US 5,036,658 AGrant
Pressure Relief Device for Solid Propellant Motors Subjected to High External Temperatures
Issue Date:1991-08-06
•3 Claims
•1 Drawing Sheets
Abstract
A rocket motor that has a solid propellant with closure means that is secd to the rocket motor housing by heat responsive means that melts before the solid propellant ignites to prevent the rocket motor from becoming propulsive when subjected to excessive external heat sufficient to cause the rocket propellant to ignite.
Metadata
Assignee
- The United States of America as represented by the Secretary of the Army
Inventor
- John M. Tate
Application Information
Application Number:US 4881796
Filing Date:1990-03-05
Priority Date:1990-03-05
Art Unit:343
Classifications
IPC:
F02K 100
Field of Search:
60102253;271;39.1;39.091;223481
Patent Drawings (1 sheets)
Description
Brief Description of the Drawing
The single FIGURE of the drawing is a sectional view illustrating a rocket motor with end closures that are secured thereto in accordance with this invention.
Description of the Preferred Embodiment
Referring now to the drawing, a rocket motor case 10 has a conventional rocket motor closure nozzle 12 mounted at one end by a groove 14 in the outer periphery of a portion of nozzle 12, by groove 16 in housing 10 and by low melting point alloy material 18 mounted between grooves 14 and 26 to secure nozzle 12 relative to rocket motor housing 10. A conventional o-ring type seal 20 is provided for sealing at the periphery of rocket motor nozzle 12. The opposite end of rocket motor housing 10 has an end closure 22 with a groove 24 in the periphery thereof and rocket motor housing 10 has a groove 26 adjacent groove 24 with a low melting alloy 28 mounted for securing end closure 22 relative to rocket motor housing 10. An o-ring type seal 30 is provided for sealing end closure 22 relative to rocket motor housing 10. A conventional type rocket motor solid propellant 32 is mounted in rocket motor housing 10 in a conventional manner. Alloy materials 18 and 28 are selected to have a melting point that is slightly below the ignition temperature of solid propellant 32 so that low melting point alloy 18 or 28 will melt before solid propellant 32 is ignited to cause build up of pressure in the rocket motor. By providing low melting point alloy 18 or 28, when the rocket motor is subjected to external high temperatures, low melting point alloy 18 and/or 28 will melt and prevent solid propellant 32 from producing thrust from the rocket motor if the solid propellant is ignited. Low melting point alloys 18 and/or 28 can be selected from alloys such as Corro 2405, 2581, etc. from Belmont Metal Products. Col, P.O. Box 388; Bellefonte, Pa. 16823. These alloys generally contain such metals as bismuth, lead cadmium and tin and have a melting point of about 280.degree. Fahrenheit. Low melting point alloys 18 and 28 are mounted in their respective groove by casting the alloy material through an opening or openings in housing 10 or by any other conventional manner.
Claims
I claim:
1. A rocket motor comprising a housing with a solid propellant mounted therein, said housing having a first groove extending into and around an internal surface which is void of said solid propellant at one of said housing, said housing having a second groove extending into and around an internal surface void of said propellant at the other end of said housing; closure means having a groove extending into and around the periphery of an external surface, said groove being in an adjacent position when installed to said first groove of said housing; heat responsive means mounted in said first groove of said housing and said groove of said closure means for securing the closure means to the housing; and a rocket motor nozzle having a groove extending into and around the periphery of an external surface, said groove being in an adjacent position when installed to said second groove of said housing; heat responsive means mounted in said second groove of said housing and said groove of said rocket nozzle for securing said rocket motor nozzle to said other end of said rocket motor housing, said heat responsive means having a melting point that is lower than the ignition point of said solid propellant so that when said housing is subjected to excessive external temperature, said heat responsive means will release said closure means and said rocket motor nozzle to prevent pressure build up in the motor housing, wherein said heat responsive means is a metal alloy and is contained in said groove of said closure means, in said groove of said rocket motor nozzle, and in said first groove and said second groove of said rocket motor housing with the grooves of the rocket motor housing, the rocket nozzle, and the closure means being filled with said metal alloy.
2. The rocket motor as set forth in claim 1, wherein said rocket motor nozzle and said housing have seal means for sealing the rocket motor nozzle relative to the housing.
3. The rocket motor as set forth in claim 2, wherein said closure means and said housing have seal means for sealing said closure means relative to said housing.
Patent Citations (6)
| Patent | Date | Inventor | Cited By |
|---|---|---|---|
| US2958184 | 1960-11-01 | Sanders | |
| US2958185 | 1960-11-01 | Sanders | |
| US3134222 | 1964-05-01 | Maxon | |
| US3613374 | 1971-10-01 | Ritchey | |
| US3887991 | 1975-06-01 | Panella | |
| US4423683 | 1984-01-01 | Telmo |