USH1806H - Variable radar altimeter test apparatus - Google Patents
Variable radar altimeter test apparatus Download PDFInfo
- Publication number
- USH1806H USH1806H US08/724,004 US72400496A USH1806H US H1806 H USH1806 H US H1806H US 72400496 A US72400496 A US 72400496A US H1806 H USH1806 H US H1806H
- Authority
- US
- United States
- Prior art keywords
- signal
- flying object
- altimeter
- test
- guidance system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C5/00—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels
- G01C5/005—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels altimeters for aircraft
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
- G01S7/4052—Means for monitoring or calibrating by simulation of echoes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
- G01S7/4052—Means for monitoring or calibrating by simulation of echoes
- G01S7/4082—Means for monitoring or calibrating by simulation of echoes using externally generated reference signals, e.g. via remote reflector or transponder
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/882—Radar or analogous systems specially adapted for specific applications for altimeters
Definitions
- This invention relates to a test apparatus and more particularly to an apparatus for testing the radar altimeter employed in the guidance system of a cruise missile or other radar guided flying device.
- the missile system In order to ensure proper operation of cruise missile systems and the like which employ radar guidance systems, it is desirable to test the system under conditions which simulate the operation of the missile system and its various guidance components under actual conditions.
- the missile system is interfaced with a flight simulation program in order to perform (in simulation) the launch events of a planned flight.
- the guidance system is stimulated by the simulation program with all of the data which it would experience during an actual flight.
- the data is recorded during the test in order to evaluate the missile performance including the guidance system.
- the variable radar altimeter test system (VRATS) of this invention provides real time simulation of terrain reflected radar signals in order to verify that the radar altimeter functions properly during an entire flight.
- flight simulation altitude data was required to be written into the guidance memory thus not providing a stimulation of the guidance system, and more particularly, the altimeter portion thereof, under the conditions it would encounter in an actual flight.
- FIG. 1 is a schematic view of the test system of this invention.
- FIG. 2 a layout of the VRATS according to this invention.
- FIG. 3 shows the signal flow during operation of the VRATS
- a variable radar altimeter test system according to this invention is shown generally at 10.
- the system includes a computer 12 which uses an Intel 80486DX4 processor.
- the system is designed to simulate a terrain reflect radar signal of the missile under test 14.
- the VRATS 10 detects a transmit signal 16 through antenna coupler and cables 36, 38 from the missile under test to create an envelope of the RF signal and a signal generated by a programmable synthesizer 18, 20 is pulse modulated by the envelope which is amplified and inverted by a video amplifier card 22.
- the pulsed RF signal is transmitted to the missile receiver 24.
- the synthesized RF signal has a time delay and attenuation characteristic of a radar return signal.
- Time delay is controlled in real time through the use of an RF delay module 26. Attenuation is manipulated in real time through program control of a digital input/output card 28.
- the control program reads simulation data from a fiber optic network card 30. Operator control initiates execution of the control program using keyboard 32 and monitor 34.
- Antenna couplers 36, 38 and cables are used to receive signals from and transmit signals to the missile under test 14.
- variable radar altimeter test system permits the missile under test to perform dynamically as it would in an actual flight. This permits the missile under test to use a large portion of its internal circuitry to sense and report altitude to the guidance computer. Altitude data collected from the guidance system is used to verify that the altimeter is capable of providing accurate data for the duration of a flight.
- FIG. 3 shows the signal flow through the system during the operation described above.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Manufacturing & Machinery (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
A variable radar altimeter test system for providing a test of the altime portion of a flying object guidance system which simulates actual flight conditions includes an antenna connection to receive a signal from the flying object being tested, a synthesizer for generating a signal programmed to simulate data characteristic of a radar return signal, pulse modulation of the programmed signal to create a third signal which is returned to the flying object under test to stimulate the altimeter portion of its guidance system.
Description
This invention relates to a test apparatus and more particularly to an apparatus for testing the radar altimeter employed in the guidance system of a cruise missile or other radar guided flying device.
