CN102156411B - System and method for simulating radio altitude echo signal - Google Patents
System and method for simulating radio altitude echo signal Download PDFInfo
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- CN102156411B CN102156411B CN201010602707A CN201010602707A CN102156411B CN 102156411 B CN102156411 B CN 102156411B CN 201010602707 A CN201010602707 A CN 201010602707A CN 201010602707 A CN201010602707 A CN 201010602707A CN 102156411 B CN102156411 B CN 102156411B
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Abstract
The invention discloses a system and method for simulating a radio altitude echo signal. The system is characterized in that a object mathematic simulator, a radio echo signal simulator and a simulation working station are respectively connected with a real-time network; the object mathematic simulator is connected with a mission computer; the radio echo signal simulator is connected with a radio altimeter; the radio altimeter is connected with the mission computer; the mission computer is connected with a steering system; an output end of the steering system is connected with an input end of the simulation working station; an output end of the simulation working station is connected with an input end of the mission computer; and an output end of the mission computer is connected with an input end of a telemetric data collector. In the invention, a real-time analog echo signal and a noise jamming signal are provided to the radio altimeter of an open-loop or closed-loop FM-CW (Frequency Modulation-Continuous Wave) system in a semi-object simulation system so as to obtain goals of simulation mode closer to that of an actual system, more credible result, low cost and more convenience for variable control experiments.
Description
Technical field
The present invention relates to the emulation mode of analog echo signal, particularly a kind of radio altitude echoed signal analogue system and method.
Background technology
Radio altimeter uses for the operation of aircraft has very large effect.Plunder in the extra large flight course at aircraft, need the real-time aircraft guidance control system that is of radio altimeter to improve flying height information, and aircraft is controlled, make aircraft according to predetermined air route flight by flight control system.When in lower flying height, need radio altimeter to have higher altimetry precision and less finding range.Therefore, must carry out strict test and checking, test its ability to work under various states for the performance of radio altimeter.For realizing this test job; In traditional FM-CW system radio altimeter performance test; Test of aircraft through reality and aircraft are hung and are flown test and carry out often, and this whole use real systems or parts are though system prototype can approaching arbitrarily last system configuration; Its simulation model in kind is also approaching with real system, and simulation result is credible.But the flight test of this reality receives the restriction in flight air route, can not test at all states of doing wartime radio altimeter, also can't accomplish the check under the ultimate limit state.And expense is high, and it is also inconvenient to do the Variable Control test.And in the laboratory method through analog radio height indicator echoed signal, can under various state, make an experiment to radio altimeter.At present, the performance test of FM-CW system radio altimeter is based on the static test of fixed point, take the altitude basically, and the dynamic indicator of corresponding radio altimeter and dynamic property are difficult to checking.
Summary of the invention
The objective of the invention is; Real-time analog echo signal, noise jamming signal is provided for open loop or closed loop FM-CW system radio altimeter in the semi-matter simulating system, to reach simulation model and real system is more approaching, simulation result is more credible; And expense is low, and the Variable Control test is more convenient.
For realizing above-mentioned purpose, the present invention adopts following technical scheme, a kind of radio altitude echoed signal analogue system; It is characterized in that mathematics emulator in kind, radioecho signal simulator, simulation work station connect real-time net respectively, mathematics emulator in kind is connected with mission computer; The radioecho signal simulator is connected with radio altimeter; Radio altimeter is connected with mission computer, and mission computer is connected with rudder system, and the output terminal of rudder system is connected with the simulation work station input end; The output terminal of simulation work station is connected with the input end of mission computer, and the output terminal of mission computer is connected with telemetry collector input end.
A kind of radio altitude echoed signal emulation mode may further comprise the steps:
1) mission computer, rudder system and radio altimeter are inserted in the Semi-Physical Simulation Test System;
2) on simulation work station, resolve the kinetic model and the kinematics model of aircraft;
3) airborne simulation fire control system is bound to mission computer the test mission data according to test parameters, on mission computer, realizes the control of resolving of guidance rule;
4) the guidance rule is resolved required angle, speed, guiding control signal and is generated by mathematics emulator in kind, and be defeated by mission computer;
5) simulation work station is passed to the radioecho signal simulator through real-time net with the elevation information of aircraft;
6) radioecho signal simulator transmitting and simulating corresponding radioecho signal on the net and give radio altimeter according to radio altimeter from the elevation information that collects in real time;
7) radio altimeter obtains height value through mixing, and then gives mission computer this height value, and mission computer is given rudder system through resolving the control rudder face signal that draws aircraft;
8) simulation work station passes through the feedback signal that the A/D conversion equipment is gathered rudder system, thereby accomplishes the closed-loop simulation of total system.
