Equatorial Radar Stare Mode for LILO Object Detection
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Solution Overview
Problem
Current Space Situational Awareness (SSA) systems face challenges in accurately detecting and tracking low inclination, low orbiting objects due to limited data acquisition, precision orbit parameter issues, and the need for comprehensive space searches, which are costly and complex.
Innovation Solution
A system and method utilizing an equatorial radar system with specialized hardware and algorithms, optimized for horizon pointing, enabling detection and orbit determination of Earth orbiting objects with a high discovery rate, particularly for small debris in Low Inclination Low Orbit (LILO) orbits, by maximizing detection in a focused angular region centered on the equatorial plane.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If ground-based radar systems conduct comprehensive space searches to detect all orbiting objects, then detection coverage is improved, but system complexity and cost increase
Solution Approach 1:
The patent applies local quality by concentrating radar resources on specific high-risk orbital regions (Low Inclination Low Orbit) rather than uniformly searching all space. The radar system optimizes its beam patterns and scanning strategies to focus on LILO zones where debris concentration is highest, achieving reliable detection coverage for critical areas while reducing overall system complexity and operational costs.
2Measurement precision
If surveillance systems use large aperture sensors to improve sensitivity, then detection capability is improved, but field of view narrows and search space increases
Solution Approach 1:
The patent resolves this contradiction by transitioning from two-dimensional sky surveys to three-dimensional orbital zone monitoring. The radar system uses multiple elevation angles and azimuth positions to create volumetric coverage of LILO regions. This dimensional approach allows the use of large aperture sensors with narrow beams to achieve comprehensive coverage through spatial diversity rather than requiring each sensor to have a wide field of view.
3Ease of manufacture
If ground detection systems are positioned away from the equator for operational reasons, then system deployment is simplified, but detection of low inclination objects deteriorates
Solution Approach 1:
The patent applies dynamics by implementing movable and reconfigurable radar systems that can dynamically adjust their positioning and beam directions. Rather than requiring fixed equatorial locations, the system uses multiple ground-based radars that can electronically steer beams and physically reposition to optimize LILO detection. This dynamic approach maintains detection accuracy while allowing flexible deployment at non-equatorial locations.
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 approach enhances detection accuracy and efficiency, overcoming the 'Too Short Arc' issue by keeping objects within the detection beam for a longer duration, allowing for precise orbit parameter determination and 24/7 operation, while reducing search dimensions and costs.
Implementation Method 1
The at least one first antenna is configured to point in a stare mode to broadcast a first detection signal... receive a second detection signal, the second detection signal comprising at least one return signal created by the first detection signal reflecting off of an Earth orbiting object
Implementation Method 2
at least one return signal created by the first detection signal reflecting off of an Earth orbiting object
Implementation Method 3
post-processing of the second detection signal is applied to determine an Angle of Arrival... determine a range and a range rate
Data Source
AI summary
A system for detection and orbit determination of Earth orbiting objects includes a first plurality of sensors including at least one first antenna. The at least one first antenna is configured to point in a stare mode to broadcast a first detection signal at an angular region centered on an equatorial plane to maximize detection of orbiting objects regardless of altitude, grade, or inclination. The first antenna may be configured to stare at a low inclination angle, and may be configured to stare at one of due east and due west along the equator.