US4142695A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Vehicle guidance system
Assignee: Raytheon Co
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Filing: 1971-10-27
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Granted: 1979-03-06
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Expires: 1991-10-27
Abstract
Abstract A vehicle guidance system wherein a vehicle is guided in either a command guidance mode or a homing guidance mode. In the command guidance mode, the target tracking element, used during the homing guidance mode serves as an inertial reference element. Such element is attitude stabilized in pitch and yaw by mechanically driven means used in both modes, such means driving the reference element with respect to the vehicle's body and, in roll, by the vehicle's roll autopilot to aerodynamically control the vehicle's attitude in roll.
Inventors
- 👤 John A. Remmell
- 👤 Frank Blitzer
- 👤 Robin L. Anderson
- 👤 Robert G. Dietrich
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 20:29
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/226; F41G7/2266; F41G7/2206; F41G7/2273; F41G7/2286; F41G7/30
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
180 words
In a vehicle guidance system, wherein a vehicle is guided during a portion of flight towards a selected target in a command guidance mode and during another portion of the flight in a homing guidance mode, apparatus comprising: (a) target tracking means, including a target tracking element carried by the vehicle, for generating guidance signals for the vehicle during the homing guidance mode; (b) first means, affixed to the target tracking element, for sensing the inertial angular rates of such element about a pitch axis and a yaw axis; (c) means, responsive to the first means, for gimballing the target tracking element with respect to the vehicle's body about the pitch axis and the yaw axis; (d) second means, affixed to the target tracking element, for sensing the inertial angular rate of such target tracking element about an axis mutually orthogonal to the pitch axis and the yaw axis; and (e) means, responsive to the first means and the second means, for stabilizing the attitude of the target tracking element at a known angular orientation during the command guidance mode.
Claim 2
Dependent Claim
180 words
In a vehicle guidance system, wherein a vehicle is guided during a portion of flight towards a selected target in a command guidance mode and during another portion of the flight in a homing guidance mode, apparatus comprising: (a) target tracking means, including a target tracking element carried by the vehicle, for generating guidance signals for the vehicle during the homing guidance mode; (b) first means, affixed to the target tracking element, for sensing the inertial angular rates of such element about a pitch axis and a yaw axis; (c) means, responsive to the first means, for gimballing the target tracking element with respect to the vehicle's body about the pitch axis and the yaw axis; (d) second means, affixed to the target tracking element, for sensing the inertial angular rate of such target tracking element about an axis mutually orthogonal to the pitch axis and the yaw axis; and (e) means, responsive to the first means and the second means, for stabilizing the attitude of the target tracking element at a known angular orientation during the command guidance mode.
Claim 3
Dependent Claim
37 words
The apparatus recited in claim 1 wherein the stabilizing means includes means, responsive to the second means, for controlling the attitude of the vehicle aerodynamically in accordance with the inertial angular rate sensed by such second means.
Claim 4
Dependent Claim
18 words
The apparatus recited in claim 2 wherein the controlling means is a roll autopilot carried within the vehicle.
Claim 5
Dependent Claim
29 words
The apparatus recited in claim 1 including stabilizing means, coupled to the gimballing means and the stabilizing means, for positioning the target tracking element at a predetermined angular orientation.
Claim 6
Dependent Claim
40 words
The apparatus recited in claim 4 wherein the positioning means includes means coupled to the first means and the second means, for integrating the inertial angular rates about the pitch axis, the yaw axis and the axis mutually orthogonal thereto.
References Cited (Backward Citations)
US3631485A
Cited
US3617016A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-03-05 | 1982-09-04 | 1983-03-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-03-05 | 1986-09-04 | 1987-03-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-03-05 | 1990-09-04 | 1991-03-06 | $7700.00 | Window Closed / Lapsed |