US3596855A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft control system
Assignee: Allard Way Holdings Ltd
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Filing: 1969-04-07
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Granted: 1971-08-03
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Expires: 1989-04-07
Abstract
Abstract An aircraft control system for enabling the aircraft to capture and follow a predetermined flight path, the system including means giving a displacement error signal which is a measure of the vertical displacement of the aircraft from the flight path, means giving a vertical velocity signal representative of the vertical velocity of the aircraft, a logic circuit for connecting the output of a pitch signal generator to the input of the pitch control channel of the aircraft when the displacement error signal is equal to the vertical velocity signal, and means for ensuring that there is no abrupt change in the pitch demand signal supplied to the pitch channel.
Inventors
- 👤 Geoffrey M Barling
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 06:28
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/0623
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
2 words
I claim:
Claim 2
Dependent Claim
44 words
An aircraft control system as claimed in claim 3 wherein the said connecting means is a switch whereby, on development of the capture initiation signal the input to the first lag filter may be disconnected from the compensating filter and connected instead to earth.
Claim 3
Dependent Claim
41 words
An aircraft control system as claimed in claim 4 wherein the output of the first lag filter, which falls gradually to zero after the input to the lag filter is connected to earth, constitutes at least part of the pitch signal.
Claim 4
Dependent Claim
80 words
An aircraft control system as claimed in claim 5 wherein combining means are provided to combine the output from the first lag filter with the displacement error signal to constitute at least part of the pitch signal. 7 An aircraft control system as claimed in claim 5 wherein means are provided for deriving an output from the accelerometer and combining the derived output with the output of the first lag filter to constitute at least part of the pitch signal.
Claim 5
Dependent Claim
29 words
An aircraft control system as claimed in claim 5 wherein means are provided for developing a pitch attitude signal and combining it to constitute part of the pitch signal.
Claim 6
Dependent Claim
43 words
A aircraft control system as claimed in claim 1 wherein an integrating circuit is connected to receive an input from the accelerometer and apply its output to the logic circuit, thereby influencing the generator of the capture initiation signal by transient aircraft motion.
Claim 7
Dependent Claim
38 words
An aircraft control system as claimed in claim 1 wherein switch means are provided responsive to the capture initiation signal to effect switching of the output of the pitch signal generator to the pitch channel of the aircraft.
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) | 1974-08-02 | 1975-02-01 | 1975-08-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-02 | 1979-02-01 | 1979-08-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-02 | 1983-02-01 | 1983-08-03 | $7700.00 | Window Closed / Lapsed |