Solid rocket motors including flight termination systems, and related multi-stage solid rocket motor assemblies and methods
AssigneeOrbital ATK, Inc.
InventorsJoseph J. Kliger, Paul C. Braithwaite, Brian C. Liechty, Donald B. Patterson
Life of this patent
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Abstract
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.
Claims28
A solid rocket motor, comprising:
- a pressure vessel;
- a solid propellant structure within the pressure vessel;
- and
- a flight termination system overlying the pressure vessel and comprising 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.
A solid rocket motor, comprising:
- a pressure vessel;
- a solid propellant structure within the pressure vessel;
- and
- a flight termination system overlying the pressure vessel and comprising:
- at least one first shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure;
- and
- at least one second shaped charge spaced apart from the at least one first shaped charge and configured and positioned to effectuate a reduction in an ability of the pressure vessel to withstand a change in internal pressure.
A multi-stage rocket motor assembly, comprising:
- an outer housing;
- and
- a plurality of stages in a stacked arrangement within the outer housing, at least one stage of the plurality of stages comprising:
- a pressure vessel;
- a solid propellant structure within the pressure vessel;
- and
- a flight termination system overlying the pressure vessel and comprising at least one 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.
A method of destroying a launch vehicle in flight, comprising initiating at least one shaped charge of a flight termination system of a solid rocket motor of the launch vehicle to pressurize the solid rocket motor and weaken a pressure vessel thereof to fragment a solid propellant structure of the solid rocket motor into multiple pieces.
Dependencies are inferred from the claim text.