US3949676A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Load actuated electro-ignition circuit switch
Assignee: United States Department of the Navy
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Filing: 1974-06-10
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Granted: 1976-04-13
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Expires: 1994-06-10
Abstract
Abstract An igniter mechanism for a rocket motor utilized for towing a load or extting an air crew member from a disabled aircraft. The mechanism operates whenever a sufficient force is exerted on the tow line to shear a pin allowing closure of the switch. Electrical energy coupled to the switch is conducted to a squib which ignites a charge to cause ignition of the rocket motor propellant. The electrical switch mechanism can only be actuated by a predetermined pulling force on the tow line thereby causing the electrical contacts to be brought positively together.
Inventors
- 👤 Joseph A. Schmidt
- 👤 W. James Stone
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 22:22
CPC Classifications
F; F42; F42C; F42C19/00; F42C19/08; F42C19/12
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
151 words
A propellant ignition mechanism for a rocket motor utilized to tow a load by means of a tow cable fastened concentric with the center of the rocket motor and rearward of its nozzles comprising; a cylindrical rocket motor housing having a nozzle portion formed with a rearward extending boss closing the rear word end of said housing; a chamber formed by an axially disposed bore that is concentric with said rocket motor housing and which extends a substantial distance into the boss; piston means in said chamber attached to a tow line and operative to move linearly rearwardly of the rocket motor after a predetermined force is exerted on said tow line; electrical contact means operative to close after a predetermined rearward linear travel of said piston means; and power supply means electrically coupled to said electrical contact means to supply a current for igniting a rocket motor for powered flight.
Claim 2
Dependent Claim
151 words
A propellant ignition mechanism for a rocket motor utilized to tow a load by means of a tow cable fastened concentric with the center of the rocket motor and rearward of its nozzles comprising; a cylindrical rocket motor housing having a nozzle portion formed with a rearward extending boss closing the rear word end of said housing; a chamber formed by an axially disposed bore that is concentric with said rocket motor housing and which extends a substantial distance into the boss; piston means in said chamber attached to a tow line and operative to move linearly rearwardly of the rocket motor after a predetermined force is exerted on said tow line; electrical contact means operative to close after a predetermined rearward linear travel of said piston means; and power supply means electrically coupled to said electrical contact means to supply a current for igniting a rocket motor for powered flight.
Claim 3
Dependent Claim
28 words
The propellant ignition mechanism of claim 1 further comprising: an electrically actuated explosive charge; and a booster charge ignited by said explosive charge for initiation of propellant burning.
Claim 4
Dependent Claim
43 words
The propellant ignitor mechanism of claim 1: wherein said piston means has a substantially thick head portion and an elongated threaded stud portion extending from one surface of said head portion, said head portion having a sealing means extending around its circumferential edge.
Claim 5
Dependent Claim
34 words
The propellant igniter mechanism of claim 1: wherein said electrical contact means has a fixed contact portion and a movable contact portion, said movable contact portion adapted to move as said piston means moves.
Claim 6
Dependent Claim
21 words
The propellant ignition mechanism of claim 1 further comprising: guide pin means for causing piston means to move linearly without rotating.
Claim 7
Dependent Claim
43 words
The propellant ignition mechanism of claim 5 further comprising: shear pin means fastened to hold said piston means from initial movement until sufficient rearward force is exerted on the tow line for shearing said pin thereby permitting rearward movement of said piston means.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-04-13 | 1979-10-13 | 1980-04-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-04-13 | 1983-10-13 | 1984-04-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-04-13 | 1987-10-13 | 1988-04-13 | $7700.00 | Window Closed / Lapsed |