Liquid-Crystal Thermal Shielding for Spacecraft Avionics Panels
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Solution Overview
Problem
Existing thermal protection systems for air and space vehicles face inefficiencies in managing temperature fluctuations due to varying solar exposure angles, leading to excessive heater power consumption and temperature extremes on payload panels.
Innovation Solution
A thermal protection system comprising screen barriers made of liquid-crystal flexible material, actuators, and heaters that adjust between transparent and opaque states to regulate heat flux, along with a control unit to manage temperature within predetermined limits, and heaters to maintain temperature adequacy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multi-layer insulation blankets and electrical heaters are used to protect panels from solar flux and maintain temperature, then thermal protection is provided, but heater power consumption becomes excessive
Solution Approach 1:
The patent applies dynamic adjustment by rotating the payload panels to different angular positions relative to the sun's direction. This dynamic repositioning allows panels that would otherwise require excessive heater power to be oriented away from direct solar flux, naturally reducing heat absorption and subsequent heater demand while maintaining reliable thermal protection
Solution Approach 2:
The invention changes the operational parameter of panel orientation angle to control thermal exposure. By adjusting the angular position of panels around the satellite body, the system modulates the amount of solar flux received, thereby controlling heat absorption and reducing dependency on high-power heaters
2Ease of operation
If payload panels always face the same direction, then payload equipment location is simplified, but temperature extremes occur due to varying solar exposure angles
Solution Approach 1:
The patent segments the satellite's thermal control into independent controllable units - individual payload panels can be rotated independently to optimal angles. This segmentation allows each panel to be positioned according to its specific thermal needs and solar exposure, preventing temperature extremes while maintaining operational simplicity through modular control
Solution Approach 2:
Rather than fixing panels in static orientations, the invention implements dynamic rotation capability for each panel. This allows the system to adapt panel angles in response to varying solar flux conditions throughout the orbit, maintaining stable temperatures despite changing external thermal environments
3Temperature
If large radiator areas are used to release heat load from panels exposed to solar flux, then thermal balance is maintained, but device complexity increases
Solution Approach 1:
Instead of using large radiators to actively reject heat from sun-exposed panels, the invention inverts the approach by rotating panels to minimize solar heat absorption in the first place. This passive avoidance strategy reduces the thermal load that would otherwise require large radiator surfaces to dissipate, thereby simplifying the thermal control system
Solution Approach 2:
The invention converts the harmful effect of solar flux exposure into a beneficial passive thermal control mechanism. By orienting panels away from the sun, the natural solar radiation pattern itself becomes the tool for thermal management, eliminating the need for complex active cooling systems and large radiator areas
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
Provides durable, reliable, and efficient temperature regulation, reducing heater power consumption and maintaining equipment within manufacturer-specified temperature ranges, regardless of solar exposure angles.
Implementation Method 1
the screen barriers (4) are activated by an electric field to allow flux passage
Implementation Method 2
screen barriers made of liquid-crystal flexible material
Implementation Method 3
panels and equipment that are not exposed to solar flux and remain on the cold side are constantly supported by electrical heaters
Implementation Method 4
the shield deflects the heat emitted from these sources into deep space
Data Source
AI summary
The present invention comprises a source (S) generating heat and/or radiation; a body (2) located on a space vehicle; at least one avionics chamber (A) on the body (2), in which the avionics equipment is provided; at least one panel (P) outside the body (2), which extends outward from the body (2) and stores the flux from the source (S); at least one shield (3) on the body (2), which at least partially covers the surface of the body (2) to protect the body (2) from the energy provided by the source (S).