CN102156411B - System and method for simulating radio altitude echo signal - Google Patents

Abstract

The invention discloses a radio height echo signal simulation system, which is characterized in that the physical mathematical simulator, the radio echo signal simulator, and the simulation workstation are respectively connected to the real-time network, the physical mathematical simulator is connected with a task computer, and the radio echo signal simulation The radio altimeter is connected with the radio altimeter, the radio altimeter is connected with the mission computer, the mission computer is connected with the rudder system, the output terminal of the rudder system is connected with the input terminal of the simulation workstation, and the output terminal of the simulation workstation is connected with the input terminal of the mission computer. The output of the mission computer is connected to the input of the telemetry data collector. Provide real-time analog echo signals and clutter interference signals to the open-loop or closed-loop FM-CW system radio altimeter in the hardware-in-the-loop simulation system, so that the simulation mode is closer to the actual system, the result is more credible, and the cost is low. Variable control experiments are more convenient.

Description

A radio height echo signal simulation system and method

technical field

The invention relates to a simulation method for simulating echo signals, in particular to a radio height echo signal simulation system and method.

Background technique

The radio altimeter plays a very important role in the combat use of aircraft. During the sea-skimming flight of the aircraft, the radio altimeter is required to provide the aircraft guidance and control system with real-time flight altitude information, and the aircraft control system controls the aircraft to make the aircraft fly according to the predetermined route. When flying at a lower altitude, a radio altimeter with high measurement accuracy and a small ranging range is required. Therefore, the performance of the radio altimeter must be strictly tested and verified to test its working ability in various states. In order to realize this test work, in the traditional FM-CW system radio altimeter performance test, it is often carried out through actual aircraft test and aircraft flight test, all of which use actual systems or components, although the system prototype can be arbitrarily close to The final system configuration, its physical simulation model is also close to the actual system, and the simulation results are credible. However, this kind of actual flight test is limited by the flight route, and it is impossible to test all the states of the radio altimeter during combat, and it is also impossible to complete the inspection under the limit state. Moreover, the cost is high, and it is inconvenient to do variable control experiments. In the laboratory, by simulating the echo signal of the radio altimeter, the radio altimeter can be tested in various states. At present, the performance test of the FM-CW system radio altimeter is basically based on the static test of fixed point and fixed altitude, but it is difficult to verify the dynamic index and dynamic performance of the corresponding radio altimeter.

Contents of the invention

The purpose of the invention is to provide real-time analog echo signal and clutter interference signal to the open-loop or closed-loop FM-CW system radio altimeter in the hardware-in-the-loop simulation system, so that the simulation mode is closer to the actual system and the simulation result is better. Credible, and low cost, variable control experiment is more convenient.

In order to achieve the above object, the present invention adopts the following technical solutions, a radio height echo signal simulation system, characterized in that, a physical mathematical simulator, a radio echo signal simulator, and a simulation workstation are connected to the real-time network respectively, and the physical mathematical simulator and The mission computer is connected, the radio echo signal simulator is connected with the radio altimeter, the radio altimeter is connected with the mission computer, the mission computer is connected with the rudder system, the output terminal of the rudder system is connected with the input terminal of the simulation workstation, and the output terminal of the simulation workstation It is connected with the input end of the mission computer, and the output end of the mission computer is connected with the input end of the telemetry data collector.

A radio height echo signal simulation method, comprising the following steps:

1) Connect the mission computer, rudder system and radio altimeter into the hardware-in-the-loop simulation test system;

2) Solve the dynamic model and kinematic model of the aircraft on the simulation workstation;

3) The airborne analog fire control system binds the test mission data to the mission computer according to the test parameters, and realizes the calculation and control of the guidance law on the mission computer;

4) The angle, speed, and guidance control signals required for the guidance law calculation are generated by the physical mathematical simulator and sent to the mission computer;

5) The simulation workstation transmits the altitude information of the aircraft to the radio echo signal simulator through the real-time network;

6) The radio echo signal simulator simulates the corresponding radio echo signal and sends it to the radio altimeter according to the transmission signal of the radio altimeter and the altitude information collected from the real-time network;

7) The radio altimeter obtains the altitude value through frequency mixing, and then sends the altitude value to the mission computer, and the mission computer obtains the control surface signal of the aircraft through calculation and sends it to the rudder system;

8) The simulation workstation collects the feedback signal of the rudder system through the A/D conversion device, thereby completing the closed-loop simulation of the entire system.

