Satellite Structural Element Deployment and Aiming Mechanism
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Solution Overview
Problem
Current satellite deployment systems require separate motors and mechanisms for deployment and aiming phases, leading to increased space and weight requirements, as well as immobilization of the pulley mechanism after deployment, which is inefficient.
Innovation Solution
A locking/unlocking system that allows a single motor to switch between deployment and aiming modes by altering the coupling law of the structural elements, using a shared pulley and cable system with ratchets and spigots to unlock or lock articulations as needed, enabling the same motor to handle both phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate motors and mechanisms are used for deployment and aiming phases, then reliability is improved, but weight and device complexity increase
Solution Approach 1:
The patent implements a universal motor and pulley system that performs both deployment and aiming functions. The same motor (21) drives pulleys (22, 23, 24, 25) during deployment, and the same motor pivots the entire structure during aiming. This multi-functional approach eliminates the need for separate motors, reducing satellite weight while maintaining operational reliability through a consolidated drive system.
Solution Approach 2:
The patent merges the deployment mechanism and aiming mechanism into a single integrated system. The pulley-cable assembly (22-25, 223-245) serves dual purposes: transferring forces during deployment and enabling pivoting during aiming. By combining these functions, the patent reduces the number of components, decreases weight, and simplifies the overall system architecture.
2Reliability
If separate motors and mechanisms are used for deployment and aiming phases, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent implements a universal motor and pulley system that performs both deployment and aiming functions. The same motor (21) drives pulleys (22, 23, 24, 25) during deployment, and the same motor pivots the entire structure during aiming. This multi-functional approach eliminates the need for separate motors, reducing satellite weight while maintaining operational reliability through a consolidated drive system.
Solution Approach 2:
The patent merges the deployment mechanism and aiming mechanism into a single integrated system. The pulley-cable assembly (22-25, 223-245) serves dual purposes: transferring forces during deployment and enabling pivoting during aiming. By combining these functions, the patent reduces the number of components, decreases weight, and simplifies the overall system architecture.
3Stability of the object's composition
If the pulley mechanism is immobilized after deployment, then deployment stability is improved, but aiming flexibility is worsened
Solution Approach 1:
The patent implements a dynamic system where the coupling between the motor and pulleys can be reconfigured between two phases. During deployment, the motor couples to pulleys to provide coordinated motion. During aiming, the motor disconnects from the pulley mechanism and directly pivots the structure. This dynamic reconfiguration allows the system to transition from a stable deployed state to a flexible aiming mode, resolving the contradiction between stability and adaptability.
Solution Approach 2:
The patent segments the operational phases into deployment and aiming, with distinct mechanical configurations for each. The locking/unlocking system separates the pulley mechanism from the pivoting function, allowing independent optimization of each phase. During deployment, all components work together in a coupled system; during aiming, the system segments into a fixed pulley assembly and a movable pivoting structure.
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 solution reduces the need for dual motors and mechanisms, minimizing weight, cost, and complexity while allowing flexible aiming configurations, enhancing the robustness and efficiency of satellite structural element deployment and targeting.
Implementation Method 1
A known coupling system uses pulleys positioned on each of the articulations and cables connecting the pulleys making it possible to transfer the forces between the structural elements at the time of deployment.
Implementation Method 2
In order to lock the pulley (22) to the articulation (4), there are means (61, 64) making it possible to create a blocking action between the pulley (22) and the articulation (4).
Data Source
AI summary
A device for deploying and aiming structural elements designed to be placed in Earth includes at least one locking/unlocking device making it possible to deactivate the first coupling mode and to activate a second coupling mode allowing a portion of the device to be aimed at a target. The device uses: a plurality of structural elements linked together by articulations, the assembly forming an articulated arm linked to a payload via a root section; the articulations having at least one pivoting connection making it possible to have two consecutive structural elements pivot relative to one another; a motor making it possible to activate at least one pivoting connection of an articulation; and a system for coupling the articulations making it possible to link the pivoting of all of the structural elements comprising a first coupling mode.