Spacecraft Propulsion-Power Integration With Reversing Valve Control
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Solution Overview
Problem
Existing spacecrafts face challenges in obtaining sufficient power in high-power scenarios and require additional power generation systems, which increase design costs and complicate directional precision and disturbance control due to complex adjustment mechanisms in propulsion systems.
Innovation Solution
An integrated propulsion and power generation system for spacecraft, incorporating a propellant supply module, engine branch, and power generation branch, with reversing valves and a controller to switch states, allowing connection to either branch for propulsion or power generation, and a tail gas treatment unit to eliminate disturbing forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If an additional power generation system is added to the spacecraft, then sufficient power can be obtained in high-power scenarios, but design costs increase and system complexity increases
Solution Approach 1:
The patent combines the propulsion system and power generation system into a single integrated system. The propellant supply module serves both propulsion (through the engine branch) and power generation (through the power generation branch), eliminating the need for separate systems and reducing overall system complexity while maintaining high power output capability.
Solution Approach 2:
The propellant supply module is designed with multi-functionality, capable of supplying propellant to either the engine branch for propulsion or the power generation branch for electricity generation. This universal design allows a single system to fulfill multiple functions, reducing the need for additional dedicated components.
2Ease of operation
If a complex adjustment mechanism is added to the propulsion system to adjust thrust, then thrust control is achieved, but directional precision deteriorates and disturbance control becomes more difficult
Solution Approach 1:
The patent replaces complex mechanical adjustment mechanisms with an electronic control system. The controller electronically adjusts the flow of propellant to the engine branch, enabling thrust control without mechanical moving parts that could compromise directional precision or generate disturbances.
Solution Approach 2:
The system uses controlled fluid flow (pneumatics/hydraulics) through the propellant supply module to adjust thrust. By regulating the propellant flow rate to the engine branch through the reversible valve and controller, thrust is adjusted without mechanical adjustment mechanisms, maintaining directional precision.
3Adaptability or versatility
If the propellant supply module is connected to both engine branch and power generation branch simultaneously, then both propulsion and power generation are achieved, but control precision deteriorates
Solution Approach 1:
The patent employs a dynamic control system with reversible valves that can rapidly switch the propellant supply module's connection between the engine branch and power generation branch. This dynamic switching capability allows precise control of propellant allocation, maintaining control precision while enabling both propulsion and power generation functions as needed.
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
The system integrates propulsion and power generation functions, converting chemical energy into electric energy, meets diverse operational requirements, and enhances control precision by adjusting thrust and power output through coordinated flow control, while minimizing disturbing forces.
Implementation Method 1
a first liquid path self-locking valve and a second liquid path self-locking valve, wherein an input end of the first liquid path self-locking valve is connected to an output end of the fuel storage tank, and an output end of the first liquid path self-locking valve is connected to a first input end of the first reversing valve; and an input end of the second liquid path self-locking valve is connected to an output end of the oxidant storage tank, and an output end of the second liquid path self-locking valve is connected to an input end of the second reversing valve
Implementation Method 2
the propellant supply module includes a first reversing valve and a second reversing valve; and the controller is configured to: control the first reversing valve and the second reversing valve to switch states, and control the propellant supply module to be connected to one or two of the engine branch and the power generation branch
Implementation Method 3
the power generation branch includes a first flow control valve, a second flow control valve, a gas generator, a turbine, a power generator, and a battery pack
Implementation Method 4
a gas generator, a turbine, a power generator, and a battery pack
Implementation Method 5
a gas generator, a turbine, a power generator, and a battery pack
Implementation Method 6
the system further comprises a tail gas treatment unit, and the tail gas treatment unit includes a throttling component and a tail gas treatment device
Data Source
AI summary
Provided are an integrated propulsion and power generation system for a spacecraft and a control method thereof. The integrated propulsion and power generation system includes a propellant supply module, an engine branch, a power generation branch, and a controller, where the propellant supply module includes a first reversing valve and a second reversing valve; and the controller is configured to: control the first reversing valve and the second reversing valve to switch states, and control the propellant supply module to be controlled to one or two of the engine branch and the power generation branch.