US4452124A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Stabilizing tab for missile launcher
Assignee: Lockheed Martin Tactical Systems Inc
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Filing: 1983-03-10
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Granted: 1984-06-05
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Expires: 2003-03-10
Abstract
Abstract A launch tube (2) for launching a missile (4) is supported by a single base (6) which enables the tube (2) to pivot about orthogonal yaw and pitch axes. An aerodynamic stabilizing trim tab (20) is positioned within the interior rear of the launch tube (2). During launch, exhaust gases from the missile (4) flow over the trim tab (20), producing a lift torque which balances the torque about the pitch axis caused by gravity acting upon the missile (4). This gravitational torque would otherwise tend to pull the nose of the launch tube (2) increasingly downward as the missile (4) is launched. The angle of incidence of the trim tab (20), its surface area, and its distance from the pitch axis are varied to adjust the lift torque and the drag attributable to the trim tab (20). The drag is used to balance forward frictional force upon the launch tube (2) caused by the motion of the missile (4). The pitch torques and the linear forces are balanced simultaneously.
Inventors
- 👤 Richard C. Morenus
- 👤 John T. Moore
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 00:21
CPC Classifications
F; F41; F41F; F41F3/00; F41F3/04; F41F3/045; F41A; F41A27/00; F41A27/30
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
104 words
An apparatus for launching a missile comprising: an elongated generally cylindrical hollow launch tube having open front and rear ends, said tube accommodating therewithin an elongated generally cylindrical missile to be launched therefrom; a single support for the tube, located generally at the center of mass thereof; and a stabilizing trim tab located within the launch tube near its rear end, the trim tab disposed to present a surface area to exhaust gases leaving the missile as it is launched, thereby producing a lift torque that balances the torque produced by gravity acting upon the missile as it travels within the tube during launch.
Claim 2
Independent Claim
104 words
An apparatus for launching a missile comprising: an elongated generally cylindrical hollow launch tube having open front and rear ends, said tube accommodating therewithin an elongated generally cylindrical missile to be launched therefrom; a single support for the tube, located generally at the center of mass thereof; and a stabilizing trim tab located within the launch tube near its rear end, the trim tab disposed to present a surface area to exhaust gases leaving the missile as it is launched, thereby producing a lift torque that balances the torque produced by gravity acting upon the missile as it travels within the tube during launch.
Claim 3
Dependent Claim
57 words
The apparatus of claim 1 wherein the trim tab has substantially the shape of an airfoil, with a substantially flat upper surface and an aerodynamically curved lower surface, a first end of the tab closer to the front of the tube being thicker than an opposing end of the tab closer to the rear of the tube.
Claim 4
Dependent Claim
39 words
The apparatus of claim 1 wherein the support enables the launch tube to pivot about the two orthogonal axes: a vertical yaw axis and a horizontal pitch axis that is orthogonal to the cylindrical axis of the launch tube.
Claim 5
Dependent Claim
44 words
The apparatus of claim 1 wherein the trim tab is offset from the cylindrical axis of the launch tube; and before the missile is launched, the center of mass of the missile is substantially aligned with the center of mass of the launch tube.
Claim 6
Dependent Claim
27 words
The apparatus of claim 1 wherein the time integral of lift torque attributable to the tab is substantially equal to the time integral of the gravitational torque.
Claim 7
Dependent Claim
78 words
The apparatus of claim 1 wherein the angle formed between the trim tab and the cylindrical axis of the launch tube, the surface area of the trim tab, and the distance between the trim tab and the center of mass of the combined tube and prelaunched missile are adjusted so that the lift torque caused by the missile's exhaust gases flowing over the tab balances the gravitational torque acting upon the missile as it travels through the tube.
Claim 8
Dependent Claim
74 words
The apparatus of claim 1 wherein the angle formed between the trim tab and the cylindrical axis of the launch tube, the surface area of the trim tab, and the distance between the trim tab and the center of mass of the combined prelaunched missile and launch tube are adjusted so that forward frictional forces and rearward exhaust-gas forces along the cylindrical axis of the launch tube are balanced as the missile is launched.
Claim 9
Dependent Claim
79 words
The apparatus of claim 7 wherein the angle formed between the trim tab and the cylindrical axis of the launch tube, the surface area of the trim tab, and the distance betrween the trib tab and the center of mass of the combined prelaunched missile and launch tube are adjusted so that the lift torque caused by the missile's exhaust gases flowing over the tab balances the gravitational torque acting upon the missile as it travels through the tube.
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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) | 1987-06-05 | 1987-12-05 | 1988-06-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-06-05 | 1991-12-05 | 1992-06-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-06-05 | 1995-12-05 | 1996-06-05 | $7700.00 | Window Closed / Lapsed |