US4337427A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Selective filter for closed loop servo system
Assignee: Hughes Missile Systems Co
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Filing: 1980-12-22
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Granted: 1982-06-29
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Expires: 2000-12-22
Abstract
Abstract In a closed loop servo system in which the input signal is inaccessible and not available for measurement, but the error signal and output signal are both accessible and measurable, a filter configuration is provided which can be inserted into the error signal path of the system to reduce the undesirable effects of noise or other unwanted signals without appreciably affecting the closed loop dynamics of the overall system. In the generalized system a filter having the characteristics g(s) in LaPlace notation is inserted into the error signal path of the system to filter selected components of the error signal. A second filter having the characteristics h(s) which satisfies the equation g(s)+h(s)=1, is coupled between the output signal and the output of the filter having the characteristics g(s). The signal passing through the filter having the characteristic h(s) is summed with the signal leaving the filter having the characteristics g(s) to cancel the filtering effect relative to the output signal and thus to decouple both filters from the control loop. Thus the filtering is accomplished without appreciably altering the characteristics of the control loop. In one application, the invention is utilized in connection with the proportional navigation guidance system for a homing missile. This permits extraneous signal components due to, for example, radome loop coupling and noise to be filtered from the error signal without affective the closed loop dynamics of the missile guidance.
Inventors
- 👤 Inge Maudal
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 03:57
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/12; G05B; G05B5/00; G05B5/01
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
128 words
In a closed loop servo system having an inaccessible input signal E i , an accessible output signal E o , an accessible error signal e, control apparatus having an input and an output, the input of said control apparatus being coupled to said error signal e and the output of said control apparatus being said output signal E o , and a first filter having the characteristics g(s) coupled in series with the input to said control apparatus, the improvement comprising: a second filter having the characteristics h(s) which satisfied the equation: g(s)+h(s)=1, the input of said second filter being coupled to a chosen component of said error signal e; and means for summing the output of said second filter to the output of said first filter.
Claim 2
Dependent Claim
128 words
In a closed loop servo system having an inaccessible input signal E i , an accessible output signal E o , an accessible error signal e, control apparatus having an input and an output, the input of said control apparatus being coupled to said error signal e and the output of said control apparatus being said output signal E o , and a first filter having the characteristics g(s) coupled in series with the input to said control apparatus, the improvement comprising: a second filter having the characteristics h(s) which satisfied the equation: g(s)+h(s)=1, the input of said second filter being coupled to a chosen component of said error signal e; and means for summing the output of said second filter to the output of said first filter.
Claim 3
Dependent Claim
22 words
The improvement defined in claim 1 wherein the input of said second filter is coupled to said output signal E o .
Claim 4
Dependent Claim
10 words
The improvement defined in claim 1 or 2 wherein: ##EQU8##
Claim 5
Independent Claim
169 words
A method of decoupling a first filter having the characteristic g(s) from a closed loop servo system, said closed loop servo system having an inaccessible input signal E i , an accessible output E o , an accessible error signal e, control apparatus having an input and an output, the input to said control apparatus being coupled to said error signal e and the output of said control apparatus being said output signal E o , and a first filter having the characteristics g(s) being coupled in series with the input to said control apparatus, said method comprising of: (a) selecting a second filter having the characteristics h(s) which satisfy the equation g(s)+h(s)=1; (b) coupling the input of said second filter to a selected component of said error signal; and (c) summing the output of said second filter with the output of said first filter to cancel the filtering action for the selected component of the error signal and thus to decouple both filters from the closed loop system.
Claim 6
Independent Claim
169 words
A method of decoupling a first filter having the characteristic g(s) from a closed loop servo system, said closed loop servo system having an inaccessible input signal E i , an accessible output E o , an accessible error signal e, control apparatus having an input and an output, the input to said control apparatus being coupled to said error signal e and the output of said control apparatus being said output signal E o , and a first filter having the characteristics g(s) being coupled in series with the input to said control apparatus, said method comprising of: (a) selecting a second filter having the characteristics h(s) which satisfy the equation g(s)+h(s)=1; (b) coupling the input of said second filter to a selected component of said error signal; and (c) summing the output of said second filter with the output of said first filter to cancel the filtering action for the selected component of the error signal and thus to decouple both filters from the closed loop system.
Claim 7
Dependent Claim
21 words
The method of claim 4 wherein the input of said second filter is coupled to said output signal E o .
Claim 8
Dependent Claim
7 words
The method of claim 3 wherein: ##EQU9##
Claim 9
Dependent Claim
214 words
In a missile having a closed loop proportional navigation guidance system for measuring the rate of rotation of the line of sight between the missile and the target and commanding the missile to maneuver so that the rate of change of the line of sight is driven to zero in which L MT is applied to a control apparatus G(s) and in which means are available for measuring L M , the improvement comprising: a first filter having the characteristics 1/(1+ts) for filtering L MT before it is applied to G(s); a second filter having the characteristics ##EQU10## for filtering L M ; and means for summing the outputs of the first and second filters and applying the sum to G(s), where: L MT is the rate of change of the vector denoting the angle of the line of sight between the missile and the target, L M is the missile contribution to the rate of change of the vector denoting the angle of the line of sight between the missile and the target, A M is the missile acceleration vector, and R C is the estimated range vector, whereby extraneous signal components due to radome loop coupling and noise will be filtered out without affecting the closed loop dynamics of the missile guidance.
Claim 10
Dependent Claim
214 words
In a missile having a closed loop proportional navigation guidance system for measuring the rate of rotation of the line of sight between the missile and the target and commanding the missile to maneuver so that the rate of change of the line of sight is driven to zero in which L MT is applied to a control apparatus G(s) and in which means are available for measuring L M , the improvement comprising: a first filter having the characteristics 1/(1+ts) for filtering L MT before it is applied to G(s); a second filter having the characteristics ##EQU10## for filtering L M ; and means for summing the outputs of the first and second filters and applying the sum to G(s), where: L MT is the rate of change of the vector denoting the angle of the line of sight between the missile and the target, L M is the missile contribution to the rate of change of the vector denoting the angle of the line of sight between the missile and the target, A M is the missile acceleration vector, and R C is the estimated range vector, whereby extraneous signal components due to radome loop coupling and noise will be filtered out without affecting the closed loop dynamics of the missile guidance.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-06-28 | 1985-12-28 | 1986-06-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-06-28 | 1989-12-28 | 1990-06-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-06-28 | 1993-12-28 | 1994-06-29 | $7700.00 | Window Closed / Lapsed |