Integrated Flash LADAR System for Space Navigation
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Solution Overview
Problem
Current navigation systems for space operations, particularly for rendezvous, docking, and planetary landing, are cumbersome and inefficient due to the need for multiple sensors, which complicates relative navigation and imposes stringent size, weight, and power constraints, limiting operational flexibility and increasing costs.
Innovation Solution
A single, integrated Flash LADAR-based system with a critical algorithm suite operating in real-time, combining data processing hardware and software, a passive camera, and auxiliary components like GPS and IMU, enabling simultaneous execution of Guidance, Navigation, and Control (GNC), Altimetry, Velocimetry, Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and dust penetration functions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple separate sensors are used for navigation functions, then measurement precision and reliability are improved, but device complexity, size, and weight increase
Solution Approach 1:
The patent combines multiple separate navigation sensors (LADAR, passive camera, GPS, IMU) into a single integrated sensor assembly that shares common optical aperture and processing hardware, thereby reducing system complexity while maintaining measurement precision through multi-functional operation
Solution Approach 2:
The integrated sensor assembly performs multiple navigation functions (GNC, Altimetry, Velocimetry, TRN, HDA) simultaneously using shared hardware components, allowing one system to fulfill the roles of multiple separate sensors through software-configurable multi-functionality
2Measurement precision
If multiple separate sensors are used for navigation functions, then measurement precision is improved, but size and weight constraints are worsened
Solution Approach 1:
The patent merges multiple navigation sensors into a single integrated assembly with shared optical aperture and processing hardware, significantly reducing the overall weight compared to using separate sensor systems while maintaining the measurement precision required for space navigation operations
3Reliability
If multiple separate sensors are used for navigation functions, then reliability is improved, but power consumption increases
Solution Approach 1:
The patent combines multiple sensors into a single integrated system with shared processing hardware and power management, reducing total power consumption while maintaining navigation reliability through coordinated multi-functional operation and efficient resource utilization
4Device complexity
If a single integrated Flash LADAR system is used, then device complexity, size, and weight are reduced, but measurement precision may be compromised
Solution Approach 1:
The integrated Flash LADAR system achieves multiple navigation functions (GNC, Altimetry, Velocimetry, TRN, HDA) through software-configurable multi-functionality, maintaining measurement precision by using the same optical aperture and detector array for all functions simultaneously
Solution Approach 2:
The patent uses a 2D detector array to capture spatial information in two dimensions simultaneously, enabling multiple measurement functions (range, velocity, terrain mapping) to be derived from a single integrated measurement, thereby maintaining precision while reducing system complexity
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
This solution significantly reduces payload size, weight, and cost while enhancing operational flexibility and precision, enabling safe and precise planetary landing and space operations by consolidating multiple functions into a single, compact unit.
Implementation Method 1
a light source 228... capable of providing flashes of light
Implementation Method 2
reflected light... received at the detector array
Implementation Method 3
A time of flight 220 for the flash of light to reach the target and for the reflected light to be received at the detector array is determined
Data Source
Figure 1~2
Figure 3A
Figure 3B
AI summary
The present invention pertains in general to a single, integrated flash LADAR system and method. The system includes data processing hardware and software, a passive two-dimensional camera, a three-dimensional camera, a light source, and a common optical path. One or more star trackers can also be included. In addition, auxiliary components, such as an inertial measurement unit and a global positioning system receiver can be included. The system can be closely integrated with a critical algorithm suite that operates in multiple modes, in real-time to enable landing, docking, and navigation functions, such as Guidance, Navigation, and Control (GNC), Altimetry, Velocimetry, Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and dust penetration.