US3791208A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Angle of attack computer
Assignee: Honeywell Inc
•
Filing: 1971-03-16
•
Granted: 1974-02-12
•
Expires: 1991-03-16
Abstract
Abstract Apparatus for providing a measure of the true angle of attack of an aircraft without external probes or vanes, which measure is derived from computations involving measurements of longitudinal and normal accelerations of the aircraft in conjunction with air data derived computations of vertical speed and true airspeed. Supplementary outputs of the angle of attack computer are instantaneous vertical speed of the aircraft which is accurate under pitch and roll maneuvers, true flight path angle, and acceleration of the craft along the flight path.
Inventors
- 👤 H Miller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 02:59
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
148 words
Angle of attack computer apparatus for aircraft comprising a. a pair of linear accelerometers mounted on the aircraft with their sensitive axes orthogonally oriented in the craft longitudinal vertical plane and responsive respectively to correspondingly orthogonal components of the total craft accelerations in said plane for providing signals in accordance therewith, b. means for supplying a signal corresponding to the angle of the flight path of said aircraft relative to the horizontal, c. means for supplying a signal corresponding to the air-speed acceleration of said aircraft along said flight path, d. means responsive to said flight path angle signal, said airspeed acceleration signal and the longitudinal acceleration component signal for supplying a signal corresponding to the algebraic sum thereof, and e. divider means responsive to said sum signal and the vertical acceleration component signal for providing a resultant signal corresponding to the angle of attack of said aircraft.
Claim 2
Dependent Claim
148 words
Angle of attack computer apparatus for aircraft comprising a. a pair of linear accelerometers mounted on the aircraft with their sensitive axes orthogonally oriented in the craft longitudinal vertical plane and responsive respectively to correspondingly orthogonal components of the total craft accelerations in said plane for providing signals in accordance therewith, b. means for supplying a signal corresponding to the angle of the flight path of said aircraft relative to the horizontal, c. means for supplying a signal corresponding to the air-speed acceleration of said aircraft along said flight path, d. means responsive to said flight path angle signal, said airspeed acceleration signal and the longitudinal acceleration component signal for supplying a signal corresponding to the algebraic sum thereof, and e. divider means responsive to said sum signal and the vertical acceleration component signal for providing a resultant signal corresponding to the angle of attack of said aircraft.
Claim 3
Dependent Claim
119 words
The angle of attack computer apparatus as set forth in claim 1 wherein said means for supplying said flight path angle signal includes: a. air data sensor means for supplying a signal corresponding to aircraft airspeed and a signal corresponding to the rate of change of altitude, b. inertial means including said accelerometers for supplying a signal corresponding to the vertical acceleration of said aircraft relative to the horizontal. c. filter means responsive to said altitude rate and vertical acceleration signals for providing a composite signal proportional to altitude rate over a wide frequency band, and d. divider means responsive to said airspeed signal and said composite signal for providing a resultant signal corresponding to aircraft flight path angle.
Claim 4
Dependent Claim
36 words
The apparatus as set forth in claim 2 wherein said inertial means includes a vertical gyro means for modifying the signals of said accelerometer means in accordance with the roll and pitch attitude of said aircraft.
Claim 5
Dependent Claim
17 words
The apparatus as set forth in claim 2 wherein said filter means is a low pass filter.
Claim 6
Dependent Claim
85 words
The angle of attack computer apparatus as set forth in claim 1 wherein said means for supplying said airspeed acceleration signal comprises a. air data sensor means for supplying a signal corresponding to aircraft airspeed, b. inertial means including said accelerometers for supplying a signal corresponding to the accleration of said aircraft along its flight path, and c. filter means responsive to said airspeed signal and said flight path acceleration signal for providing a composite signal proportional to airspeed acceleration over a wide frequency band.
Claim 7
Dependent Claim
35 words
The apparatus as set forth in claim 5 wherein said inertial means includes a vertical gyro means for modifying the signals of said accelerometers in accordance with the roll and pitch attitude of said aircraft.
Claim 8
Dependent Claim
16 words
The apparatus as set forth in claim 5 wherein said filter means is a wash-out filter.
Claim 9
Dependent Claim
32 words
The apparatus as set forth in claim 5 further including feedback means responsive to said angle of attack signal for modifying the vertical acceleration component signal of said accelerometers in accordance therewith.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-02-11 | 1977-08-13 | 1978-02-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-02-11 | 1981-08-13 | 1982-02-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-02-11 | 1985-08-13 | 1986-02-12 | $7700.00 | Window Closed / Lapsed |