Reduction of depressurization thrust termination jolt
AssigneeUnited Technologies Corporation
InventorClarence A. LeFebvre
Life of this patent
Estimating the term…
Abstract
Thrust termination of a solid propellant rocket motor is obtained by connecting the nozzle to the combustion chamber pressure vessel by means of explosive and extrusable bolts. When it is desired to obtain thrust termination, the explosive bolts are blown leaving the nozzle connected to the pressure vessel by the extrusable bolts. The extrusable bolts have sufficient strength to retain the nozzle assembly; however, upon elimination of the strength of the explosive bolts, the nozzle is permitted to separate from the pressure vessel and move to the rear by drawing the extrusable bolts through dies. The bolts deform to absorb the energy of the nozzle and the jolt of forward acceleration which would normally be obtained if the nozzle were ejected, is reduced or eliminated.
Claims14
In a method for thrust termination of a reaction motor by depressurization of the combustion chamber which comprises forming a port in the combustion chamber by causing a portion of the structure defining said combustion chamber to move away from the remainder of the structure, the improvement whereby the jolt produced by the escape of gas through said port is reduced which comprises:
- a. maintaining said portion of said combustion chamber structure physically connected to the remainder of said structure by deformable connecting means during the movement of said portions away from each other;
- b. directing the gases escaping through the port formed between said portion and the remainder of the structure into a pattern substantially symmetrically distributed about an axis extending substantially parallel to the direction of motion;
- c. permanently deforming said connecting means as said portions move away from each other.
A depressurization thrust termination system for a reaction motor comprising:
- a. means defining a combustion chamber;
- b. thrust termination port forming means for separating said combustion chamber defining means into first and second portions;
- c. deformable connecting means connecting said first portion to said second portion;
- and,
- d. means for permanently deforming said connecting means as said first and second portions move away from each other.
A thrust termination system for a reaction motor comprising, in combination:
- a. a combustion chamber
- b. thrust termination port forming means adapted to produce a substantially symmetrical radially distributed gas pattern;
- c. a plurality of connecting means for releasably, maintaining said port forming means in gas sealing contact with said combustion chamber;
- d. means for rendering said connecting means partially inoperative;
- and,
- e. means for permanently deforming the remainder of said connecting means as said port forming means separate from said combustion chamber.
In a method for depressurization of the combustion chamber of a reaction motor which comprises forming a port in the combustion chamber by causing a portion of the structure defining said combustion chamber to move away from the remainder of the structure, the improvement which comprises:
- a. maintaining said portion of said combustion chamber structure physically connected to the remainder of said structure by deformable connecting means during the movement of said portions away from each other;
- and
- b. permanently deforming said connecting means as said portions move away from each other.
In a method for reducing the pressure within the combustion chamber of a reaction motor which comprises forming a port in the combustion chamber by causing a portion of the structure defining said combustion chamber to move away from the remainder of the structure, the improvement whereby the jolt produced by the escape of gas through said port is reduced which comprises:
- a. maintaining said portion of said combustion chamber structure physically connected to the remainder of said structure by deformable connecting means during the movement of said portions away from each other;
- b. directing the gases escaping through the port formed between said portion and the remainder of the structure into a pattern substantially symmetrically distributed about an axis extending substantially parallel to the direction of motion;
- c. permanently deforming said connecting means as said portions move away from each other.
A system for reducing the chamber pressure of a reactor motor combustion chamber comprising, in combination:
- a. means defining a combustion chamber;
- b. port-forming means for separating said combustion chamber defining means into first and second portions;
- c. deformable connecting means connecting said first portion to said second portion;
- and
- d. means for permanently deforming said connecting means as said first and second portins move away from each other.
Dependencies are inferred from the claim text.