Rocket Engine Thrust Control via Electrical Power Constraints
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Solution Overview
Problem
Rocket engines face challenges in managing thrust due to limited electrical power supply, leading to potential operational failures during space missions due to sudden power demands or energy shortages.
Innovation Solution
A method for managing thrust that calculates an initial thrust setpoint and adjusts it based on electrical power limitations, reducing propellant consumption and thrust levels when power thresholds are exceeded, ensuring the engine operates within available energy constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the rocket engine operates at maximum thrust to achieve desired speed and kinetic energy, then the mission objective is met, but the electrical power supply may be depleted prematurely causing operational failure
Solution Approach 1:
The thrust setpoint is made dynamic and adjustable based on real-time electrical power availability. The control device continuously monitors power supply status and adapts the thrust profile accordingly, transitioning between maximum thrust and reduced thrust modes to optimize the balance between mission objectives and power constraints
Solution Approach 2:
The invention changes the thrust parameter dynamically by comparing initial thrust setpoint against effective maximum thrust setpoint derived from electrical power constraints. When power limitations are detected, the thrust parameter is adjusted to a lower value that maintains mission progress while preventing power depletion
2Power
If the electrical pump consumes high instantaneous power to deliver maximum thrust, then the rocket engine performance is optimized, but the power supply may be overloaded causing system failure
Solution Approach 1:
The control device implements feedback control by continuously monitoring the electrical power consumption of the pump and comparing it against the maximum power supply capacity. When the pump power approaches the supply limit, the system provides feedback to reduce the thrust setpoint, thereby reducing pump power demand and preventing power supply overload
Solution Approach 2:
The system dynamically adjusts the pump power demand by modifying the thrust setpoint in real-time based on power supply capacity. This creates a dynamic balance where pump power consumption is optimized to match available electrical power, preventing both underutilization and overload conditions
3Duration of action of moving object
If the rocket engine maintains high thrust levels throughout the mission, then the flight duration is extended, but the cumulative energy consumption exceeds the power supply capacity
Solution Approach 1:
The thrust profile is structured as periodic alternating phases of maximum thrust and reduced thrust. During periods when electrical power is abundant, the engine operates at maximum thrust to make progress toward mission objectives. When power reserves are depleted or constraints are approached, the system transitions to reduced thrust mode, creating a periodic pattern that extends flight duration while managing cumulative energy consumption within available capacity
Data Source
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AI summary
Disclosed is a method for managing the thrust of a rocket engine (100) by which an initial thrust setpoint (PGCc ini) is computed. Taking into account at least one limitation of the electrical power supply (104), a filtered thrust setpoint (PGCc f) is then computed for the engine (100) by performing at least one of two sets of operations (S31, S32, S33; S35, S36, S37, S38). These two sets of operations comprise operations intended as a safeguard for any malfunction of the rocket engine that could occur due to a lack of sufficient available electrical power. Also disclosed is a computer program and recording medium for implementing said method, a control device for implementing said method, and a rocket engine comprising such a control device.