In order to ensure proper operation of cruise missile systems and the like which employ radar guidance systems, it is desirable to test the system under conditions which simulate the operation of the missile system and its various guidance components under actual conditions. During such tests (static firing), the missile system is interfaced with a flight simulation program in order to perform (in simulation) the launch events of a planned flight. Following the simulated launch, the guidance system is stimulated by the simulation program with all of the data which it would experience during an actual flight. The data is recorded during the test in order to evaluate the missile performance including the guidance system. Of particular importance is the testing of the radar altimeter subassembly. The variable radar altimeter test system (VRATS) of this invention provides real time simulation of terrain reflected radar signals in order to verify that the radar altimeter functions properly during an entire flight.
Prior to this invention, flight simulation altitude data was required to be written into the guidance memory thus not providing a stimulation of the guidance system, and more particularly, the altimeter portion thereof, under the conditions it would encounter in an actual flight.
Accordingly, it is an object of this invention to provide a missile test system which simulates all of the altitude conditions which would be encountered in actual flight.
FIG. 1 is a schematic view of the test system of this invention.
FIG. 2 a layout of the VRATS according to this invention.
FIG. 3 shows the signal flow during operation of the VRATS
Referring to FIGS. 1 and 2, a variable radar altimeter test system according to this invention is shown generally at 10. The system includes a computer 12 which uses an Intel 80486DX4 processor. The system is designed to simulate a terrain reflect radar signal of the missile under test 14. The VRATS 10 detects a transmit signal 16 through antenna coupler and cables 36, 38 from the missile under test to create an envelope of the RF signal and a signal generated by a programmable synthesizer 18, 20 is pulse modulated by the envelope which is amplified and inverted by a video amplifier card 22. The pulsed RF signal is transmitted to the missile receiver 24. The synthesized RF signal has a time delay and attenuation characteristic of a radar return signal. Time delay is controlled in real time through the use of an RF delay module 26. Attenuation is manipulated in real time through program control of a digital input/output card 28. The control program reads simulation data from a fiber optic network card 30. Operator control initiates execution of the control program using keyboard 32 and monitor 34. Antenna couplers 36, 38 and cables are used to receive signals from and transmit signals to the missile under test 14.
It can be seen from the foregoing description that a variable radar altimeter test system according to this invention permits the missile under test to perform dynamically as it would in an actual flight. This permits the missile under test to use a large portion of its internal circuitry to sense and report altitude to the guidance computer. Altitude data collected from the guidance system is used to verify that the altimeter is capable of providing accurate data for the duration of a flight.
FIG. 3 shows the signal flow through the system during the operation described above.
Claims (2)
1. An apparatus for testing the altimeter portion of the guidance system of a flying object during a simulated flight including,
means for detecting the envelope of a signal received from the flying object under test,
means including a programmable synthesizer for creating programmable signal,
means for pulse modulating the programmable signal with the envelope of the signal from the flying object to create a third signal,
and means for transmitting the third signal to the flying object to stimulate the altimeter portion of the flying object guidance system.
