Satellite Thermal Heaters for Latitude Argument Drift Control
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Solution Overview
Problem
Satellites in orbit experience drift due to asymmetric heat dissipation from radiators, leading to orbital disturbances, which require periodic and disruptive correction maneuvers to maintain position within satellite positioning systems.
Innovation Solution
A method utilizing heaters on the satellite to create a thermal power difference between opposite faces, controlled by a thermal setpoint law based on solar elevation, to generate a tangential force that counterbalances the drift, keeping the satellite's latitude argument within a predetermined angular window.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If chemical nozzles are used for satellite station keeping, then the satellite can be corrected back to nominal orbit, but the satellite operation must be interrupted and xenon consumables are depleted over time
Solution Approach 1:
The patent replaces the mechanical/chemical propulsion system (chemical nozzles consuming xenon) with a thermal control system (heaters and radiators) that uses electrical power to generate thermal forces for orbit maintenance, eliminating consumable depletion and operational interruptions
Solution Approach 2:
The satellite uses its own thermal control system components (heaters and radiators) for dual purposes: both temperature regulation and orbit maintenance, eliminating the need for separate propulsion systems and enabling continuous operation without consumable depletion
2Reliability
If chemical nozzles are used for satellite station keeping, then the satellite can be corrected back to nominal orbit, but frequent correction maneuvers are required which disrupt satellite operation
Solution Approach 1:
The patent replaces the mechanical/chemical propulsion system with a thermal control system that provides continuous, fine-adjustment capability for orbit maintenance, eliminating the need for frequent disruptive correction maneuvers and enabling uninterrupted mission operations
Solution Approach 2:
The patent implements dynamic control of heater power levels to continuously adjust the thermal force and counteract varying orbital disturbances, allowing the satellite to maintain precise orbit without discrete correction maneuvers that would interrupt operations
3Temperature
If asymmetric heat dissipation is used for thermal control, then the satellite can regulate its temperature, but it generates orbital disturbances causing latitude argument drift
Solution Approach 1:
The patent implements a feedback control system that monitors both satellite temperature and orbital position (latitude argument), dynamically adjusting heater power levels to simultaneously maintain thermal regulation and counteract orbital drift, resolving the conflict between these two functions
Solution Approach 2:
The patent makes the thermal control system universally functional by using the same heaters and radiators for both temperature regulation and orbit maintenance, allowing coordinated control of both thermal and orbital parameters through a single integrated 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
This approach allows continuous orbit control without the need for frequent and disruptive correction maneuvers, maintaining satellite position over its lifetime and reducing energy consumption by avoiding the use of xenon for station keeping.
Implementation Method 1
the satellite comprises, on two faces substantially opposite one another, radiators making it possible to evacuate the heat energy generated inside the satellite
Implementation Method 2
a thermal setpoint law is applied to at least one of the heaters, as a function of the solar elevation, to create a target thermal power difference between the two opposite faces, which thermal power difference is the origin of a force having a component tangential to an orbit of the satellite
Data Source
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AI summary
The invention relates to a method (100) for controlling the orbit of a satellite comprising a body having two substantially parallel opposite faces, each comprising at least one heater. According to the invention, the method comprises: - a step (110) for determining the evolution of a free drift of a latitude argument of the satellite; - a step (120) for controlling the drift of the latitude argument of the satellite during which a thermal setpoint law is applied to at least one of the heaters, as a function of the solar elevation, to create a target thermal power difference between the two opposite faces, which thermal power difference generates a force having a component tangential to an orbit of the satellite intended to counteract the free drift of the latitude argument of the satellite and allow the latitude argument to remain within a predetermined angular window.The invention also relates to a computer program product and a satellite.