Solar Array Torque Generation for Spacecraft Attitude Control

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Solution Overview

Problem

Current spacecraft attitude control systems face challenges in achieving high precision attitude stabilization and turbulence-free operation, especially in high-altitude orbits, due to limitations in fuel capacity and existing thruster and reaction wheel technologies.

Innovation Solution

A torque generation system utilizing solar array panels, where the electricity generation ratio is controlled by switching shunt switches or altering the thermal emissivity and conductivity between the light receiving and opposite surfaces to generate torque for attitude control, allowing precise control without additional devices.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If thrusters are used for attitude control, then attitude correction capability is improved, but fuel consumption increases and operational lifespan decreases

Engineering Contradiction:

Improveattitude control capabilityVSAvoidoperational lifespan

Core Design Contradiction:

ReliabilityVSDuration of action of moving object

Solution Approach 1:

The patent replaces the mechanical thruster system with a thermal radiation pressure system. By controlling the thermal emissivity of solar array panel surfaces, the spacecraft generates control forces through differential thermal radiation pressure, eliminating the need for propellant-based thrusters and enabling indefinite operational lifespan.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the thermal emissivity parameter of the solar array panel surfaces to control attitude. By dynamically adjusting the emissivity of different surface regions, the system generates controlled thermal radiation pressure differences that produce the necessary torque for attitude correction without consuming fuel.

Inventive Principle:

Principle #35Parameter changes

2Reliability

If reaction wheels are used for attitude control, then attitude stabilization is improved, but turbulence is generated

Engineering Contradiction:

Improveattitude stabilizationVSAvoidturbulence

Core Design Contradiction:

ReliabilityVSObject-generated harmful factors

Solution Approach 1:

The patent replaces the rotating mechanical reaction wheel system with a static thermal radiation pressure system. By controlling thermal emission from solar array surfaces, the system generates control torques without any moving parts, thereby eliminating the turbulence and vibrations that reaction wheels inherently produce.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Measurement precision

If additional control devices are mounted on spacecraft, then control precision is improved, but spacecraft weight increases

Engineering Contradiction:

Improvecontrol precisionVSAvoidspacecraft weight

Core Design Contradiction:

Measurement precisionVSWeight of moving object

Solution Approach 1:

The patent makes the solar array panels multi-functional by enabling them to serve both as power generation surfaces and as attitude control actuators. By controlling the thermal emissivity of the same surfaces that generate electricity, the system achieves precise attitude control without adding separate control devices, thereby avoiding additional weight.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent merges the power generation function and attitude control function into a single integrated system. The solar array panels simultaneously generate electrical power and produce control forces through differential thermal radiation pressure, eliminating the need for separate control hardware and reducing overall spacecraft weight.

Inventive Principle:

Principle #5Merging (Combining)

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 enables high-precision attitude and relative position/velocity control of spacecraft without causing turbulence, using solar array panels integrated into the spacecraft, thereby extending lifespan and reducing weight.

Implementation Method 1

a torque generation system, an attitude control system for a spacecraft, and a relative position and velocity control system for a spacecraft, which use a thermal radiation pressure generated from a solar array panel

Methodology Applied

Scientific EffectThermal radiation pressure: Radiation Pressure

Implementation Method 2

control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque

Methodology Applied

Scientific EffectThermal radiation: Thermal Radiation

Data Source

PatentUS10577132B2Torque generation system, attitude control system for spacecraft, and relative position and velocity control system for spacecraft

Publication Date: 2020.03.03 JAPAN AEROSPACE EXPLORATION AGENCY

AI summary

A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.