US4007688A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Timed missile flight termination system
Assignee: United States Department of the Navy
•
Filing: 1976-02-23
•
Granted: 1977-02-15
•
Expires: 1996-02-23
Abstract
Abstract A pressure activated, timed missile flight termination system for destroy a test missile after a predetermined period of flight to shorten its hazard space so that it can be used on firing ranges having a minimum amount of area. A delayed destruct sequence is initiated by pressure in the missile combustion chamber upon ignition of the missile. A pressure driven piston is compressed by the pressure created in the combustion chamber, causing it to strike a primer which initiates a delay fuse, a detonator, and a linear-shaped charge to destroy the missile.
Inventors
- 👤 David Bruce Franz
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 23:00
CPC Classifications
F; F42; F42B; F42B15/00; F42B15/36; F42B8/00; F42B8/12; F42B8/24; F42C; F42C15/00; F42C15/28; F42C15/30
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
174 words
A pressure activated, timed missile flight termination system comprising: a. threaded casing means for insertion in a combustion chamber wall of said missile; b. a cylindrical piston disposed within a cylinder formed in said threaded casing means; c. a primer detachably connected to said threaded casing means; d. pin means connected to said cylindrical piston for penetrating said primer and causing said primer to ignite whenever said cylindrical piston is compressed due to a pressure buildup in said combustion chamber; e. a pyrotechnic delay fuse connected to said primer; f. detonation means connected to said primer for causing a detonation when ignited by said delay fuse; g. linear-shaped charge means wrapped around said missile for severing said missile into a plurality of pieces in response to said detonation of said detonation means; wherein said pressure buildup in said combustion chamber occurs instantaneously upon ignition of said missile and said pyrotechnic delay fuse provides a predetermined delay before ignition of said detonation means so that said missile is automatically destroyed after a predetermined flight period.
Claim 2
Dependent Claim
174 words
A pressure activated, timed missile flight termination system comprising: a. threaded casing means for insertion in a combustion chamber wall of said missile; b. a cylindrical piston disposed within a cylinder formed in said threaded casing means; c. a primer detachably connected to said threaded casing means; d. pin means connected to said cylindrical piston for penetrating said primer and causing said primer to ignite whenever said cylindrical piston is compressed due to a pressure buildup in said combustion chamber; e. a pyrotechnic delay fuse connected to said primer; f. detonation means connected to said primer for causing a detonation when ignited by said delay fuse; g. linear-shaped charge means wrapped around said missile for severing said missile into a plurality of pieces in response to said detonation of said detonation means; wherein said pressure buildup in said combustion chamber occurs instantaneously upon ignition of said missile and said pyrotechnic delay fuse provides a predetermined delay before ignition of said detonation means so that said missile is automatically destroyed after a predetermined flight period.
Claim 3
Dependent Claim
31 words
The timed missile flight termination system of claim 1 wherein said threaded casing means is formed of molybdenum to withstand high pressures and temperatures while maintaining a capability to be milled.
Claim 4
Dependent Claim
37 words
The timed missile flight termination system of claim 1 further comprising retaining spring means for preventing said cylindrical piston from being compressed until said pressure buildup in said combustion chamber occurs due to ignition of said missile.
Claim 5
Dependent Claim
28 words
The timed missile flight termination system of claim 1 further comprising retaining pin means mounted in said threaded casing means for maintaining said cylindrical piston within said cylinder.
Claim 6
Dependent Claim
20 words
The timed missile flight termination system of claim 1 wherein said pyrotechnic delay fuse comprises a lead spitter delay fuse.
Claim 7
Dependent Claim
37 words
The timed missile flight termination system of claim 2 further comprising retaining spring means for preventing said cylindrical piston from being compressed until said pressure buildup in said combustion chamber occurs due to ignition of said missile.
Claim 8
Dependent Claim
28 words
The timed missile flight termination system of claim 3 further comprising retaining pin means mounted in said threaded casing means for maintaining said cylindrical piston within said cylinder.
Claim 9
Dependent Claim
28 words
The timed missile flight termination system of claim 6 further comprising retaining pin means mounted in said threaded casing means for maintaining said cylindrical piston within said cylinder.
Claim 10
Dependent Claim
20 words
The timed missile flight termination system of claim 6 wherein said pyrotechnic delay fuse comprises a lead spitter delay fuse.
References Cited (Backward Citations)
US2145507A
Cited
US2704033A
Cited
US2937595A
Cited
FR1291668A
Cited
US3185090A
Cited
US3135204A
Cited
DE1428656A1
Cited
US3331324A
Cited
US3343489A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-02-15 | 1980-08-16 | 1981-02-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-02-15 | 1984-08-16 | 1985-02-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-02-15 | 1988-08-16 | 1989-02-15 | $7700.00 | Window Closed / Lapsed |