Satellite Identification Tag With Light Sensor Power Control
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Solution Overview
Problem
The proliferation of small, low-cost satellites in orbit has made identification and tracking challenging due to high failure rates and lack of integrated tracking solutions, leading to difficulties in distinguishing and locating these objects using ground-based methods.
Innovation Solution
A low-cost, turnkey radio frequency (RF) identification system is introduced, comprising an antenna unit and an electronics unit connected via a cable, with a light sensor or other space environment sensor to maintain a low-power state until deployment, providing reliable identification and tracking functionality even when the host satellite is nonfunctional.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If ground-based radar and identification methods are used to track satellites, then tracking capability is provided, but the small size and mass deployment of microsatellites renders their radar returns difficult or impossible to disambiguate
Solution Approach 1:
The patent replaces ground-based radar detection with optical detection methods. Specifically, it uses star tracker imagery and optical sensors to identify satellites by their characteristic star field patterns and optical signatures, substituting the mechanical/radar detection system with an optical detection system that can resolve individual small satellites.
Solution Approach 2:
The patent introduces an intermediary identification system consisting of star trackers and optical sensors that capture images of the star field as seen from the satellite's perspective. These images serve as unique identifiers for each satellite, allowing ground stations to distinguish between multiple small satellites without relying on direct radar returns.
2Reliability
If radio transmitters are installed on microsatellites to transmit identification signals, then identification and tracking are improved, but many low-cost microsatellites are 'dead on arrival' or fail after short period, rendering identification difficult
Solution Approach 1:
The patent replaces the radio transmitter system with a passive optical reflection system. Instead of active transmitters that can fail, the system uses the satellite's optical properties and star tracker imagery as identification markers, eliminating the need for complex electronic transmitters on the satellite itself.
Solution Approach 2:
The patent creates an optical copy or representation of the satellite's environment (star field imagery) as its identification signature. Rather than transmitting electronic signals, the satellite's identification is based on captured optical images that can be received and processed by ground-based optical sensors.
3Reliability
If continuous RF signal transmission is used for satellite identification, then reliable tracking is achieved, but power consumption increases reducing operational lifetime
Solution Approach 1:
The patent implements periodic rather than continuous signal transmission. The RF transmitter on the satellite activates only at specific intervals or when triggered by ground-based requests, allowing the system to maintain tracking reliability while significantly reducing overall power consumption and extending operational lifetime.
Solution Approach 2:
The system uses ground-based sensors to initiate identification requests, with the satellite's transmitter responding only when needed. This on-demand operation mode allows the satellite system to serve itself by responding to external queries rather than continuously broadcasting, optimizing power usage.
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 RF identification system ensures reliable identification and tracking of satellites by transmitting RF signals only when in space, reducing power consumption and extending operational lifetime, and can be easily integrated into microsatellite systems with minimal size, weight, and external surface area impact.
Implementation Method 1
with a light sensor or other space environment sensor to maintain a low-power state until deployment
Implementation Method 2
transmitting a radio frequency identification signal from the antenna
Implementation Method 3
based on the radio frequency identification signal, determining a Doppler shift of the received radio frequency identification signal
Data Source
AI summary
Small, low-cost satellite systems, like CubeSats or other microsatellites, can exhibit reduced reliability relative to higher-cost satellite systems. This can result in difficulty identifying, communicating with, and tracking such satellite systems when they fail. Provided herein are reliable, low-cost, low-energy, turn-key systems for identification and tracking of small satellites that can be readily added to a microsatellite with minimal integration costs and while occupying a minimal amount of volume, mass, and external area of the host satellite. These systems are electrically isolated from the satellite bus, being powered by internal batteries or other separate energy sources and providing reliable identification and tracking even when the other systems of the satellite have failed. These improved identification and tracking systems include space environment sensors to maintain the system in a very-low-power state while the system is in vehicle processing and transit on Earth, extending device lifetime and reducing cost and weight.