Advantage of the present invention is; Can be in the HWIL simulation test; Transmitting of information such as the height that provides according to simulation work station, extra large land state and radio altimeter simulates the radio altitude echoed signal under the corresponding height situation in real time, can controlled radio altitude echoed signal be provided for test; Under testing laboratory's state, radio altimeter is carried out the test under the various states.
Description of drawings
Fig. 1 is the HWIL simulation test schematic block diagram of closed loop radio altimeter of the present invention.
Fig. 2 is the test synoptic diagram of open loop radio altimeter index of the present invention.
Among the figure: the real-time net of 1-, 2-radioecho signal simulator, 3-simulation work station, 4-radio altimeter, 5-mission computer, 6-rudder system, 7-mathematics emulator in kind, 8-telemetry collector.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described further; Referring to Fig. 1; A kind of radio altitude echoed signal analogue system, mathematics emulator in kind 7, radioecho signal simulator 2, simulation work station 3 connect net 1 in real time respectively, and mathematics emulator 7 in kind is connected with mission computer 5; Radioecho signal simulator 2 is connected with radio altimeter 4; Radio altimeter 4 is connected with mission computer 5, and mission computer 5 is connected with rudder system 6, and the output terminal of rudder system 6 is connected with simulation work station 3 input ends; The output terminal of simulation work station 3 is connected with the input end of mission computer 5, and the output terminal of mission computer 5 is connected with telemetry collector 8 input ends.
A kind of radio altitude echoed signal emulation mode may further comprise the steps:
1) mission computer 5, rudder system 6 and radio altimeter 4 are inserted in the Semi-Physical Simulation Test System;
2) on simulation work station 3, resolve the kinetic model and the kinematics model of aircraft;
3) airborne simulation fire control system is bound to mission computer 5 the test mission data according to test parameters, on mission computer 5, realizes the control of resolving of guidance rule;
4) the guidance rule is resolved required angle, speed, guiding control signal by mathematics emulator 7 generations in kind, and is defeated by mission computer 5;
5) simulation work station 3 is passed to radioecho signal simulator 2 through real-time net 1 with the elevation information of aircraft;
6) radioecho signal simulator 2 transmitting and simulating corresponding radioecho signal on the net and give radio altimeter 4 according to radio altimeter from the elevation information that collects in real time;
7) radio altimeter 4 obtains height value through mixing, and then gives mission computer 5 this height value, and mission computer 5 is given rudder system 6 through resolving the control rudder face signal that draws aircraft;
8) simulation work station 3 passes through the feedback signal that the A/D conversion equipment is gathered rudder system, thereby accomplishes the closed-loop simulation of total system.
The present invention obtains altitude information from real-time net 1, again by the standard (open loop or closed loop) of radioecho signal simulator 2 according to radio altimeter 4, and generates corresponding echoed signal signal and noise signal, gives radio altimeter 4 through feeder line then.In order to simulate the echoed signal under the various conditions more truly, also in radioecho signal simulator 2, increased the noise signal generation system, noise signals such as the wired clutter of its clutter type, extra large clutter.Satisfy requirement with this, and verify height indicator influence to the aircraft performance index under various states two kinds of standard radio altimeter dynamic indicator tests.
Embodiment 1:
The HWIL simulation test of closed loop radio altimeter referring to Fig. 1, is directly connected to rudder system 6, closed loop radio altimeter 4 on the mission computer 5, connects and composes closed-loop simulation system in kind to simulation work station 3 and mission computer 5 simultaneously.On simulation work station 3, resolve the kinetic model and the kinematics model of aircraft; Before the test according to combination table to make an experiment task data bookbinding of mission computer 5, simulation work station 3 is given mathematics emulator 7 in kind with signals such as the angle that calculates, speed, guiding controls, mathematics emulator 7 in kind is defeated by mission computer 5 through interface; Simulation work station 3 is passed to radioecho signal simulator 2 through real-time network with the elevation information of aircraft; Radioecho signal simulator 2 is given radio altimeter 4 according to transmitting and simulating corresponding radioecho signal from the elevation information that collects in real time on the net of this height indicator of radio, and the height that radio altimeter 4 will obtain is given mission computer 5 again through interface; Mission computer 5 carries out the control signal that obtains to resolve from conductance, and four control rudder face signals that draw aircraft are given rudder system 6; Give simulation work station 3 feedback signal of the rudder face of rudder system 6 through the A/D conversion equipment in the simulation work station 3 simultaneously, thereby accomplish the closed-loop simulation of total system.The data that mission computer 5 produces in the process of simulation are gathered by telemetry collector 8;
Embodiment 2:
The test of open loop radio altimeter index; Referring to Fig. 2; Simulation work station 3 and radioecho signal simulator 2 are connected through real-time network, and directly link to each other radioecho signal simulator 2, radio altimeter 4, telemetry collector 8 and mission computer 5.When test; Send height value to give radioecho signal simulator 2 by simulation work station 3; Radioecho signal simulator 2 simulates corresponding radioecho signal according to height value and gives radio altimeter 4; Radio altimeter 4 resolves through difference frequency and gives mission computer 5 height that obtains, and mission computer 5 is given telemetry collector 8 through interface.Relatively simulation work station 3 is seen the data that data and telemetry collector 8 obtain off.Thereby reach the purpose of test radio altimeter 4 static indexs.
