Variable Reflection Glass Panels for Satellite Attitude Control
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Solution Overview
Problem
Current satellite attitude and orbital control systems face challenges with transient attitude disturbances and fuel consumption, particularly in long-duration operations, and require precise control without contaminating sensitive instruments.
Innovation Solution
The use of electrically controllable variable reflection glass panels, comprising two thin outer layers of glass and a middle layer of liquid crystal droplets embedded in a polymer, with a reflective film on the rear surface, to modulate solar radiation pressure for attitude and orbital control by varying reflectivity in response to error signals from sensors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If chemical or electrical thrusters are used for satellite attitude control, then attitude control is achieved, but transient attitude disturbances are created and thruster fuel is consumed
Solution Approach 1:
The patent replaces mechanical thruster systems with an optical control system using variable reflectivity panels. These panels modulate solar radiation pressure to produce attitude control torques without consuming propellant, substituting a mechanical propulsion system with an optical-mechanical system that uses sunlight as the control medium.
Solution Approach 2:
The patent changes the optical parameter (reflectivity) of the panels to control the satellite attitude. By varying the reflectivity of the panels facing the sun, the system modulates the solar radiation pressure to generate the required control torques, replacing the chemical parameter changes (fuel consumption) of traditional thrusters.
2Reliability
If chemical or electrical thrusters are used for satellite orbital control, then orbital adjustments are achieved, but greater fuel and power are required over satellite lifetime
Solution Approach 1:
The patent replaces electrical thruster systems with variable reflectivity panels that use solar radiation pressure for orbital control. This substitution eliminates the need for electrical power to drive thrusters and removes propellant consumption, using instead the free energy of sunlight to provide continuous orbital adjustment capability.
Solution Approach 2:
The system uses solar radiation, a free and abundant resource, to provide orbital control without consuming the satellite's limited power and propellant resources. The panels passively intercept and reflect sunlight to generate control forces, making the system self-sufficient for orbital maintenance over the satellite lifetime.
3Reliability
If momentum wheels are used for attitude control, then attitude control is improved, but periodic thruster actuation is required to keep angular momentum within limits
Solution Approach 1:
The patent replaces the momentum wheel system with variable reflectivity panels that directly generate attitude control torques through solar radiation pressure modulation. This eliminates the need for momentum storage devices and the associated periodic desaturation maneuvers that consume fuel.
Solution Approach 2:
The patent extracts and eliminates the momentum storage function from the attitude control system by using direct solar radiation pressure modulation. This removes the requirement for periodic thruster actuation to manage angular momentum buildup, as the panels can provide continuous torque without accumulating momentum.
4Reliability
If traditional control systems are used, then attitude and orbital control are achieved, but transient disturbances contaminate sensitive instruments
Solution Approach 1:
The patent replaces mechanical thruster systems with variable reflectivity panels that produce control forces through optical-mechanical interaction with sunlight. This substitution eliminates the mechanical disturbances, vibrations, and plume contamination associated with thruster operation, providing a clean control method suitable for satellites with sensitive instruments.
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 minimizes transient attitude disturbances, enables precise control, and potentially extends satellite lifetime by eliminating the need for thrusters, while maintaining the cleanliness of sensitive instruments and allowing for both attitude and orbital control without fuel consumption.
Implementation Method 1
a middle layer, of liquid crystal droplets embedded in a polymer, whose transparency is electrically controlled by transparent electrodes
Implementation Method 2
utilizing the control of solar radiation pressure by the use of electrically controllable variable reflection glass panels to provide the required torques and forces
Data Source
AI summary
A method and apparatus for the control of the attitude of earth orbiting satellites and the orbit and attitude control of a novel gravitational wave detection satellite configuration located near the sun-earth Lagrangian points L3, L4 and L5, utilizing the control of solar radiation pressure by the use of electrically controllable variable reflection glass panels to provide the torques and forces needed.