting the rotor speed, the system can optimize performance for different maneuvering requirements without adding complex mechanical structures. The variable speed capability allows dynamic adjustment of angular momentum, providing greater control flexibility while managing system complexity through electronic control rather than mechanical complexity
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
This design allows for efficient use of available space by enabling the CMG to project outward during operation while remaining compact within the payload envelope, enhancing attitude control capabilities and reducing spatial constraints.
Implementation Method 1
A rotor assembly is rotatably mounted to a gimbal system about a rotor spin axis
Implementation Method 2
gimbal system is in turn rotatably mounted to the housing about a gimbal axis. Rotor motor mounted to the gimbal system is provided for controllably spinning the rotor assembly about the rotor spin axis
Implementation Method 3
gimbal system is in turn rotatably mounted to the housing about a gimbal axis
Data Source
Figure 1
Figure 1(a)~1(b)
Figure 1(c)~1(d)
AI summary
A control moment gyroscope (CMG) is provided, selectively having a first spatial configuration and a second spatial configuration at least during operation of the CMG. In the first spatial configuration the CMG occupies a smaller volume than in the second spatial configuration. For example, in the first spatial configuration no part of the CMG projects beyond a predetermined geometrical boundary, while in the second spatial configuration, a portion of the CMG projects beyond the geometrical boundary.