Dual Spacecraft Interconnection Using Pneumatic and Spring Forces
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Solution Overview
Problem
The high costs associated with launching spacecraft into orbit are exacerbated by the mass of launch vehicles and fuel, prompting the need for efficient interconnection systems for dual manifested spacecraft to reduce overall mass and launch costs, while ensuring secure coupling and demating mechanisms.
Innovation Solution
Systems and methods for interconnecting dual manifested spacecraft utilize different motive forces, such as pneumatic pressure and spring force, to securely couple and restrict demating, employing coupling mechanisms with pins and trigger mechanisms to facilitate mating and secure positioning, with the option to remain ground-based to reduce launch vehicle mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If multiple spacecraft are coupled together for a single launch, then launch costs are reduced by lowering overall mass, but the interconnection between spacecraft must be significantly more secure to handle the forces involved
Solution Approach 1:
The coupling system is divided into separate functional components: pins for load bearing, keyed restrictions for rotational control, and spring-loaded locking mechanisms. This segmentation allows each component to specialize in a specific aspect of coupling security while keeping individual component masses low.
Solution Approach 2:
The coupling mechanism transitions from a static design to a dynamic one where pins are selectively translated into aligned bores, and spring force dynamically adjusts to maintain coupling security. The keyed pins can rotate to different positions (locked or unlocked) to adapt to different operational requirements.
2Reliability
If a secure coupling mechanism is designed with multiple pins and locking features, then interconnection reliability is improved, but the mass of the interconnection components increases
Solution Approach 1:
Pneumatic pressure is utilized to translate pins into aligned bores for coupling and to operate spring-loaded locking mechanisms. This allows a relatively light pneumatic system to achieve the coupling function that would otherwise require heavier mechanical actuators or motors.
Solution Approach 2:
The system changes the state of pins from retracted to extended positions, and utilizes spring force parameters to maintain coupling. By changing the positional parameter of pins and utilizing elastic potential energy in springs, the system achieves secure coupling without heavy mechanical structures.
3Device complexity
If pins are configured to bear vertical load but not lateral load, then the coupling mechanism is simplified and mass is reduced, but the pins must be selectively translated and keyed to restrict rotation
Solution Approach 1:
The keyed pins are configured to automatically restrict their own rotation through the key geometry, and spring force automatically maintains coupling pressure. The system serves itself by using the inherent properties of the keyed pin design and spring elasticity rather than requiring external control mechanisms for each function.
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
These systems effectively reduce launch costs by minimizing the mass of the interconnection components and ensuring secure coupling and demating of spacecraft, while allowing for efficient transition between coupled and uncoupled configurations, thereby optimizing the launch process.
Implementation Method 1
Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft
Implementation Method 2
utilize spring force to restrict demating of the second spacecraft from the first spacecraft
Data Source
AI summary
Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.