Spacecraft Collision Avoidance Using Relative-Velocity Plane Targeting
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Solution Overview
Problem
Traditional spacecraft collision avoidance (COLA) methods lead to unnecessary orbit modifications and increased operational costs due to early maneuvers, especially in crowded low-earth orbits, and often result in orbit-state uncertainties and cross-system coordination issues.
Innovation Solution
A system and method for determining a two-dimensional plane orthogonal to the relative velocity between spacecraft, identifying a boundary on this plane that reduces collision probability, and selecting optimal maneuver points based on user-defined parameters to minimize impact on mission objectives.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If COLA maneuvers are executed early in advance of POCA, then collision avoidance is achieved, but orbit-state uncertainty increases and unnecessary maneuvers are triggered
Solution Approach 1:
The system performs preliminary collision risk assessment and identifies potential COLA maneuvers in advance, but delays actual maneuver execution until closer to POCA when orbit uncertainty is reduced. This allows early preparation while avoiding premature maneuvers that would amplify uncertainty.
Solution Approach 2:
The system dynamically adjusts the timing of COLA maneuver execution based on real-time orbit uncertainty assessment. As POCA approaches and orbit covariance volumes shrink, the system transitions from early planning to later execution, optimizing the balance between collision avoidance and uncertainty management.
2Reliability
If COLA maneuvers are performed early, then collision probability is reduced, but vehicle life and performance are degraded due to unnecessary maneuvers
Solution Approach 1:
The system continuously monitors orbit uncertainty and collision probability in real-time, using feedback to determine whether early COLA maneuvers are actually necessary. Many early-predicted COLA situations are found to resolve naturally as uncertainty shrinks, allowing the system to avoid unnecessary maneuvers that would degrade vehicle life.
Solution Approach 2:
The system changes the timing parameter of COLA maneuver execution from early to late based on evolving orbit uncertainty conditions. This parameter adjustment allows the same collision avoidance function to be achieved with fewer maneuvers, preserving vehicle life and performance.
3Reliability
If early COLA maneuvers are executed, then collision avoidance is achieved, but cross-system coordination problems increase
Solution Approach 1:
The system performs preliminary identification of potential COLA maneuvers and shares this information with other space systems in advance, but delays actual maneuver execution until closer to POCA. This allows other systems to prepare for potential coordination needs without requiring complex real-time coordination during the maneuver itself.
4Reliability
If traditional early COLA methods are used, then collision avoidance is achieved, but operational costs increase
Solution Approach 1:
The system uses feedback from real-time orbit uncertainty assessment to determine whether early COLA maneuvers are necessary. This feedback mechanism reveals that many early-predicted collisions resolve naturally, allowing the system to avoid expensive maneuvers and reduce operational costs while maintaining collision avoidance effectiveness.
Data Source
AI summary
Systems and methods include determining a collision probability between a first spacecraft and a second spacecraft; responsive to a determination that the collision probability exceeds a threshold, identifying a plane that is orthogonal to a relative velocity between the first spacecraft and the second spacecraft; determining a boundary on the plane that, when intersected by the first spacecraft, reduces the collision probability to a threshold level; selecting a first test point along the boundary and a second test point along the boundary; determining a first cost associated with maneuvering the first spacecraft towards the first test point and a second cost associated with maneuvering the first spacecraft towards the second test point, the first cost and the second cost based on one or more user-defined parameters; and maneuvering the first spacecraft toward a target point along the boundary that is determined based on the first cost and the second cost.