Hybrid Lunar Sensor for Cislunar and Surface Monitoring
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current systems require distinct instruments and platforms to monitor the cislunar space domain and lunar surface domain effectively, due to differing requirements for object detection and imaging, which complicates continuous and complete monitoring.
Innovation Solution
An integrated hybrid sensor system with electro-optic capabilities, capable of operating in both full frame and time delay integration modes, is deployed on a pair of spacecraft in high eccentricity orbits phased 180 degrees apart, allowing for continuous monitoring of the cislunar space domain and frequent access to the lunar surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If distinct instruments are used for cislunar space domain awareness and lunar surface domain awareness, then each domain can be monitored with optimized instrument capabilities, but system complexity increases and continuous monitoring becomes difficult
Solution Approach 1:
The patent implements a hybrid sensor that can operate in multiple modes (full-frame mode for space domain awareness and time-delay integration mode for lunar surface domain awareness) using a single instrument design. This multi-functional approach allows one sensor to replace what would traditionally require two separate specialized sensors, thereby reducing system complexity while maintaining the ability to effectively monitor both domains with optimized capabilities for each
2Device complexity
If a single hybrid sensor is used for both cislunar space and lunar surface monitoring, then device complexity is reduced, but the ability to simultaneously optimize for both domains' specific requirements may be compromised
Solution Approach 1:
The hybrid sensor employs dynamic operational modes that can be switched based on the observation target. The sensor dynamically transitions between full-frame mode (with all pixels operating simultaneously for space domain) and time-delay integration mode (with selective pixel rows for lunar surface), allowing the system to optimize performance for the current operational requirement while using a single unified sensor platform
3Duration of action of stationary object
If spacecraft are positioned in high eccentricity orbits phased 180 degrees apart, then continuous monitoring of cislunar space domain is achieved, but orbital complexity and positioning requirements increase
Solution Approach 1:
The patent utilizes the specific local conditions provided by high eccentricity orbits, where the spacecraft spends most of its orbital period at high altitude (providing continuous cislunar space domain coverage) and periodically passes through low altitude regions (enabling lunar surface domain awareness). By phasing two spacecraft 180 degrees apart, the system ensures that at least one spacecraft is continuously positioned to monitor the cislunar space domain, achieving prolonged duration of action through exploitation of orbital mechanics rather than complex active control
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
Enables continuous or nearly continuous monitoring of the cislunar space domain and frequent access to the lunar surface with a single instrument design, optimizing lighting and geometric conditions for both domains, thereby providing comprehensive space and surface domain awareness.
Implementation Method 1
all or most of the pixels are operated to convert light collected during a common exposure period, and to convert the collected light into an electrical charge
Data Source
AI summary
Systems and methods for obtaining images of a lunar surface and cislunar space using a hybrid telescope are provided. One hybrid telescope is carried by each of two spacecraft. Each spacecraft is in an elliptical orbit about the Moon. The periapsides of the spacecraft orbits are 180° apart from one another. In addition, the spacecraft can be phased 180° apart from one another to enable an offset in access times of each telescope to the cislunar and surface domains respectively. The image sensors associated with the telescopes can include a staring mode for collecting images from cislunar space, and a scanning mode for collecting images from the lunar surface.