Spacecraft Deployment via Threaded Rod Stacking Mechanism
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current spacecraft deployment systems, such as the EELV-ESPA, face inefficiencies in volume and weight utilization, create convoluted load paths leading to deflections, and lack control over deployment and retrieval of spacecraft, particularly in low Earth orbit missions where standardization and efficient use of space are critical.
Innovation Solution
A system utilizing a baseplate with orthogonal threaded rods and coupling mechanisms that allow for efficient stacking, preloading, and controlled deployment of cylindrical spacecraft, enabling precise control over deployment velocity and facilitating retrieval by using an Orbital Service Module for navigation and maneuvering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If multiple spacecraft are launched using the ESPA adapter system, then multiple payloads can be deployed from a single launch vehicle, but volume efficiency decreases to as low as 50% due to wasted space between vehicles and fairing
Solution Approach 1:
The patent implements a nested configuration where spherical spacecraft are stacked vertically within the cylindrical fairing, with each spacecraft nested within the space defined by the fairing boundaries. This nesting approach maximizes the use of available vertical space while maintaining proper separation between spacecraft, thereby improving volume efficiency compared to the ESPA adapter's side-by-side configuration
Solution Approach 2:
The patent transitions from the ESPA adapter's horizontal side-by-side arrangement to a vertical stacking configuration. By utilizing the vertical dimension more effectively and arranging spacecraft along the launch vehicle's longitudinal axis, the system achieves better space utilization within the cylindrical fairing volume
2Quantity of substance
If the ESPA adapter is used to support multiple spacecraft, then multiple payloads can be carried, but mass efficiency rarely exceeds 50% due to the weight of the adapter and fairing
Solution Approach 1:
The patent extracts and eliminates the heavy ESPA adapter component entirely, replacing it with a direct mounting system where spherical spacecraft are attached to the fairing structure using lighter attachment mechanisms. This removal of the intermediate adapter structure significantly reduces the overhead mass, improving mass efficiency
Solution Approach 2:
Instead of using a central adapter structure to which spacecraft are attached (ESPA approach), the patent inverts the architecture by having spacecraft directly mounted to the fairing structure. This inversion eliminates the need for the heavy adapter and its support infrastructure, thereby reducing overall system mass
3Quantity of substance
If the ESPA adapter architecture is used, then multiple spacecraft can be launched, but convoluted load paths create potentially large deflections that are difficult to prevent without adding substantial mass
Solution Approach 1:
The patent segments the load path into direct, independent vertical load paths from each spacecraft through its attachment points directly to the fairing structure. This segmentation eliminates the convoluted load paths of the ESPA adapter, where loads must travel through multiple intermediate connection points, thereby reducing deflections without requiring additional mass for reinforcement
4Quantity of substance
If the ESPA adapter system is used, then multiple spacecraft can be deployed, but control over deployment is lost as spacecraft tumble away until navigation systems direct them to their proper station
Solution Approach 1:
The patent implements preliminary action by providing each spacecraft with predetermined deployment characteristics, including pre-configured deployment velocities and orientation controls. This allows spacecraft to be deployed in a controlled manner with initial conditions already set, eliminating the uncontrolled tumbling phase that occurs with the ESPA adapter system
Data Source
AI summary
A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.