Patent US3699310A successfully refreshed from Google Patents.
US3699310A
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US
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Angular rate bombing system
Assignee: United States Department of the Navy
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Filing: 1970-11-06
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Granted: 1972-10-17
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Expires: 1990-11-06
Abstract
Abstract An angular rate bombing system (ARBS) which utilizes angular rate and angle measurements from an automatic target tracker, pitch and roll information from a standard vertical gyro, true airspeed data and angle of attack information to compute an azimuth lead angle to release ordnance at the correct elevation lead angle.
Inventors
- 👤 Roy D Cole
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 22:13
CPC Classifications
G; G06; G06G; G06G7/00; G06G7/48; G06G7/80
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
166 words
In an angular rate bombing system for use with an aircraft for providing an automatic weapon-release signal without a range to target measurement, inertial velocity-of-aircraft measurement or true-altitude-over-target measurement whenever the measured (elevation) rate of the line-of-sight to the target equals the computed rate necessary to obtain a hit; a tracker carried by said aircraft and providing outputs corresponding to angular rates omega i, omega j and angles xi , Eta ; vertical reference means carried by said aircraft and furnishing outputs corresponding to pitch delta and roll phi ; true airspeed measuring means on said aircraft furnishing an output corresponding to magnitude of velocity (U); true airspeed measuring means on said aircraft furnishing an output corresponding to magnitude of velocity (U); computer means carried by said aircraft operatively receiving the outputs from the automatic tracker, vertical reference means and true airspeed means and for calculating outputs corresponding to the azimuth and elevation lead angles necessary to obtain a hit and to cause automatic weapon release.
Claim 2
Dependent Claim
166 words
In an angular rate bombing system for use with an aircraft for providing an automatic weapon-release signal without a range to target measurement, inertial velocity-of-aircraft measurement or true-altitude-over-target measurement whenever the measured (elevation) rate of the line-of-sight to the target equals the computed rate necessary to obtain a hit; a tracker carried by said aircraft and providing outputs corresponding to angular rates omega i, omega j and angles xi , Eta ; vertical reference means carried by said aircraft and furnishing outputs corresponding to pitch delta and roll phi ; true airspeed measuring means on said aircraft furnishing an output corresponding to magnitude of velocity (U); true airspeed measuring means on said aircraft furnishing an output corresponding to magnitude of velocity (U); computer means carried by said aircraft operatively receiving the outputs from the automatic tracker, vertical reference means and true airspeed means and for calculating outputs corresponding to the azimuth and elevation lead angles necessary to obtain a hit and to cause automatic weapon release.
Claim 3
Dependent Claim
48 words
The system as set forth in claim 1 and further including; sight unit means carried by said aircraft; said sight unit operatively receiving the outputs from said computer means corresponding to azimuth and elevation lead angles and displaying them on said sight unit as a computed impact point.
Claim 4
Dependent Claim
88 words
The system as set forth in claim 1 further including; angle of attack measuring means carried by said aircraft and furnishing an output signal corresponding to aircraft angle of attack Alpha k V2/V3 - Alpha cos phi which signal is also inputted to said computer means and used to compute sin eta r, ( omega ir/ omega id), sin epsilon s, ( omega is/ omega ir), hr 1, omega i, psi r, phi and Tau as set forth in equations 126-130, 134, 136, 2'', 7'' and 142 respectively.
Claim 5
Dependent Claim
42 words
The system as set forth in claim 3 and further including; pressure altitude measuring means for measuring barometric pressure and outputting a signal corresponding thereto; said output signal being inputted to said computer means for computing air drag on a released weapon.
Claim 6
Dependent Claim
45 words
The system as set forth in claim 3 and further including; normal acceleration measuring means for measuring aircraft acceleration and outputting a signal corresponding to kn said signal being inputted to said computer means and used to compute Omega as set forth in equation 137.
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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) | 1975-10-17 | 1976-04-17 | 1976-10-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-10-17 | 1980-04-17 | 1980-10-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-10-17 | 1984-04-17 | 1984-10-17 | $7700.00 | Window Closed / Lapsed |