Rotatable Space Object Deployment System with Spring-Loaded Countermass
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Solution Overview
Problem
Current space object deployment systems face challenges in achieving high velocity deployment without complex and costly countermeasures, as they struggle with maintaining stability and controlling equal and opposite forces, especially when deploying multiple objects simultaneously or on different trajectories, which can lead to increased system complexity and potential failure points.
Innovation Solution
A space object deployment system utilizing a rotatable housing with spring-loaded countermass and deployable objects, where the housing is selectively rotated to generate centripetal force, allowing for detachment and automatic expansion of the spring and countermass to maintain center of mass harmony, eliminating the need for equal and opposite force systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a force is applied to launch the deployed object at high velocity, then the deployment speed is improved, but the space vehicle experiences opposite reaction force causing displacement and stability issues
Solution Approach 1:
The patent employs a counterweight mechanism where a mass is positioned on the opposite side of the deployment axis to balance the reaction force generated during object deployment. This counterweight system allows high velocity deployment while maintaining space vehicle stability by canceling out the opposite reaction force through gravitational balance rather than thruster compensation.
2Force
If symmetric deployment of equal mass objects in opposite directions is used to cancel reaction forces, then the counterforce balance is improved, but the system complexity and cost increase due to sacrificial objects and synchronization requirements
Solution Approach 1:
The patent utilizes asymmetric deployment geometry where objects are deployed from chambers positioned at specific angles relative to the space vehicle's center of mass, not in symmetric opposite directions. This asymmetric configuration allows the counterweight mechanism to balance reaction forces while deploying only the necessary number of objects without requiring sacrificial counterweights or complex synchronization systems.
Solution Approach 2:
The patent extracts and eliminates the need for sacrificial counterweight objects by using the space vehicle's own structural mass as the counterbalance. Instead of deploying paired objects where one serves as a sacrificial counterweight, the system uses pre-positioned counterweights integrated into the deployment mechanism, reducing object count and system complexity.
3Force
If thrusters are used to apply opposite force for maintaining position and stability, then the counterforce control is improved, but the system requires precise operation and propellant consumption
Solution Approach 1:
The patent replaces the mechanical thruster-based counterforce system with a passive gravitational counterweight mechanism. Instead of using propellant-consuming thrusters to generate opposite force, the system uses the gravitational force of pre-positioned counterweights to balance the reaction forces during deployment, eliminating propellant consumption and reducing active control requirements.
4Productivity
If multiple objects are deployed simultaneously on different trajectories, then the deployment capability is improved, but the equal and opposite force control becomes even more complex and challenging
Solution Approach 1:
The patent segments the deployment system into multiple independent chambers, each capable of deploying objects on different trajectories. Each chamber has its own counterweight mechanism that operates independently, allowing simultaneous deployment of multiple objects without requiring complex coordinated force control. The segmentation isolates the force balance requirements to individual chamber-deployment pairs.
Solution Approach 2:
The patent designs a universal deployment mechanism where the same counterweight-based chamber structure can deploy objects on various trajectories by adjusting the chamber orientation and counterweight position. This multi-functional design allows the system to handle multiple deployment scenarios with a single standardized mechanism, reducing overall system complexity while maintaining high deployment capability.
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 system enables efficient and stable deployment of objects at varying velocities while maintaining the center of mass and rotation harmony, reducing system complexity and potential failure points, and allowing for simultaneous deployment of multiple objects without the need for traditional counterforce systems.
Implementation Method 1
a spring (112) disposed adjacent to the first end (110A). A countermass (114) is coupled to the spring (112) opposite from the first end (110A)... automatically expanding the spring and attached countermass
Implementation Method 2
the housing is selectably rotatable about the longitudinal axis of rotation... the housing is selectively rotated to generate centripetal force
Data Source
AI summary
Provided is a space object deployment system. Specifically, the system in at least one embodiment, includes at least one deployable object. A deployment chamber is paired with each deployable object, each chamber including: a base opposite from the deployable object; and a spring loaded countermass coupled to the base and slidably disposed within the chamber, the deployment chamber at least partially disposed within a rotatable body transverse to the axis of rotation. At least one coupler is paired to each deployable object and adapted to detachably couple the deployable object to the body and constrain the countermass within the chamber. An associated method of use is provided as well.