Antenna Reflector Sunlight Heating for Spacecraft Orbit Raising

Solution Overview

Problem

Regulating the temperature of a spacecraft during orbit raising is technically challenging, especially when using electrical propulsion, as it requires significant DC power and can reduce battery life or increase the time of flight, and existing heating methods are inefficient.

Innovation Solution

The use of an antenna reflector to reflect sunlight onto a thermal radiator panel to warm the spacecraft during orbit raising, allowing for thermal regulation and maintaining internal temperatures above a minimum threshold without relying solely on battery power or reducing power for propulsion.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If electrically powered heaters are used to warm the spacecraft during orbit raising, then the temperature of internal circuitry is maintained above minimum temperature, but battery life is reduced and power available for EOR is decreased

Engineering Contradiction:

Improveinternal circuitry temperatureVSAvoidbattery power consumption

Core Design Contradiction:

TemperatureVSUse of energy by moving object

Solution Approach 1:

The invention converts the harmful effect of excessive heat dissipation by thermal radiator panels into a beneficial heating source for the spacecraft body during orbit raising. By strategically positioning and controlling these panels, the waste heat they emit is redirected to warm the spacecraft, eliminating the need for additional battery-powered heaters and preserving power for propulsion.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

Solution Approach 2:

The spacecraft uses its own thermal radiator panels to provide heating during orbit raising, rather than requiring separate heating systems. The thermal management system serves dual purposes: dissipating heat when needed and providing warmth during orbit raising, making the system self-sufficient and reducing dependency on battery power.

Inventive Principle:

Principle #25Self-service

2Temperature

If electrically powered heaters are used to warm the spacecraft during orbit raising, then the temperature of internal circuitry is maintained above minimum temperature, but the time of flight is increased due to reduced power for EOR

Engineering Contradiction:

Improveinternal circuitry temperatureVSAvoidtime of flight

Core Design Contradiction:

TemperatureVSLoss of time

Solution Approach 1:

The invention converts the harmful effect of excessive heat dissipation by thermal radiator panels into a beneficial heating source for the spacecraft body during orbit raising. By strategically positioning and controlling these panels, the waste heat they emit is redirected to warm the spacecraft, eliminating the need for additional battery-powered heaters and preserving power for propulsion.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

Solution Approach 2:

The spacecraft uses its own thermal radiator panels to provide heating during orbit raising, rather than requiring separate heating systems. The thermal management system serves dual purposes: dissipating heat when needed and providing warmth during orbit raising, making the system self-sufficient and reducing dependency on battery power.

Inventive Principle:

Principle #25Self-service

3Temperature

If thermal radiator panels are designed to dissipate heat when in operational orbit, then heat from internal circuitry is managed, but the panels cannot provide heating during orbit raising

Engineering Contradiction:

Improveheat dissipation capabilityVSAvoidthermal regulation flexibility

Core Design Contradiction:

TemperatureVSAdaptability or versatility

Solution Approach 1:

The invention makes the thermal radiator panels dynamically controllable, allowing their orientation and functionality to change based on mission phase. During orbit raising, the panels are positioned to reflect sunlight and trap heat for warming the spacecraft. In operational orbit, they are repositioned to dissipate heat effectively. This dynamic adaptability allows the same panels to serve opposite thermal functions at different times.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The thermal radiator panels are designed to perform multiple functions: heat dissipation during operational orbit and heat retention/reflection during orbit raising. This multi-functionality eliminates the need for separate heating and cooling systems, reducing overall system complexity and improving thermal management efficiency across different mission phases.

Inventive Principle:

Principle #6Universality (Multi-functionality)

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 method effectively maintains the internal temperature of the spacecraft above a minimum operating temperature during orbit raising, reducing the need for battery power and potentially shortening the time of flight by optimizing power usage for propulsion.

Implementation Method 1

the antenna reflector is used in the orbit raising configuration to regulate the spacecraft temperature. In some embodiments, the antenna reflector is positioned such that sunlight will reflect off the antenna reflector onto the thermal radiator panel of the spacecraft, thereby warming the spacecraft

Methodology Applied

Scientific EffectReflection: Reflection

Data Source

PatentUS20230369737A1Antenna reflector spacecraft temperature regulation during orbit raising

Publication Date: 2023.11.16 LANTERIS SPACE LLC

AI summary

Technology is disclosed herein for using an antenna reflector to regulate a spacecraft temperature during orbit raising. When in a launch configuration, the antenna reflector may be stowed in a fairing of a launch vehicle. After the spacecraft is deployed from the launch vehicle and prior to orbit raising, the antenna reflector is moved from the launch configuration to an orbit raising configuration in which the antenna reflector is used to regulate the spacecraft temperature. The antenna reflector may be proximate a thermal radiator panel of the spacecraft when in the launch configuration. The antenna reflector may be positioned such that sunlight will reflect off the antenna reflector onto the thermal radiator panel, thereby warming the spacecraft. After orbit raising, the antenna reflector is moved from the orbit raising configuration to an operational configuration in which a boresight of the antenna reflector may be directed toward nadir.