Patent US4240599A successfully refreshed from Google Patents.
US4240599A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Vehicle launching device
Assignee: United States Department of the Navy
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Filing: 1979-04-30
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Granted: 1980-12-23
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Expires: 1999-04-30
Abstract
Abstract A pneumatic system for launching aircraft wherein an elongated frame having pressurized interior chamber is volumetrically related and communicatively connected to a longitudinally-slotted cylinder supported within the frame so that expansion of air into the cylinder produces a desired thrust pressure therein that is equalized by the residual pressure external of the cylinder within the chamber. A piston member slidably contained within the cylinder is adapted to receive the compressed air and is connected to a shuttle for accelerating the aircraft to be launched. The shuttle is releasably restrained at the rearward end of the cylinder and is adapted to travel longitudinally through the slot which is dynamically sealed by a flexible strip as the shuttle passes through the slot to preserve thrust pressure within the cylinder. Means for braking the shuttle after launch include a hydraulic shock absorber connected to the frame at the forward end of the cylinder, and a longitudinal elastomeric member attached at one end thereof to the shock absorber within the cylinder. The elastomeric member is formed having a gradually reduced cross-sectional area from either end thereof so that upon impact by the moving shuttle, the longitudinal surface of the member expands against the inside of the cylinder to dissipate a portion of the kinetic energy therealong and provide sufficient dampening, in cooperation with the absorber, to effectively brake the shuttle near the forward end of the frame.
Inventors
- 👤 Joseph Hammond
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 21:03
CPC Classifications
B; B64; B64F; B64F1/00; B64F1/04
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
102 words
A pneumatic system for launching an aircraft, comprising: an elongated frame having a closed chamber adapted to be filled with an amount of compressed air; and a launch cylinder provided with a longitudinal slot and suspended within the chamber of said frame with the slot exposed to the atmosphere, said cylinder being coupled at one end thereof to the chamber to receive compressed air therefrom so that expansion of the compressed air into the cylinder produces a thrust pressure therein equal to pressure external to the cylinder within the chamber thereby preventing outward distortion of the cylinder along the slot during launch.
Claim 2
Dependent Claim
102 words
A pneumatic system for launching an aircraft, comprising: an elongated frame having a closed chamber adapted to be filled with an amount of compressed air; and a launch cylinder provided with a longitudinal slot and suspended within the chamber of said frame with the slot exposed to the atmosphere, said cylinder being coupled at one end thereof to the chamber to receive compressed air therefrom so that expansion of the compressed air into the cylinder produces a thrust pressure therein equal to pressure external to the cylinder within the chamber thereby preventing outward distortion of the cylinder along the slot during launch.
Claim 3
Dependent Claim
100 words
A pneumatic launching system according to claim 1, further comprising: exhaust means connected to said launch cylinder at a distance along the length of said cylinder for venting said cylinder to the atmosphere, the distance from the open end of said cylinder being the launch stroke thereof; a piston member slidably positioned within said cylinder to receive the compressed air; shuttle means connected to said piston member and adapted to travel through the slot of said cylinder for carrying the aircraft to launch velocity; and closure means for sealing the slot of said cylinder as said shuttle means travels therethrough.
Claim 4
Dependent Claim
53 words
A pneumatic launching system according to claim 2, wherein the volume of the chamber of said frame is in the range of ten to twenty times greater than the volume of said cylinder to minimize the reduction of system pressure during expansion of the compressed air through the launch stroke of said cylinder.
Claim 5
Dependent Claim
29 words
A pneumatic launching system according to claim 1, further comprising: holdback means connected to said frame for releasably retaining said shuttle means at the open end of said cylinder.
Claim 6
Dependent Claim
30 words
A pneumatic launching system according to claim 4, further comprising: impact absorbing means operatively connected to said frame for stopping said shuttle means at the closed end of said cylinder.
Claim 7
Dependent Claim
86 words
A pneumatic launching system according to claim 5, wherein said impact absorbing means comprises: shock absorbing means connected to said frame at the closed end of said cylinder for dampening the travel of said shuttle means at the end of the launch stroke; and elastomeric cushion means attached to said shock absorbing means within said cylinder near the closed end thereof for frictionally dissipating kinetic energy of said shuttle means against the inside of said cylinder as said cushion means moves against said shock absorbing means.
Claim 8
Dependent Claim
43 words
A pneumatic launching system according to claim 6, wherein said cushion means comprises: a longitudinal cushion member formed of a solid elastomeric material and having a gradually reduced cross-section from either end thereof, the ends of said member fitting snugly within said cylinder.
Claim 9
Dependent Claim
135 words
A braking device for absorbing the impact of a shuttle adapted to travel forwardly through a pressurized cylinder of an aircraft launcher, comprising: shock absorbing means coaxially connected to the forward, external end of the cylinder for dampening the travel of the shuttle; and elastomeric cushion means attached to said shock absorbing means and located within the pressurized cylinder, said cushion means including: a longitudinal cushion member formed of a solid elastomeric material and having a gradually reduced cross-section from either end thereof, the ends of said member fitting snugly within said cylinder, said reduced cross-section expanding, upon impact of said shuttle, into engagement with the inside of said pressurized cylinder for frictionally dissipating kinetic energy of the shuttle along the inside of the cylinder as said cushion means moves against said shock absorbing means.
Claim 10
Dependent Claim
135 words
A braking device for absorbing the impact of a shuttle adapted to travel forwardly through a pressurized cylinder of an aircraft launcher, comprising: shock absorbing means coaxially connected to the forward, external end of the cylinder for dampening the travel of the shuttle; and elastomeric cushion means attached to said shock absorbing means and located within the pressurized cylinder, said cushion means including: a longitudinal cushion member formed of a solid elastomeric material and having a gradually reduced cross-section from either end thereof, the ends of said member fitting snugly within said cylinder, said reduced cross-section expanding, upon impact of said shuttle, into engagement with the inside of said pressurized cylinder for frictionally dissipating kinetic energy of the shuttle along the inside of the cylinder as said cushion means moves against said shock absorbing 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) | 1983-12-23 | 1984-06-23 | 1984-12-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1987-12-23 | 1988-06-23 | 1988-12-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1991-12-23 | 1992-06-23 | 1992-12-23 | $7700.00 | Window Closed / Lapsed |