The present invention has the advantages that in the semi-physical simulation test, the radio height echo signal under the corresponding height can be simulated in real time according to the information such as the height, sea and land status provided by the simulation workstation and the transmission signal of the radio altimeter. Provide controllable radio altitude echo signals for the test, and conduct tests on the radio altimeter in various states in the laboratory state.

Description of drawings

Fig. 1 is a schematic block diagram of the hardware-in-the-loop simulation test of the closed-loop radio altimeter of the present invention.

Fig. 2 is the test schematic diagram of open-loop radio altimeter index of the present invention.

In the figure: 1-real-time network, 2-radio echo signal simulator, 3-simulation workstation, 4-radio altimeter, 5-mission computer, 6-rudder system, 7-physical mathematical simulator, 8-telemetry data acquisition device.

Detailed ways

Below in conjunction with accompanying drawing and embodiment the present invention will be further described, referring to Fig. 1, a kind of radio height echo signal simulation system, physical object mathematical simulator 7, radio echo signal simulator 2, emulation workstation 3 connect real-time network 1 respectively, The physical mathematical simulator 7 is connected with the task computer 5, the radio echo signal simulator 2 is connected with the radio altimeter 4, the radio altimeter 4 is connected with the task computer 5, the task computer 5 is connected with the rudder system 6, and the output of the rudder system 6 The terminal is connected with the input terminal of the simulation workstation 3, the output terminal of the simulation workstation 3 is connected with the input terminal of the task computer 5, and the output terminal of the task computer 5 is connected with the input terminal of the telemetry data collector 8.

A radio height echo signal simulation method, comprising the following steps:

1) Connect mission computer 5, rudder system 6 and radio altimeter 4 into hardware-in-the-loop simulation test system;

2) Solve the dynamic model and kinematic model of the aircraft on the simulation workstation 3;

3) The airborne simulated fire control system binds the test mission data to the mission computer 5 according to the test parameters, and realizes the calculation and control of the guidance law on the mission computer 5;

4) The angle, speed, and guidance control signals required for solving the guidance law are generated by the physical mathematical simulator 7 and sent to the mission computer 5;

5) The simulation workstation 3 transmits the altitude information of the aircraft to the radio echo signal simulator 2 through the real-time network 1;

6) The radio echo signal simulator 2 simulates the corresponding radio echo signal and sends it to the radio altimeter 4 according to the transmission signal of the radio altimeter and the altitude information collected from the real-time network;

7) The radio altimeter 4 obtains the altitude value through frequency mixing, and then sends the altitude value to the mission computer 5, and the mission computer 5 obtains the control surface signal of the aircraft through calculation and sends it to the rudder system 6;

8) The simulation workstation 3 collects the feedback signal of the rudder system through the A/D conversion device, thereby completing the closed-loop simulation of the entire system.

The present invention obtains the altitude data from the real-time network 1, and then the radio echo signal emulator 2 generates corresponding echo signal signals and clutter signals according to the standard (open loop or closed loop) of the radio altimeter 4, and then sends them through the feeder line. Give radio altimeter 4. In order to more realistically simulate echo signals under various conditions, a clutter signal generation system is added to the radio echo signal simulator 2, and its clutter types are wired clutter, sea clutter and other clutter signals. In order to meet the requirements for testing the dynamic indicators of the two radio altimeters, and verify the influence of the altimeter on the performance indicators of the aircraft in various states.

