Precision Pointing Interface for Spacecraft Payloads
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Solution Overview
Problem
The attitude control system of spacecrafts introduces disturbances that affect instrument pointing accuracy, and existing solutions to mitigate these disturbances, such as improving the spacecraft's attitude control or using a centralized metrology system, are costly and complex.
Innovation Solution
A localized metrology and correction system with a built-in star tracker and an active-passive disturbance rejection system, comprising a series configuration of spring-damper systems and actuators, is implemented to reduce high and low-frequency vibrations and maintain precise instrument pointing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a centralized metrology system is used to correct for instrument interface disturbance, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The patent divides the disturbance correction function into localized segments at each instrument interface rather than using a single centralized system. Each interface has its own vibration isolation system with sensors and actuators that independently measure and correct disturbances, reducing overall system complexity while maintaining measurement precision.
Solution Approach 2:
The patent implements local vibration isolation systems at each instrument interface with tailored spring-damper configurations and actuators specific to the local disturbance characteristics. This localized approach provides precise measurement and correction at each interface without the complexity of a unified centralized metrology system spanning the entire spacecraft.
2Stability of the object's composition
If the spacecraft attitude control system is improved to reduce disturbances, then stability is improved, but device complexity increases
Solution Approach 1:
The patent introduces vibration isolation systems as intermediary elements between the spacecraft structure and the instruments. These intermediaries include spring-damper systems and active actuators that filter and reject vibrations before they reach the instruments, allowing the use of standard spacecraft attitude control systems without requiring expensive high-precision control systems.
3Stability of the object's composition
If deeper or more stable trusses are used to mitigate disturbance, then stability is improved, but weight increases
Solution Approach 1:
The patent replaces purely mechanical solutions (deeper, heavier trusses) with a hybrid approach combining passive spring-damper systems and active actuators. This substitution allows standard-weight trusses to achieve the same disturbance mitigation performance through active vibration rejection, significantly reducing the weight penalty associated with mechanically stiffening the truss structure.
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
The solution provides a cost-effective and precise method for maintaining instrument pointing accuracy by reducing disturbances from the spacecraft, enabling efficient assembly and upgrade of payloads on spacecrafts, suitable for both robotic and human operations.
Implementation Method 1
a passive vibration isolation system including a spring-damper system configured to reduce high frequency disturbances from the host
Implementation Method 2
an actuator configured to reduce low frequency disturbances from the host
Implementation Method 3
The disclosed precision pointing interfaces comprise a built-in star tracker and a combination of active-passive disturbance rejection system
Data Source
AI summary
Pointing interfaces that can be used to assemble/disassemble instruments/payloads from a spacecraft/host are disclosed. The disclosed interfaces provide structural, communications, power, and fluid connections (for thermal control). Such interfaces also provide active and passive vibration isolation capability for precision pointing. They can further act as an interface to the launch vehicle for secondary delivery of the instrument/payload to the spacecraft.