Satellite Stacking Pillars With Pivot Locks for Single-Point Release
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Solution Overview
Problem
Existing satellite retention systems on launch vehicles rely on tie rods and individual separation systems, which are cumbersome and require complex coordination for release.
Innovation Solution
A system featuring pivotable mounting posts within stacking pillars, biased to an unlocked position, and a motor-operated retention mechanism to apply tension, allowing secure stacking and seamless release of satellites using a single mechanism.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If tie rods and individual separation systems are used for satellite retention, then satellites can be securely retained on the launch vehicle, but the system complexity and coordination requirements increase
Solution Approach 1:
The patent combines the retention and separation functions into a single integrated mechanism. The stacking pillars with engagement features on adjacent satellites work together with a single actuated mechanism to provide both secure retention during launch and automatic separation upon actuation, eliminating the need for separate tie rods and individual separation systems for each satellite pair.
Solution Approach 2:
The stacking pillar structure serves multiple functions: it provides mechanical engagement for retention, enables separation when actuated, and works universally across all satellites in the stack through standardized engagement features. This multi-functional design reduces overall system complexity while maintaining reliability.
2Ease of operation
If individual separation systems are used for each satellite pair, then each satellite can be separated independently, but the coordination and operational complexity increase
Solution Approach 1:
Multiple satellites share a common separation mechanism actuated from a single location. When the actuation mechanism is triggered, all engaged satellites separate simultaneously through the interconnected stacking pillar engagement features, eliminating the need for individual separation systems and complex coordination protocols.
Solution Approach 2:
The separation function is segmented into modular engagement features on each stacking pillar that can independently engage and disengage while being part of a unified system. This allows individual satellite-pair engagement variability while maintaining system-wide separation through a single actuation event.
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
Enables secure stacking and efficient release of satellites with reduced complexity, allowing for scalable and flexible satellite arrangements without the need for additional tie rods or complex separation systems.
Implementation Method 1
wherein the mounting post is spring-biased to the unlocked position
Implementation Method 2
a retention mechanism, wherein the retention mechanism is configured to apply a retention force to the mounting post of one of the plurality of space vehicles, and wherein the retention force is configured to act against the spring-biasing so as to retain the mounting post of the one of the plurality of space vehicles in the locked position
Data Source
AI summary
A space vehicle includes a body; a stacking pillar coupled to an exterior of the body and defining a longitudinal axis, wherein the stacking pillar is configured to be removably coupled to a stacking pillar of an adjacent space vehicle; and an engagement mechanism including: a pivot point within the stacking pillar defining a pivot axis perpendicular to the longitudinal axis; and a mounting post positioned within the stacking pillar and pivotably engaged with the pivot point so as to be pivotable about the pivot axis between a locked position and an unlocked position, wherein the mounting post is spring-biased to the unlocked position, and wherein the mounting post is configured to restrain the space vehicle from movement away from the adjacent space vehicle when the mounting post is positioned in the locked position and a mounting post of the adjacent space vehicle is positioned in a locked position.