Embodiment 1 :

For the semi-physical simulation test of the closed-loop radio altimeter, see Figure 1, the rudder system 6 and the closed-loop radio altimeter 4 are directly connected to the mission computer 5, and the simulation workstation 3 and the mission computer 5 are connected to form a physical closed-loop simulation system. Solve the dynamics model and kinematics model of aircraft on the simulation workstation 3; According to the combination table, the task computer 5 is bound to test task data before the test, and the simulation workstation 3 sends the signals such as the angle, speed, and guidance control calculated by the solution to Mathematical simulator in kind 7, maths simulator in kind 7 is lost to task computer 5 through interface; Simulation workstation 3 passes the height information of aircraft to radio echo signal simulator 2 through real-time network, and radio echo signal simulator 2 is according to the radio echo signal simulator 2. The emission signal of the altimeter and the altitude information collected from the real-time network simulate the corresponding radio echo signal and send it to the radio altimeter 4, and the height obtained by the radio altimeter 4 is sent to the task computer 5 through the interface; the task computer 5 will get The control signal of the control signal is calculated for the self-guidance rate, and the four control surface signals of the aircraft are obtained and sent to the rudder system 6; at the same time, the feedback signal of the rudder surface of the rudder system 6 is sent to the simulation through the A/D conversion device in the simulation workstation 3. Workstation 3, thus completing the closed-loop simulation of the whole system. The data that task computer 5 produces in the simulation process is collected by telemetry data collector 8;

Embodiment 2 :

The test of the open-loop radio altimeter index, referring to Fig. 2, connects the simulation workstation 3 and the radio echo signal emulator 2 through a real-time network, and connects the radio echo signal emulator 2, the radio altimeter 4, and the telemetry data collector 8 It is directly connected with the mission computer 5 . During the test, the height value is sent to the radio echo signal emulator 2 by the simulation workstation 3, and the radio echo signal emulator 2 simulates the corresponding radio echo signal according to the height value and sends it to the radio altimeter 4, and the radio altimeter 4 passes The difference frequency calculation sends the obtained altitude to the mission computer 5, and the mission computer 5 sends it to the telemetry data collector 8 through the interface. Compare the data sent by the simulation workstation 3 with the data obtained by the telemetry data collector 8 . Thereby the purpose of testing the static index of the radio altimeter 4 is achieved.

Claims (2)

1. A radio height echo signal simulation system is characterized in that a physical mathematical simulator (7), a radio echo signal simulator (2), and a simulation workstation (3) are connected to the real-time network (1) respectively, and the physical mathematical simulation The device (7) is connected with the mission computer (5), the radio echo signal simulator (2) is connected with the radio altimeter (4), the radio altimeter (4) is connected with the mission computer (5), and the mission computer (5) is connected with the mission computer (5). The rudder system (6) is connected, the output end of the rudder system (6) is connected with the input end of the simulation workstation (3), the output end of the simulation workstation (3) is connected with the input end of the mission computer (5), and the mission computer ( The output end of 5) is connected with the input end of the telemetry data collector (8). 2. a kind of method that adopts radio height echo signal emulation system as claimed in claim 1 to carry out the method for radio height echo signal emulation, it is characterized in that: comprise the following steps: 1) Connect the mission computer (5), rudder system (6) and radio altimeter (4) into the hardware-in-the-loop simulation test system; 2) Solve the dynamic model and kinematic model of the aircraft on the simulation workstation (3); 3) The airborne simulated fire control system binds the test mission data to the mission computer (5) according to the test parameters, and realizes the calculation and control of the guidance law on the mission computer (5); 4) The angle, speed, and guidance control signals required for solving the guidance law are generated by the physical mathematical simulator and sent to the mission computer (5); 5) The simulation workstation (3) transmits the altitude information of the aircraft to the radio echo signal simulator (2) through the real-time network; 6) The radio echo signal simulator (2) simulates the corresponding radio echo signal according to the transmission signal of the radio altimeter (4) and the altitude information collected from the real-time network (1) and sends it to the radio altimeter (4) ; 7) The radio altimeter (4) obtains the altitude value through frequency mixing, and then sends the altitude value to the mission computer (5), and the mission computer (5) obtains the control surface signal of the aircraft through calculation and sends it to the rudder system (6 ); 8) The simulation workstation (3) collects the feedback signal of the rudder system (6) through the A/D conversion device, thereby completing the closed-loop simulation of the entire system.

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