Claims (2)
1. radio altitude echoed signal analogue system; It is characterized in that; Mathematics emulator (7) in kind, radioecho signal simulator (2), simulation work station (3) connect real-time net (1) respectively; Mathematics emulator in kind (7) is connected with mission computer (5), and radioecho signal simulator (2) is connected with radio altimeter (4), and radio altimeter (4) is connected with mission computer (5); Mission computer (5) is connected with rudder system (6); The output terminal of rudder system (6) is connected with simulation work station (3) input end, and the output terminal of simulation work station (3) is connected with the input end of mission computer (5), and the output terminal of mission computer (5) is connected with telemetry collector (8) input end.
2. one kind is adopted radio altitude echoed signal analogue system as claimed in claim 1 to carry out radio altitude echoed signal method of emulation, it is characterized in that: may further comprise the steps:
1) mission computer (5), rudder system (6) and radio altimeter (4) are inserted in the Semi-Physical Simulation Test System;
2) on simulation work station (3), resolve the kinetic model and the kinematics model of aircraft;
3) airborne simulation fire control system is bound to mission computer (5) the test mission data according to test parameters, goes up the control of resolving that realizes the guidance rule at mission computer (5);
4) the guidance rule is resolved required angle, speed, guiding control signal and is generated by mathematics emulator in kind, and be defeated by mission computer (5);
5) simulation work station (3) is passed to radioecho signal simulator (2) through real-time net with the elevation information of aircraft;
6) radioecho signal simulator (2) transmitting and simulating corresponding radioecho signal and give radio altimeter (4) according to radio altimeter (4) from the elevation information that real-time net (1) collects;
7) radio altimeter (4) obtains height value through mixing, and then gives mission computer (5) this height value, and mission computer (5) is given rudder system (6) through resolving the control rudder face signal that draws aircraft;
8) simulation work station (3) passes through the feedback signal that the A/D conversion equipment is gathered rudder system (6), thereby accomplishes the closed-loop simulation of total system.
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| CN108051787A (en) * | 2017-12-05 | 2018-05-18 | 上海无线电设备研究所 | A kind of missile-borne radar flying test method |
| CN108919671A (en) * | 2018-06-29 | 2018-11-30 | 西安现代控制技术研究所 | One kind is for realizing more simulation equipment real-time synchronized control methods |
| CN109634141A (en) * | 2019-02-02 | 2019-04-16 | 帆美航空科技(北京)有限公司 | A kind of medium-and-large-sized unmanned plane semi-physical simulation method and system that Open-closed-loop combines |
| CN109992897B (en) * | 2019-04-03 | 2022-11-22 | 西安飞机工业（集团）有限责任公司 | Radio altimeter simulation method for ground proximity warning equipment |
| CN112558495B (en) * | 2020-11-27 | 2022-04-22 | 中国人民解放军火箭军工程大学 | Anti-interference semi-physical simulation system and method for radar altimeter |
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| US5786790A (en) * | 1997-02-27 | 1998-07-28 | Northrop Grumman Corporation | On-the-fly accuracy enhancement for civil GPS receivers |
| CN101046387A (en) * | 2006-08-07 | 2007-10-03 | 南京航空航天大学 | Scene matching method for raising navigation precision and simulating combined navigation system |
| CN201001127Y (en) * | 2006-12-27 | 2008-01-02 | 中国科学院上海光学精密机械研究所 | Full-digital space optical communication array signal diversity receiving system |
| CN201266242Y (en) * | 2007-12-27 | 2009-07-01 | 中国人民解放军空军工程大学 | Semi-physical simulation device for measuring height of low altitude depopulated drive flying vehicle |
| CN201887775U (en) * | 2010-12-23 | 2011-06-29 | 江西洪都航空工业集团有限责任公司 | Simulation system for radio altitude echoed signals |
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Application publication date: 20110817 Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000184 Denomination of invention: System and method for simulating radio altitude echo signal Granted publication date: 20120926 License type: Exclusive License Record date: 20140714 |
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Effective date of registration: 20160114 Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co., Ltd. |