|Publication number||USH1806 H|
|Application number||US 08/724,004|
|Publication date||Oct 5, 1999|
|Filing date||Sep 30, 1996|
|Priority date||Sep 30, 1996|
|Publication number||08724004, 724004, US H1806 H, US H1806H, US-H-H1806, USH1806 H, USH1806H|
|Inventors||Troy W. Ammons, Lawrence G. Miller|
|Original Assignee||The United States Of America As Represented By The Secretary Of The Navy|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (11), Referenced by (4), Classifications (14)|
|External Links: USPTO, USPTO Assignment, Espacenet|
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.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US3955199 *||Aug 21, 1974||May 4, 1976||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|
|US4121213 *||Oct 31, 1977||Oct 17, 1978||Westinghouse Electric Corp.||Radar altimeter simulator|
|US4490117 *||Jun 11, 1982||Dec 25, 1984||The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration||Inflight IFR procedures simulator|
|US4531127 *||Apr 9, 1984||Jul 23, 1985||Springer Earl W||Tester for aircraft altitude reporting system|
|US4679049 *||Nov 7, 1985||Jul 7, 1987||U.S. Philips Corporation||Delay simulator for FM-CW range measuring apparatus|
|US4683473 *||Jan 10, 1986||Jul 28, 1987||Honeywell Inc.||Radar transit time simulator device|
|US4698635 *||Mar 2, 1986||Oct 6, 1987||The United States Of America As Represented By The Secretary Of The Navy||Radar guidance system|
|US4945360 *||Sep 12, 1989||Jul 31, 1990||Messerschmitt-Boelkow-Blohm Gmbh||Radar altimeter|
|US5160933 *||May 20, 1991||Nov 3, 1992||Honeywell Inc.||Radar altimeter with self-calibration feature|
|US5260874 *||Dec 23, 1992||Nov 9, 1993||The Boeing Company||Aircraft flight emulation test system|
|US5300934 *||Aug 27, 1992||Apr 5, 1994||Fieldtech Avionics & Instruments, Inc.||Radar altimeter loop simulator|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US6346909 *||Sep 6, 2000||Feb 12, 2002||The United States Of America As Represented By The Secretary Of The Army||System for generating simulated radar targets|
|US7138940 *||Jul 22, 2004||Nov 21, 2006||Honeywell International Inc.||Method and systems for automatic zero calibration of radar altimeters|
|US7417586||Feb 7, 2006||Aug 26, 2008||Honeywell International Inc.||Methods and systems for interferometric cross track phase calibration|
|US20060017609 *||Jul 22, 2004||Jan 26, 2006||Hager James R||Methods and systems for automatic zero calibration of radar altimeters|
|U.S. Classification||342/165, 342/120|
|International Classification||G01C5/00, G01S7/40, G01S13/88, G01C25/00|
|Cooperative Classification||G01S2007/4082, G01C25/00, G01S7/4052, G01C5/005, G01S13/882|
|European Classification||G01S7/40R, G01C25/00, G01C5/00A|