2. An apparatus according to claim 1 wherein the third signal includes time delay and attenuation characterisic of a radar return signal.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/724,004 USH1806H (en) | 1996-09-30 | 1996-09-30 | Variable radar altimeter test apparatus |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/724,004 USH1806H (en) | 1996-09-30 | 1996-09-30 | Variable radar altimeter test apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
USH1806H true USH1806H (en) | 1999-10-05 |
Family
ID=24908560
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US08/724,004 Abandoned USH1806H (en) | 1996-09-30 | 1996-09-30 | Variable radar altimeter test apparatus |
Country Status (1)
Country | Link |
---|---|
US (1) | USH1806H (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6346909B1 (en) * | 2000-09-06 | 2002-02-12 | The United States Of America As Represented By The Secretary Of The Army | System for generating simulated radar targets |
US20060017609A1 (en) * | 2004-07-22 | 2006-01-26 | Hager James R | Methods and systems for automatic zero calibration of radar altimeters |
US7417586B2 (en) | 2006-02-07 | 2008-08-26 | Honeywell International Inc. | Methods and systems for interferometric cross track phase calibration |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3955199A (en) * | 1974-08-21 | 1976-05-04 | The United States Of America As Represented By The Secretary Of The Navy | Method of and apparatus for ground testing doppler navigation sets-a doppler radar simulator |
US4121213A (en) * | 1977-10-31 | 1978-10-17 | Westinghouse Electric Corp. | Radar altimeter simulator |
US4490117A (en) * | 1982-06-11 | 1984-12-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Inflight IFR procedures simulator |
US4531127A (en) * | 1984-04-09 | 1985-07-23 | Springer Earl W | Tester for aircraft altitude reporting system |
US4679049A (en) * | 1984-11-13 | 1987-07-07 | U.S. Philips Corporation | Delay simulator for FM-CW range measuring apparatus |
US4683473A (en) * | 1986-01-10 | 1987-07-28 | Honeywell Inc. | Radar transit time simulator device |
US4698635A (en) * | 1986-03-02 | 1987-10-06 | The United States Of America As Represented By The Secretary Of The Navy | Radar guidance system |
US4945360A (en) * | 1988-09-12 | 1990-07-31 | Messerschmitt-Boelkow-Blohm Gmbh | Radar altimeter |
US5160933A (en) * | 1990-08-28 | 1992-11-03 | Honeywell Inc. | Radar altimeter with self-calibration feature |
US5260874A (en) * | 1990-09-05 | 1993-11-09 | The Boeing Company | Aircraft flight emulation test system |
US5300934A (en) * | 1992-08-27 | 1994-04-05 | Fieldtech Avionics & Instruments, Inc. | Radar altimeter loop simulator |
-
1996
- 1996-09-30 US US08/724,004 patent/USH1806H/en not_active Abandoned
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3955199A (en) * | 1974-08-21 | 1976-05-04 | The United States Of America As Represented By The Secretary Of The Navy | Method of and apparatus for ground testing doppler navigation sets-a doppler radar simulator |
US4121213A (en) * | 1977-10-31 | 1978-10-17 | Westinghouse Electric Corp. | Radar altimeter simulator |
US4490117A (en) * | 1982-06-11 | 1984-12-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Inflight IFR procedures simulator |
US4531127A (en) * | 1984-04-09 | 1985-07-23 | Springer Earl W | Tester for aircraft altitude reporting system |
US4679049A (en) * | 1984-11-13 | 1987-07-07 | U.S. Philips Corporation | Delay simulator for FM-CW range measuring apparatus |
US4683473A (en) * | 1986-01-10 | 1987-07-28 | Honeywell Inc. | Radar transit time simulator device |
US4698635A (en) * | 1986-03-02 | 1987-10-06 | The United States Of America As Represented By The Secretary Of The Navy | Radar guidance system |
US4945360A (en) * | 1988-09-12 | 1990-07-31 | Messerschmitt-Boelkow-Blohm Gmbh | Radar altimeter |
US5160933A (en) * | 1990-08-28 | 1992-11-03 | Honeywell Inc. | Radar altimeter with self-calibration feature |
US5260874A (en) * | 1990-09-05 | 1993-11-09 | The Boeing Company | Aircraft flight emulation test system |
US5300934A (en) * | 1992-08-27 | 1994-04-05 | Fieldtech Avionics & Instruments, Inc. | Radar altimeter loop simulator |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6346909B1 (en) * | 2000-09-06 | 2002-02-12 | The United States Of America As Represented By The Secretary Of The Army | System for generating simulated radar targets |
US20060017609A1 (en) * | 2004-07-22 | 2006-01-26 | Hager James R | Methods and systems for automatic zero calibration of radar altimeters |
US7138940B2 (en) * | 2004-07-22 | 2006-11-21 | Honeywell International Inc. | Method and systems for automatic zero calibration of radar altimeters |
US7417586B2 (en) | 2006-02-07 | 2008-08-26 | Honeywell International Inc. | Methods and systems for interferometric cross track phase calibration |
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Free format text: PATENTED CASE |