Launch Lock Assembly for All-Direction Isolator Clearance
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Solution Overview
Problem
Spacecraft isolation systems face limitations in providing sufficient clearance for vibration isolators to effectively dampen vibrations between the payload and spacecraft, as existing launch lock systems restrict the range of motion due to limited clearance.
Innovation Solution
A launch lock system with increased clearance in all directions is designed, featuring a housing assembly with a movable pivot arm subassembly and fastener system that transitions from a locked to a released state, allowing the payload support structure to move freely relative to the spacecraft, thereby enhancing the range of motion for vibration isolators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the launch lock system uses a traditional rigid coupling design, then the structure is simple and easy to manufacture, but the clearance for isolator motion is insufficient
Solution Approach 1:
The launch lock system is divided into separate functional components: a first housing portion coupled to the payload support structure, a second housing portion coupled to the spacecraft, and a fastener subassembly that connects them. This segmentation allows each component to be optimized independently, enabling increased clearance while maintaining structural integrity and manageable complexity.
Solution Approach 2:
The system transitions from a static rigid coupling to a dynamic design where the fastener subassembly can move between a first position (providing clearance) and a second position (providing rigid coupling). This dynamic capability allows the system to adapt its characteristics based on operational requirements, resolving the contradiction between clearance and structural rigidity.
2Ease of operation
If the launch lock system provides large clearance for isolator motion, then the isolators can effectively dampen vibrations, but the shock loads during launch may compromise the rigid coupling
Solution Approach 1:
The fastener subassembly is designed to be movable between two positions: a first position that provides large clearance for isolator motion during normal operation, and a second position that provides rigid coupling during launch to withstand shock loads. This dynamic reconfiguration allows the system to optimize its performance characteristics based on the operational phase.
Solution Approach 2:
The system changes its structural parameters by repositioning the fastener subassembly. When moved to the second position, the fastener provides rigid coupling with high strength to withstand launch shock loads. When moved to the first position, the system provides large clearance that enables isolators to effectively dampen vibrations during operational phases.
3Length of moving object
If the fastener subassembly is designed to move between positions, then the clearance is increased for isolator motion, but the mechanism complexity increases
Solution Approach 1:
The movable fastener subassembly is segmented into distinct components including a fastener body, a biasing member, and coupling elements. This segmentation allows each component to perform a specific function, simplifying the overall design and manufacturing while enabling the complex motion required to provide increased clearance in all directions.
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 system provides increased clearance, enabling vibration isolators to effectively dampen vibrations between the payload and spacecraft, protecting sensitive components and reducing shock loads during launch and operation.
Implementation Method 1
a biasing member coupled to the second housing portion that biases against the lock wedge
Implementation Method 2
The lock wedge contact surface is spherical
Data Source
AI summary
A launch lock system includes a first portion rigidly coupled to the second portion in a first state and the first portion movable in all directions relative to the second portion in a second state. The launch lock system includes a fastener subassembly coupled to the second portion, and the fastener subassembly is movable relative to the second portion from a first position to a second position. The launch lock system includes at least one pivot arm subassembly having a pivot arm movable between a first position and a second position. The pivot arm is coupled to the first portion in the first position. In the first state, the pivot arm is in the first position and cooperates with the fastener subassembly in the first position, and in the second state, the pivot arm is uncoupled from the first portion and the fastener subassembly.