US3744309A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Pitch signal calculator for aircraft
Assignee: United Control Corp
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Filing: 1970-07-20
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Granted: 1973-07-10
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Expires: 1990-07-20
Abstract
Abstract An instrument for calculating the pitch angle of an aircraft from two pitch signals, one having long term and the other short term pitch accuracy. The long term pitch signal is derived from a longitudinal accelerometer. A measured pitch signal having short term accuracy is provided by a vertical gyroscope. An airspeed acceleration signal is provided by a vertical gyroscope. An airspeed acceleration signal is subtracted from the accelerometer output to eliminate the acceleration component of the signal. The calculated and measured pitch signals are combined or blended in selected inverse proportions.
Inventors
- 👤 R Astengo
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 18:57
CPC Classifications
G; G01; G01C; G01C19/00; G01C19/02; G01C19/44
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
156 words
A pitch angle generator for an aircraft, comprising: a longitudinal accelerometer having an output which is a function of the forward acceleration and the pitch attitude of the aircraft; a vertical gyroscope having an output which represents the measured pitch of the aircraft, subject to static and long time drift errors; first means for deriving from the output of the longitudinal accelerometer a signal which is a function essentially only of the forward acceleration and the long term pitch attitude of the aircraft; second means for deriving from the output of the vertical gyroscope a signal which is a function essentially only of short term pitch attitude of the aircraft; third means for developing a signal representing forward acceleration of the aircraft; and combining means for subtracting the forward acceleration signal from the signal derived by the first means and adding said long term and short term pitch attitude signals to generate a calculated pitch signal.
Claim 2
Dependent Claim
156 words
A pitch angle generator for an aircraft, comprising: a longitudinal accelerometer having an output which is a function of the forward acceleration and the pitch attitude of the aircraft; a vertical gyroscope having an output which represents the measured pitch of the aircraft, subject to static and long time drift errors; first means for deriving from the output of the longitudinal accelerometer a signal which is a function essentially only of the forward acceleration and the long term pitch attitude of the aircraft; second means for deriving from the output of the vertical gyroscope a signal which is a function essentially only of short term pitch attitude of the aircraft; third means for developing a signal representing forward acceleration of the aircraft; and combining means for subtracting the forward acceleration signal from the signal derived by the first means and adding said long term and short term pitch attitude signals to generate a calculated pitch signal.
Claim 3
Dependent Claim
46 words
The pitch angle generator of claim 1 in which the means for developing a signal representing forward acceleration of the aircraft includes means for measuring the air speed of the aircraft and means for establishing a signal representing the rate of change of the air speed.
Claim 4
Dependent Claim
46 words
The pitch angle generator of claim 1 in which the two signal deriving means form a complementary filter having a low pass filter section connected with the output of said longitudinal accelerometer and a high pass filter section connected with the output of said vertical gyroscope.
Claim 5
Dependent Claim
64 words
The pitch angle generator of claim 3 in which the means for developing a signal representing a forward acceleration of the aircraft includes means for measuring the air speed of the aircraft and means, including a band pass filter section, for establishing a signal representing the rate of change of air speed, which is combined with the output of said low pass filter section.
Claim 6
Dependent Claim
39 words
The pitch angle generator of claim 1 including means for summing a signal representing the measured pitch of the aircraft from the vertical gyroscope and the calculated pitch signal from said combining means, to form a blended pitch signal.
Claim 7
Dependent Claim
38 words
The pitch angle generator of claim 5 in which said summing means relates the calculated and measured pitch signals by factors of K and 1-K, respectively, where K is a positive factor which is not greater than one.
References Cited (Backward Citations)
US3371528A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-07-09 | 1977-01-08 | 1977-07-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-07-09 | 1981-01-08 | 1981-07-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-07-09 | 1985-01-08 | 1985-07-10 | $7700.00 | Window Closed / Lapsed |