US3773281A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Automatic flight control system using instrument landing system information and including inertial filtering means for reducing ils noise
Assignee: Bendix Corp
•
Filing: 1971-06-18
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Granted: 1973-11-20
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Expires: 1991-06-18
Abstract
Abstract A flight control system includes localizer and glide path couplers using instrument landing system (ILS) information and inertially sensed data to generate appropriate control signals, and inertial filtering means for providing significant attenuation of ILS noise to reduce spurious signal generation.
Inventors
- 👤 J Doninger
- 👤 F Swern
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 10:11
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0653; G05D1/0676; G01; G01S; G01S1/00; G01S1/02
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
154 words
An aircraft control system comprising: means for providing a signal corresponding to the displacement of the craft from a predetermined reference beam; means for providing a low frequency beam rate signal; means for providing a high frequency beam rate signal; means connected to both of the beam rate signal means and to the beam displacement signal means and responsive to the signals therefrom for providing a control signal including means for combining the high and low frequency beam rate signals, means for desensitizing the beam displacement signal, means for combining the desensitized beam displacement signal and the combined beam rate signal, means for filtering the combined signal from the last mentioned means to provide a command signal and means connected to the command signal means for providing the control signal in response to the signals therefrom; and means connected to the control signal means and responsive to the control signal for controlling the craft.
Claim 2
Dependent Claim
154 words
An aircraft control system comprising: means for providing a signal corresponding to the displacement of the craft from a predetermined reference beam; means for providing a low frequency beam rate signal; means for providing a high frequency beam rate signal; means connected to both of the beam rate signal means and to the beam displacement signal means and responsive to the signals therefrom for providing a control signal including means for combining the high and low frequency beam rate signals, means for desensitizing the beam displacement signal, means for combining the desensitized beam displacement signal and the combined beam rate signal, means for filtering the combined signal from the last mentioned means to provide a command signal and means connected to the command signal means for providing the control signal in response to the signals therefrom; and means connected to the control signal means and responsive to the control signal for controlling the craft.
Claim 3
Dependent Claim
58 words
An aircraft control system as described by claim 1, wherein the means for providing a high frequency beam rate signal includes: means for providing a normal acceleration signal; and means having a predetermined lag constant for filtering the normal acceleration signal to provide the high frequency beam rate signal, said signal being nearly proportional to aircraft altitude rate.
Claim 4
Dependent Claim
47 words
An aircraft control system as described by claim 1, wherein the means for providing a low frequency beam rate signal includes; means for desensitizing the beam displacement signal; means for filtering the desensitized signal; means for limiting the filtered signal; and means for integrating the limited signal.
Claim 5
Dependent Claim
45 words
An aircraft control system as described by claim 3, including: means for combining the integrated signal and the high frequency beam rate signal; means for combining the combined signal and the limited signal; and the integrator integrating the signal from the last mentioned combining means.
Claim 6
Dependent Claim
95 words
An aircraft control system as described by claim 1, wherein the means connected to the desensitizing means and to the command signal means for providing the control signal in response to the signals therefrom includes: means for integrating the desensitized signal; means for modifying the command signal; means for combining the integrated signal and the modified signal; means for providing an attitude error signal; means for providing an attitude rate signal; and means for combining the combined integrated and modified signal, the attitude error signal and the attitude rate signal to provide the control signal.
Claim 7
Dependent Claim
37 words
An aircraft control system as described by claim 5, wherein: the means for providing an attitude error signal provides a pitch error signal; and the means for providing an attitude rate signal provides a pitch rate signal.
Claim 8
Dependent Claim
37 words
An aircraft control system as described by claim 5, wherein: the means for providing an attitude error signal provides a roll error signal; and the means for providing an attitude rate signal provides a roll rate signal.
References Cited (Backward Citations)
US2981500A
Cited
US3132828A
Cited
US3223362A
Cited
US3335980A
Cited
US3447765A
Cited
US3489378A
Cited
US3652835A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-11-19 | 1977-05-21 | 1977-11-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-11-19 | 1981-05-21 | 1981-11-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-11-19 | 1985-05-21 | 1985-11-20 | $7700.00 | Window Closed / Lapsed |