Multi-pulse Rocket Motor Flight Termination via Propellant Overpressurization
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Solution Overview
Problem
Existing flight termination systems for flight vehicles face challenges in accommodating termination components within the existing vehicle envelope, leading to undesirable length and volume additions that negatively impact testing operations.
Innovation Solution
A flight termination destruct charge configured as an electroexplosive detonator is explosively coupled to the propellant in the pressure vessel, igniting it without a vent path to rupture the vessel and terminate thrust, allowing integration within the existing envelope and utilizing an additional pulse in multi-pulse rocket motors as the thrust termination charge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional flight termination components are incorporated into existing flight vehicles, then thrust termination capability is achieved, but the vehicle envelope is exceeded with additional length and volume
Solution Approach 1:
The flight termination system merges the destruct charge functionality with the existing propellant load. The destruct charge is positioned to directly contact the propellant grain, eliminating the need for separate external termination devices. This integration allows the termination system to fit within the existing vehicle envelope without adding external length or volume.
Solution Approach 2:
The propellant serves dual functions: as the thrust-generating fuel during normal operation and as the target for the destruct charge during termination. This multi-functionality eliminates the need for dedicated termination components, allowing the same propellant mass to serve both propulsion and termination purposes.
2Reliability
If larger energetic trains are used for flight termination, then termination reliability is improved, but device complexity and system qualifications increase
Solution Approach 1:
The invention extracts only the essential termination function from complex energetic trains. Instead of using large, multi-component termination systems, the patent employs a simple destruct charge that directly contacts the propellant grain. This extraction of the core function eliminates unnecessary complexity and reduces system qualifications while maintaining termination reliability.
Solution Approach 2:
The destruct charge is designed as a simple, disposable component that requires minimal qualification. Rather than using complex, heavily-qualified energetic trains, the invention uses a straightforward destruct charge that contacts the propellant directly, reducing both device complexity and the extensive system qualifications typically required for flight termination systems.
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 solution effectively meets range safety requirements by eliminating the need for larger energetic trains and additional system qualifications, enabling seamless integration into existing flight vehicles while terminating thrust efficiently.
Implementation Method 1
The activated detonator is configured to ignite the propellant grain without venting the pressure vessel
Implementation Method 2
ignites the propellant with no vent path, resulting in a rupturing of the propellant grain
Implementation Method 3
When a critical pressure of the pressure vessel is reached, the rocket motor casing's structural capabilities are exceeded. The overpressurized case then ruptures thereby terminating thrust
Implementation Method 4
The overpressurized case then ruptures thereby terminating thrust of the rocket motor
Data Source
AI summary
A flight test system uses a flight termination destruct charge that is configured to overpressurize a pressure vessel in a rocket motor to terminate thrust. The flight termination destruct charge is an electroexplosive detonator arranged on a final burn surface of a propellant contained in the pressure chamber. In a multi-pulse rocket motor, one of the pulses is ignited by the activation of the detonator. The activated detonator is configured to ignite the propellant grain without venting of the gas resulting from the burning of the propellant. Due to the burning of the propellant, the surface area in the pressure vessel is increased which causes increased pressure in the pressure vessel until a critical pressure is reached. When the critical pressure is reached, the rocket motor casing structural capabilities are exceeded. The overpressurized rocket motor casing then ruptures and thrust of the rocket motor is terminated.