Movable Base Pulsed Detonation Engine Supply
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Solution Overview
Problem
Current pulsed detonation engine supply devices, such as aeroacoustic and electromechanical valves, are complex, inefficient, and costly, limiting engine performance and complicating design, especially for aerospace applications.
Innovation Solution
A pulsed detonation engine design featuring a transverse movable base that acts as both the thrust wall and supply device, moving between two positions to control the supply and detonation phases, eliminating the need for external valves and using elastic return means for autonomous operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional valves (aeroacoustic or electromechanical) are used to control combustible charge supply, then the engine can operate, but the device complexity increases and performance is reduced
Solution Approach 1:
The patent merges the thrust wall and supply device control functions into a single integrated component. The movable base that forms the thrust wall is also configured to control the supply opening, eliminating the need for separate valves or control devices. This integration directly reduces device complexity while maintaining operational control.
Solution Approach 2:
The movable base serves multiple functions simultaneously: it acts as the thrust wall for detonation phase, controls the supply opening for charge admission, and works with locking means for position stabilization. This multi-functionality eliminates the need for separate dedicated components for each function, reducing overall system complexity.
2Ease of operation
If electromechanical valves are used to control supply phase, then admission control is improved, but the valve cost increases and design complexity increases
Solution Approach 1:
The supply control function is merged into the movable base structure itself. The base's movement between positions naturally controls the supply opening without requiring separate electromechanical valves, thereby simplifying the design while maintaining admission control capability.
Solution Approach 2:
The movable base controls the supply opening through its own movement, which is driven by the detonation pressure and expansion phase mechanics. The system uses its own operational cycles to control the supply phase without requiring external electromechanical control systems.
3Device complexity
If aeroacoustic supply control is used, then device simplicity is maintained, but admission optimization for full operation range is reduced
Solution Approach 1:
The movable base provides dynamic control of the supply opening through its movement between positions. This dynamic mechanism allows optimization of admission across the full operation range, unlike static aeroacoustic control, while maintaining relative simplicity through the mechanical movement approach.
4Reliability
If conventional valves are used for supply control, then engine operation is achieved, but manufacturing cost increases
Solution Approach 1:
By merging the thrust wall and supply control functions into the movable base, the patent eliminates the need for separate expensive valves or control devices. This integration reduces the number of components that require manufacturing and assembly, thereby reducing overall manufacturing cost while maintaining engine operation reliability.
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 design simplifies the engine, enhances operational safety and reliability, and allows for efficient fuel/oxidizer admission, reducing complexity and cost while improving performance and integration in aerospace applications.
Implementation Method 1
said transverse base of the flame tube is mounted so that it can move with respect to the latter in order to be able to occupy two boundary positions
Implementation Method 2
the shock wave compresses the combustible charge (fuel/oxidizer mixture) situated in the combustion chamber of the engine, in order to bring it above its self-ignition temperature
Implementation Method 3
detonation is a particular method of propagating a flame which results from the coupling between a shock wave and a combustion front
Implementation Method 4
elastic return means for autonomous operation
Data Source
AI summary
A pulsed detonation engine may include a flame tube with a lateral wall and a transverse base defining a combustion chamber and a supply device cyclically feeding said combustion chamber with a combustible charge. The transverse base of the flame tube may be movable for reciprocating in translation inside said flame tube in order to be able to occupy two boundary positions, a first position corresponding to the detonation phase of the combustible charge in the combustion chamber of said flame tube and a second position corresponding to the phase wherein the combustible charge is supplied to said combustion chamber.