Patent US3775766A successfully refreshed from Google Patents.
US3775766A
Expired / Lapsed
US
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Independent landing monitoring pulse radar system
Assignee: Thales SA
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Filing: 1972-01-11
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Granted: 1973-11-27
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Expires: 1992-01-11
Abstract
Abstract An Independent Landing Monitoring pulse radar system supplying angular information similar to these supplied by an I.L.S. system comprising circuits for improving the precision of the supplied data through compensation of the dynamic computation errors due to the aircraft displacement between successive data measurements, and circuits supplying additional position information such as location, velocity distance and estimated stopping distance. The system may also be operated for synthetic runway display, as a weather and as an anti-collision radar system.
Inventors
- 👤 R Gendreu
- 👤 J Genuist
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 11:20
CPC Classifications
G; G01; G01S; G01S13/00; G01S13/88; G01S13/91; G01S13/913; G01S13/93; G01S13/933; G01S13/935
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
193 words
An Independent Landing Monitoring (ILM) pulse radar system for use in cooperation with three reflectors B1 , B2 and B3 (FIGS. 10, 14) and with auxiliary on board - systems supplying flight parameters, said ILM system supplying bearing and elevation information ( gamma , delta FIGS.10 and 11) relative to the position of the aircraft on which it is mounted with respect to the runway on which the aircraft has to land, similar to those supplied by conventional I.L.S. Systems, said radar system further comprising : compensation circuit means (310 ,FIG. 12b)for supplying bearing values compensated for the dynamic errors in the computation of said bearing information said circuit means comprising : first correcting means (305, 306) for compensating for the longitudinal displacement of the aircraft , said first means having inputs for the reflector parameters (IB ) and an output , and second correcting means (300 and 303) for compensating for the aircraft yaw movement , said second means having an input for the course of the aircraft (C), an input for the antenna bearing indication (gi),an input coupled to said first correcting means output, and an output supplying said compensated value.
Claim 2
Dependent Claim
193 words
An Independent Landing Monitoring (ILM) pulse radar system for use in cooperation with three reflectors B1 , B2 and B3 (FIGS. 10, 14) and with auxiliary on board - systems supplying flight parameters, said ILM system supplying bearing and elevation information ( gamma , delta FIGS.10 and 11) relative to the position of the aircraft on which it is mounted with respect to the runway on which the aircraft has to land, similar to those supplied by conventional I.L.S. Systems, said radar system further comprising : compensation circuit means (310 ,FIG. 12b)for supplying bearing values compensated for the dynamic errors in the computation of said bearing information said circuit means comprising : first correcting means (305, 306) for compensating for the longitudinal displacement of the aircraft , said first means having inputs for the reflector parameters (IB ) and an output , and second correcting means (300 and 303) for compensating for the aircraft yaw movement , said second means having an input for the course of the aircraft (C), an input for the antenna bearing indication (gi),an input coupled to said first correcting means output, and an output supplying said compensated value.
Claim 3
Dependent Claim
135 words
An ILM System according to claim 1, wherein said second correcting means comprise a course variation computer (303) having an input for said course (C) and an output ( Delta C) , a first algebraic adder (301, FIG.13) having a first addition input for said antenna bearing indication input, a second addition input ,coupled to said course variation computer output , a subtraction input, and an output, averaging means (302) having an input coupled to said adder output , and an output, a second adder (307) having two inputs respectively coupled to said integrating means output and to said first correcting means output, and an output, an integrator means (304) having an input coupled to said second adder output, and an output coupled to said subtraction input, said integrator output supplying the compensated bearing value.
Claim 4
Dependent Claim
45 words
An ILM System according to claim 1, wherein said first correcting means comprise a computing means (305, FIG. 13) having an input . . . for said reflector parameters and an output, and differentiating means (306) having an input coupled to said last mentioned output.
Claim 5
Dependent Claim
125 words
An ILM System according to claim 1, comprising distance parameter outputs (ro, r1 , r2 , r3 FIG. 12a) , bearing indication outputs (Go, G3), elevation indication outputs ( Beta ) , said ILM system further comprising further circuit means (201, FIG. 12 b) having inputs for said distance parameters, for said bearing and elevation indication, and for said reflector (IB) parameters, said further circuit means (201) . . . supplying the distance of the aircraft to the far end of the runway (r3 e) , the coordinates of said aircraft ( Xof, Yof, Zof) with respect to a trihedral fixed to the runway of the decrabing angle ( Delta psi ), and the ILS angular deviation ( gamma cf and delta f ) .
Claim 6
Dependent Claim
62 words
An ILM system according to claim 4, having an input for the aircraft acceleration parallel to the runway axis ( < xo FIG. 12b ) , said system further comprising distance computing means (204) having an input for said aircraft abcissa in said trihedral (Xof) , an input for said acceleration and an output supplying the predicted stopping distance of the aircraft.
Claim 7
Dependent Claim
43 words
An ILM system according to claim 1 having distance (r) antenna axis elevation ( eta ) and elevation error signal ( Delta S) outputs, said system further comprising an anti-collision circuit (205 FIG. 12b) having respective inputs coupled to said last mentioned outputs.
Claim 8
Dependent Claim
92 words
An ILM . . . system according to claim 1 having an input for the aircraft attitudes (IAT) , an input for the runway parameters (IRW) associated with a runway display means having display inputs said ILM system further comprising further circuit means (203) FIG. 12 b) for supplying said runway display means, said last mentioned further circuit means having respective inputs for said aircraft attitudes, for said runway parameters and for said bearing values supplied by said compensation circuit means, and respective outputs coupled respectively to said runway display means inputs.
Claim 9
Dependent Claim
112 words
An ILM System according to claim 1 transmitting pulses of a first given duration at a first given repetition frequency, comprising a monopulse antenna, a difference reception channel ( Delta ) and a sun reception channel, said sun channel comprising frequency changing means (7 FIG.12a) having an output, said ILM system further comprising means for weather radar operation, said last mentioned means comprising a weather receiver (15 FIG. 12 b and FIG.21), means for synchroneously (i) transmitting pulses of a second given duration longer than said first one and at a second repetition frequency smaller than said first one, and means for (ii) coupling said changing means output to said weather receiver.
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) | 1976-11-26 | 1977-05-28 | 1977-11-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-11-26 | 1981-05-28 | 1981-11-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-11-26 | 1985-05-28 | 1985-11-27 | $7700.00 | Window Closed / Lapsed |