Spacecraft Optical Tracking via Imaging Device

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Solution Overview

Problem

Existing spacecraft, particularly small satellites like nanosatellites, face challenges in tracking and capturing moving communication partners without increasing their size, as they require complex mechanisms for directivity control, which is impractical for compact designs.

Innovation Solution

Implementing an attitude control system that uses an imaging device to capture and track optical communication signals, allowing the spacecraft to adjust its attitude based on the position of the signal in the image, thereby eliminating the need for additional tracking mechanisms and maintaining a compact size.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a directivity control mirror mechanism is provided for tracking a communication partner, then the spacecraft can capture and track moving communication partners, but the size of the spacecraft increases

Engineering Contradiction:

Improvetracking capabilityVSAvoidspacecraft size

Core Design Contradiction:

ReliabilityVSVolume of moving object

Solution Approach 1:

The patent combines the optical communication signal receiving function and the tracking function into a single imaging device. The imaging device captures both the communication signal and the position information of the communication partner, eliminating the need for a separate directivity control mirror mechanism. This merging allows nanosatellites to perform tracking without adding significant volume.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The imaging device serves multiple functions: it receives optical communication signals, determines the position of communication partners, and provides tracking information for attitude control. This multi-functionality eliminates the need for dedicated tracking mechanisms, enabling compact spacecraft design while maintaining reliable tracking capability.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If a directivity control mirror mechanism is provided for tracking, then the spacecraft can maintain communication with moving partners, but the device complexity increases

Engineering Contradiction:

Improvecommunication stabilityVSAvoidmechanism complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent merges the optical signal detection and position tracking functions into a single imaging device, eliminating the need for complex directivity control mirror mechanisms. This simplification reduces device complexity while maintaining communication stability through integrated functionality.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent replaces the mechanical directivity control mirror system with an optical/electronic solution using an imaging device and attitude control actuators. This substitution eliminates complex mechanical tracking mechanisms while achieving the same communication stability through software-controlled attitude adjustment.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Measurement precision

If the spacecraft uses a narrow laser beam for transmission, then the communication precision is improved, but the difficulty of detecting and measuring the signal increases

Engineering Contradiction:

Improvecommunication precisionVSAvoidsignal detection difficulty

Core Design Contradiction:

Measurement precisionVSDifficulty of detecting and measuring

Solution Approach 1:

The patent uses the imaging device to continuously monitor the position of the communication partner and provides feedback to the attitude control system. This feedback mechanism enables real-time adjustment of the spacecraft's attitude to maintain optimal alignment with narrow laser beams, improving detection capability while maintaining communication precision.

Inventive Principle:

Principle #23Feedback

Solution Approach 2:

The patent replaces mechanical directivity control with an optical imaging and electronic control system. The imaging device detects the position of communication partners using optical methods, and the attitude control actuators adjust the spacecraft orientation based on electronic signals, simplifying the detection of narrow laser beams while maintaining precision.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

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 stable communication with moving partners while preventing an increase in spacecraft size, as the attitude control actuator and imaging device work together to capture and track optical signals effectively, even with low accuracy, using LED or wide-angle laser light for transmission and reception.

Implementation Method 1

an imaging device that receives the optical communication signal from the first spacecraft

Methodology Applied

Scientific EffectPhotoelectric Effect: Photoelectric Effect

Data Source

PatentUS12065269B2Spacecraft, communication method, and communication system

Publication Date: 2024.08.20 THE FOUND FOR GLOBAL HEALTH CARE

AI summary

A disclosed spacecraft is provided with: an attitude control actuator configured to control an attitude of the spacecraft; an imaging device configured to receive an optical communication signal from another spacecraft; and an attitude controller configured to control the attitude control actuator, based on a position of the optical communication signal in an image obtained by the imaging device.