Patent US4444086A successfully refreshed from Google Patents.
US4444086A
Expired / Lapsed
US
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Missile azimuth aiming apparatus
Assignee: United States Department of the Army
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Filing: 1981-12-23
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Granted: 1984-04-24
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Expires: 2001-12-23
Abstract
Abstract Apparatus for fast, accurate aiming of a missile from a launch vehicle. Thepparatus permits fast accurate aiming of a missile inertial measurement unit for cases in which the inertial measurement unit does not possess required performance capability for self-aiming. The apparatus involves no optical link and is not expended with the missile.
Inventors
- 👤 Harold V. White
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-10 01:36
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/007
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
92 words
Apparatus for fast, accurate aiming of a missile positioned on a launch vehicle, said missile having a strapdown inertial measurement unit carried thereon, said apparatus comprising: a. a retract mechanism supported on said launch vehicle; b. a gyrocompass carried on said retract mechanism; c. said strapdown inertial measurement unit having a precision surface thereon and said gyrocompass having a reference surface thereon for intimate contact therebetween; d. said retract mechanism disposed for displacement for separation of said gyrocompass from said inertial measurement unit responsive to said gyrocompass acquiring the desired azimuth information.
Claim 2
Dependent Claim
92 words
Apparatus for fast, accurate aiming of a missile positioned on a launch vehicle, said missile having a strapdown inertial measurement unit carried thereon, said apparatus comprising: a. a retract mechanism supported on said launch vehicle; b. a gyrocompass carried on said retract mechanism; c. said strapdown inertial measurement unit having a precision surface thereon and said gyrocompass having a reference surface thereon for intimate contact therebetween; d. said retract mechanism disposed for displacement for separation of said gyrocompass from said inertial measurement unit responsive to said gyrocompass acquiring the desired azimuth information.
Claim 3
Dependent Claim
24 words
Apparatus as in claim 1 wherein said launch vehicle is provided with a prime mover for positioning said missile to the proper target azimuth.
Claim 4
Dependent Claim
32 words
Apparatus as in claim 2 including a data link circuit connected between said prime mover and said gyrocompass to provide target information for said prime mover for proper positioning of said missile.
Claim 5
Dependent Claim
79 words
Apparatus as in claim 2 including a guidance and control computer carried on board said missile, second data link means connected between computer and said gyrocompass and third data link means connected between said inertial measurement unit and said computer, whereby said second data link means is disposed for transmitting azimuth information from said gyrocompass to said computer, and, said third data link means is disposed for transmitting reference coordinate information from said inertial measurement unit to said computer.
Claim 6
Dependent Claim
16 words
Apparatus as in claim 2 wherein said precision and reference surface are precision machined smooth surfaces.
References Cited (Backward Citations)
US3941345A
Cited
US3955468A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-04-24 | 1987-10-24 | 1988-04-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-04-24 | 1991-10-24 | 1992-04-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-04-24 | 1995-10-24 | 1996-04-24 | $7700.00 | Window Closed / Lapsed |