Solid Rocket Motor Flight Termination System
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Solution Overview
Problem
Conventional flight termination systems for solid rocket motors are inadequate in breaking up unpressurized stages of multi-stage rocket motor assemblies into smaller pieces, are complex and costly, and can be insufficient for larger motors, particularly when attempting to mitigate overpressure near populated areas.
Innovation Solution
A flight termination system comprising at least one shaped charge configured to ignite an inner portion of the solid propellant structure and another shaped charge to weaken the pressure vessel, facilitating controlled fragmentation and reducing overpressure by utilizing the energy produced by the propellant to assist in the destruction process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional flight termination systems use shaped charges to cut through the pressure vessel and solid propellant structure, then thrust termination is achieved, but the solid propellant structure of unpressurized motors is not adequately broken into smaller pieces
Solution Approach 1:
The patent divides the single shaped charge into multiple segments arranged in a circular pattern around the motor axis. Each segment independently cuts and ignites a portion of the propellant structure. This segmentation allows the system to effectively terminate thrust while adequately fragmenting the propellant into smaller pieces, even in unpressurized motors, by distributing the cutting action across multiple locations simultaneously.
2Reliability
If multiple shaped charges are used to cut completely through the pressure vessel and solid propellant structure, then flight termination is achieved, but device complexity and weight increase
Solution Approach 1:
The patent designs a universal flight termination system where multiple shaped charge segments serve dual functions: (1) cutting through the pressure vessel wall to vent combustion products, and (2) igniting the solid propellant structure directly. This multi-functionality eliminates the need for separate ignition devices and simplifies the overall system architecture while maintaining reliable flight termination capability across different motor types and sizes.
3Object-affected harmful factors
If shaped charges are configured to pulverize the solid propellant structure, then overpressure is reduced, but the system becomes very complicated and prohibitively expensive for larger motors
Solution Approach 1:
The patent applies shaped charge segments that cut through the pressure vessel and ignite the propellant structure, which is sufficient to terminate thrust and fragment the propellant into adequately sized pieces. The system does not attempt complete pulverization, which would be excessively complex and expensive. Instead, it achieves the necessary level of fragmentation to reduce overpressure hazards while maintaining practical simplicity and cost-effectiveness for motors of various sizes.
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 solution effectively fragments the solid propellant into smaller pieces, reducing overpressure and increasing safety, while reducing the need for excessive ordnance and enabling safer operations near populated areas, with increased destruction efficiency and cost-effectiveness compared to conventional systems.
Implementation Method 1
a flight termination system overlying the pressure vessel. The flight termination system includes at least one shaped charge configured and positioned to produce at least one cutting jet effective to ignite and pressurize the solid rocket motor
Implementation Method 2
configured and positioned to effectuate ignition of an inner portion of the solid propellant structure
Implementation Method 3
at least one shaped charge configured and positioned to produce at least one cutting jet effective to ignite and pressurize the solid rocket motor and also effective to reduce the ability of the solid rocket motor to withstand a change in internal pressure
Implementation Method 4
as it burns it generates combustion products (e.g., exhaust gases) that are expelled through a thrust nozzle of the nozzle assembly as to provide a thrusting force
Data Source
AI summary
A solid rocket motor comprises a pressure vessel, a solid propellant structure within the pressure vessel, and a flight termination system overlying the pressure vessel. The flight termination system comprises a shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure and a reduction in an ability of the pressure vessel to withstand a change in internal pressure. Another solid rocket motor, a multi-stage rocket motor assembly, and a method of destroying a launch vehicle in flight are also described.