Non-Co-Orbital Satellite Imaging Along Apparent Motion
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Solution Overview
Problem
Existing imaging technologies face challenges in capturing high-resolution images of non-earth objects in space due to orbital mechanics constraints, conjunction opportunities, and factors like excessive relative angular rates, solar interference, and background illumination, which affect image quality.
Innovation Solution
A method involving identifying orbital directions, determining a line of apparent motion, assessing an encounter window, and aligning sensors to capture high-resolution images of non-earth objects by aligning sensors along this motion, considering factors like relative distance, velocity, and solar position to ensure optimal imaging conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If imaging is performed between non-co-orbital satellites with different orbital directions, then high-resolution images of non-earth objects can be captured, but image quality deteriorates due to excessive relative angular rates and orbital mechanics constraints
Solution Approach 1:
The system performs preliminary identification of orbital directions for both the first and second satellites, determines the line of apparent motion between them, and identifies optimal encounter windows before actual imaging occurs. This advance preparation allows the system to select imaging opportunities where relative angular rates are minimized, ensuring both high resolution and image quality.
Solution Approach 2:
The system dynamically adjusts imaging parameters based on real-time orbital mechanics calculations. By continuously monitoring the relative motion between non-co-orbital satellites and adapting the imaging timing to encounter windows, the system optimizes image quality while maintaining the ability to capture high-resolution data of non-earth objects.
2Measurement precision
If sensors are aligned along the line of apparent motion to capture high-resolution images, then measurement precision improves, but the system complexity increases due to orbital direction identification and encounter window assessment
Solution Approach 1:
The system integrates multiple functions into a unified imaging platform: orbital direction identification, line of apparent motion determination, encounter window assessment, and sensor alignment all occur within the same satellite imaging system. This multi-functionality reduces overall system complexity by eliminating the need for separate specialized systems for each function.
Solution Approach 2:
The system employs feedback mechanisms where orbital parameters and relative motion data continuously inform sensor alignment decisions. By using real-time data from orbital direction identification and encounter window assessment to dynamically adjust sensor orientation, the system achieves high measurement precision without requiring overly complex predetermined mechanical alignment systems.
3Reliability
If imaging occurs during optimal encounter windows to minimize smear and maintain image quality, then image reliability improves, but the productivity decreases due to limited imaging opportunities
Solution Approach 1:
The system performs advance identification of multiple encounter windows based on orbital mechanics calculations, allowing it to plan and execute multiple imaging opportunities in advance. By pre-determining when optimal imaging conditions will occur, the system maximizes productivity within the constraints of reliable imaging windows.
Solution Approach 2:
The system maintains continuous monitoring of orbital parameters and relative motion to identify successive encounter windows. Rather than treating imaging opportunities as isolated events, the system continuously assesses conditions to capture multiple images during different encounter windows, thereby improving overall productivity while maintaining image quality through reliable timing.
Data Source
AI summary
Examples of the present disclosure include a method of collecting a non-earth image of an object in space, the method including identifying a first orbital direction of the object in space, identifying a second orbital direction of an image capture device, determining a line of apparent motion between the object in space and the image capture device based on the identified first orbital direction and the identified second orbital direction, determining a residual motion across the image capture device, assessing an encounter window between the image capture device and the object in space, aligning sensors of the image capture device along the line of apparent motion, and when the object in space and the image capture device are within the encounter window, scanning at least the object in space by the image capture device along the line of apparent motion.