Rotatable Stacked Spacecraft Inter-Spacecraft Coupling
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Solution Overview
Problem
In stacked spacecraft configurations, shadowing of solar arrays by one spacecraft on another limits electrical power generation during orbit transfer maneuvers, as the orientation of solar arrays is constrained by the thrust vector and launch configuration.
Innovation Solution
An inter-spacecraft coupling arrangement that allows selective rotation of one spacecraft with respect to another about a axis parallel to the thrust vector, reducing or preventing shadowing by switching between launch and orbit-raising configurations using mechanisms like V-band clamps and motorized actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If spacecraft are configured in a stacked launch configuration, then multiple spacecraft can be launched together on a single launch vehicle, but shadowing of solar arrays by one spacecraft on another limits electrical power generation
Solution Approach 1:
The inter-spacecraft coupling arrangement allows dynamic rotation of one spacecraft with respect to another about an axis parallel to the thrust vector. This rotational degree of freedom enables the solar arrays to be oriented away from shadowing by adjacent spacecraft during orbit transfer maneuvers, thereby increasing electrical power generation while maintaining the stacked configuration benefits.
2Productivity
If spacecraft are fixed in launch configuration, then structural stability is maintained, but solar array orientation cannot be optimized for power generation during orbit transfer
Solution Approach 1:
The coupling arrangement transitions from a fixed launch configuration to a dynamic on-orbit configuration where rotation about the thrust vector axis is permitted. This controlled introduction of a single rotational degree of freedom balances the need for structural stability during launch with the need for solar array orientation optimization during orbit transfer, avoiding excessive complexity while achieving the power generation goal.
3Productivity
If spacecraft rotate with respect to each other during orbit transfer, then solar array shadowing is reduced, but control precision during maneuver is compromised
Solution Approach 1:
The rotational movement is segmented into discrete, controlled increments about the thrust vector axis rather than continuous free rotation. This segmented approach allows the spacecraft to achieve shadow-free solar array orientation while maintaining sufficient alignment precision with the thrust vector for effective orbit transfer maneuvers, balancing power generation needs with maneuver control requirements.
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
Enhances electrical power generation by ensuring unshadowed sunlight for solar arrays during orbit transfer, allowing for efficient thruster operation and extended mission duration by optimizing solar array orientation relative to the sun vector.
Implementation Method 1
enhances electrical power generation by ensuring unshadowed sunlight for solar arrays
Implementation Method 2
a thruster delivering thrust along a thrust vector configured to execute an orbit transfer maneuver
Data Source
AI summary
A system includes at least two spacecraft disposed together for launch by a launch vehicle. In a launch configuration, a second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement (ISCA). The system is configured to be deployed following injection into a first orbit by the launch vehicle, while the second spacecraft is mechanically coupled with the first spacecraft. The first spacecraft includes a thruster configured to execute an orbit transfer maneuver from the first orbit to a second orbit, the thruster delivering thrust along a thrust vector. In an on-orbit configuration, the ISCA is switchable between a first mode that permits rotation of the first spacecraft with respect to the second spacecraft about a first axis of rotation that is approximately parallel with the thrust vector and a second mode that prevents rotation of the first spacecraft with respect to the second spacecraft.