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US4148452A
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US
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Filtering technique based on high-frequency plant modeling for high-gain control
Assignee: National Aeronautics and Space Administration
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Filing: 1977-12-08
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Granted: 1979-04-10
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Expires: 1997-12-08
Abstract
Abstract This invention is an improvement in aircraft control systems that utilize feedback motion sensors to generate a control signal to control the aircraft. The improvement consists essentially of a complementary filter comprising a simplified model of the aircraft, a high-pass filter, a low-pass filter and a summing amplifier. The control signal is applied to the simplified model of the aircraft which ateempts to compute the vehicle response to the signal. This computed response is then fed into the high-pass filter to eliminate long-term errors in the calculated response, with the result that a good estimate of the high frequency content of the aircraft motion is obtained. In order to obtain a good estimate of the low frequency content of the motion a rate gyro signal is fed through the low-pass filter that eliminates all of the offending noise. The outputs from the high-pass and low-pass filters are summed by the summing amplifier to produce an estimated rate which is then used as a motion feedback signal. The use of the complementary filter permits a substantial increase in frequency band-width due to the simultaneous reduction in noise amplificaton and control limit-cycle tendencies.
Inventors
- 👤 Frank R. Niessen
- 👤 John F. Garren, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 10:55
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0816; G05D1/0825
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
80 words
In an aircraft control system in which the outputs from feedback devices including a feedback rate gyro are combined with the pilot input to produce a control signal for actuating the control surfaces of the aircraft, complementary filter means receiving said control signal and the output from said feedback rate gyro for producing an estimated angular rate signal that is free of both noise and phase lag and that is combined with said pilot input to produce said control signal.
Claim 2
Dependent Claim
80 words
In an aircraft control system in which the outputs from feedback devices including a feedback rate gyro are combined with the pilot input to produce a control signal for actuating the control surfaces of the aircraft, complementary filter means receiving said control signal and the output from said feedback rate gyro for producing an estimated angular rate signal that is free of both noise and phase lag and that is combined with said pilot input to produce said control signal.
Claim 3
Dependent Claim
108 words
In an aircraft control system as in claim 1 wherein said complementary filter means includes a simplified model of the aircraft receiving said control signal for producing a signal representing the aircraft's computed response to the control signal, a high-pass filter means receiving said computed response signal for eliminating long-term errors in the signal, a low-pass filter means receiving said output from said feedback rate gyro for eliminating the noise from the signal thereby giving a good estimate of the low frequency content of the motion of the aircraft, and means for summing the outputs of said high-pass and low-pass filters to produce said estimated angular rate signal.
Claim 4
Dependent Claim
46 words
In an aircraft control system as in claim 2 wherein the transfer functions of the high-pass filter and the low-pass filter are (r 1 s/r 1 s+1) and (1/r 2 s+1), respectively, where r 1 and r 2 are the time constants for the two filters.
Claim 5
Dependent Claim
18 words
In an aircraft control system as in claim 3 wherein r 1 is equal to r 2 .
Claim 6
Dependent Claim
48 words
In an aircraft control system as in claim 2 including means responsive to the pilot input into the controls of said aircraft for producing a desired rate response signal and means for subtracting said estimated rate signal from said desired rate response signal to produce said control signal.
Claim 7
Dependent Claim
24 words
In an aircraft control system as in claim 5 wherein said means for producing a desired rate response signal is a desired response model.
Claim 8
Dependent Claim
231 words
In an aircraft control system means for summing signals to produce a control signal for controlling an aircraft roll rate signal and an aircraft roll acceleration signal in response to the input from the pilot of the aircraft; a desired response model for producing signals proportional to aircraft roll attitude, aircraft roll rate and aircraft roll acceleration in response to the pilot input; a vertical gyro attached to the aircraft for producing an aircraft roll attitude signal; means for obtaining the difference between the aircraft roll attitude signals produced by said desired response model and said vertical gyro and for applying a portion of the difference signal to said means for summing signals to produce a control signal; a rate gyro attached to the aircraft for producing an aircraft roll rate signal; a complementary filter means receiving said control signal and the output from said rate gyro for producing an aircraft estimated roll rate signal; means for applying a portion of said estimated roll rate signal to said means for summing signals to produce a control signal; means for obtaining the difference between said roll rate signal produced by said desired response model and said estimated roll rate signal to produce an estimated roll rate error signal; and means for applying a portion of said estimated roll rate error signal to said means for summing signal to produce a control signal.
Claim 9
Dependent Claim
231 words
In an aircraft control system means for summing signals to produce a control signal for controlling an aircraft roll rate signal and an aircraft roll acceleration signal in response to the input from the pilot of the aircraft; a desired response model for producing signals proportional to aircraft roll attitude, aircraft roll rate and aircraft roll acceleration in response to the pilot input; a vertical gyro attached to the aircraft for producing an aircraft roll attitude signal; means for obtaining the difference between the aircraft roll attitude signals produced by said desired response model and said vertical gyro and for applying a portion of the difference signal to said means for summing signals to produce a control signal; a rate gyro attached to the aircraft for producing an aircraft roll rate signal; a complementary filter means receiving said control signal and the output from said rate gyro for producing an aircraft estimated roll rate signal; means for applying a portion of said estimated roll rate signal to said means for summing signals to produce a control signal; means for obtaining the difference between said roll rate signal produced by said desired response model and said estimated roll rate signal to produce an estimated roll rate error signal; and means for applying a portion of said estimated roll rate error signal to said means for summing signal to produce a control signal.
Claim 10
Dependent Claim
103 words
In an aircraft control system according to claim 7 wherein said complementary filter means comprises: a simplified model of the aircraft receiving said control signal for producing a calculated roll rate signal; a high-pass filter receiving said calculated roll rate signal for eliminating long-term errors in the signal; a low-pass filter receiving the roll rate signal from the rate gyro for eliminating the noise from the signal thereby giving a good estimate of the low frequency content of the motion of the aircraft; and means for summing the outputs of said high-pass and low-pass filters to produce said aircraft estimated roll rate signal.
Claim 11
Dependent Claim
45 words
In an aircraft control system according to claim 8 wherein the transfer functions of the high-pass filter and low-pass filter are r 1 s/r 1 s+1 and 1/r 2 s+1, respectively, where r 1 and r 2 are the time constants of the two filters.
Claim 12
Dependent Claim
18 words
In an aircraft control system according to claim 9 wherein r 1 is equal to r 2 .
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) | 1982-04-09 | 1982-10-09 | 1983-04-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-04-09 | 1986-10-09 | 1987-04-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-04-09 | 1990-10-09 | 1991-04-10 | $7700.00 | Window Closed / Lapsed |