Aircraft simulation test system, method, device and storage medium

Abstract

The embodiments of the present application provide an aircraft simulation test system, method, device and storage medium, and relate to the field of aircraft simulation test technology. The system includes: an altimeter simulation test device, which is used to perform echo simulation processing on the transmission signal emitted by the altimeter to obtain a simulated echo signal; an altimeter, which is connected to the altimeter simulation test device, and is used to determine a first altitude based on the transmission signal and the simulated echo signal sent by the altimeter simulation test device; a flight control device, which is connected to the altimeter, and is used to control the flight of the aircraft based on the first altitude. The embodiments of the present application can connect the first altitude of the altimeter to the flight control device, that is, the height measurement data of the altimeter can be involved in the calculation of the flight control program, so as to realize the simulation test of the aircraft under the condition of the participation of the altimeter, and improve the effectiveness and fidelity of the simulation test of the aircraft.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft simulation testing, and more specifically, to an aircraft simulation testing system, method, device and storage medium. Background Art

[0002] Aircraft simulation testing is generally carried out in the form of semi-physical simulation before flight testing. Semi-physical simulation is a simulation technology that introduces part of the simulation object into the simulation loop through physical simulation. It is a simulation technology between mathematical simulation and physical simulation. It has higher credibility and accuracy than pure mathematical simulation and is closer to the final system.

[0003] However, the current aircraft simulation test system still has problems with low effectiveness and realism. Summary of the invention

[0004] The embodiments of the present application provide an aircraft simulation test system, method, device and storage medium for solving the technical problem of how to improve the effectiveness and realism of the aircraft simulation test system.

[0005] In a first aspect, an embodiment of the present application provides an aircraft simulation test system, comprising:

[0006] Altimeter simulation test equipment, used to perform echo simulation processing on the transmission signal emitted by the altimeter to obtain a simulated echo signal;

[0007] an altimeter connected to the altimeter simulation test device, and configured to determine a first altitude based on the transmitted signal and a simulated echo signal sent by the altimeter simulation test device;

[0008] The flight control device is connected to the altimeter and is used to control the flight of the aircraft based on the first altitude sent by the altimeter.

[0009] In a possible implementation, the aircraft simulation test system further includes: a combined navigation device;

[0010] The integrated navigation device is connected to the flight control device and is used to send flight control information to the flight control device; the flight control information includes the second altitude and related flight information; the related flight information includes at least one of the following: flight speed and flight attitude; the first altitude and the second altitude are respectively measured by the altimeter and the integrated navigation device based on the same flight trajectory;

[0011] The flight control device is also used to fuse the first altitude with the second altitude to obtain a fused altitude, and control the flight of the aircraft based on the fused altitude and related flight information.

[0012] In a possible implementation, the altimeter simulation test equipment includes:

[0013] The real-time simulator is used to generate a flight trajectory based on parameter configuration information carried in the flight trajectory generation instruction when receiving the flight trajectory generation instruction, and determine a third altitude and a signal attenuation value based on the flight trajectory;

[0014] The echo simulator is connected to the real-time simulator and the altimeter, and is used to determine the simulated echo signal based on the third altitude sent by the real-time simulator, the signal attenuation value and the transmitting signal sent by the altimeter, and send the simulated echo signal to the altimeter.

[0015] In a possible implementation, the altimeter simulation test device further includes:

[0016] The host computer is connected to the real-time simulator and is used to send a flight trajectory generation instruction and determine the high performance of the altimeter based on the acquired first altitude and the third altitude sent by the real-time simulator.

[0017] In one possible implementation, the real-time simulator is specifically used to generate a flight trajectory based on parameter configuration information through a target mathematical simulation model, determine a third altitude based on position information in the flight trajectory, and determine a signal attenuation value based on the third altitude.

[0018] In a possible implementation, the real-time simulator is connected to the flight control device for clock synchronization with the flight control device, and receives the first altitude sent by the flight control device and sends the first altitude to a host computer.

[0019] In a possible implementation, the echo simulator includes a scene selection module, which is used to select a scene, and the scene includes at least one of the following: ground surface, water surface;

[0020] The echo simulator is specifically used to perform echo simulation processing on the transmission signal based on the third height, the signal attenuation value and the selected scene to obtain a simulated echo signal; the echo simulation processing includes at least one of the following: delay processing, signal attenuation processing, and scattering information modulation;

[0021] Among them, the delay processing is to delay the transmission signal based on the third height, the signal attenuation processing is to attenuate the transmission signal based on the signal attenuation value, and the scattering information modulation is to scatter modulate the transmission signal based on the selected scene.

[0022] In one possible implementation, the host computer is specifically used to determine that the measurement accuracy of the altimeter meets the performance requirements if the difference between the first altitude and the third altitude is within a first preset range; if the difference between the first altitude and the preset altitude is within a second preset range, then determine that the measurement capability of the altimeter meets the performance requirements.

[0023] In a second aspect, an embodiment of the present application provides an aircraft simulation test method, which is applied to the aircraft simulation test system of the first aspect, including:

[0024] Based on the first altitude, the flight of the aircraft is controlled; the first altitude is determined by the altimeter based on the transmission signal and the simulated echo signal, and the simulated echo signal is obtained by the altimeter simulation test equipment performing echo simulation processing on the transmission signal emitted by the altimeter.

[0025] In a possible implementation, controlling the flight of the aircraft based on the first altitude includes:

[0026] Acquire flight control information sent by the integrated navigation device; the flight control information includes the second altitude and related flight information; the related flight information includes at least one of the following: flight speed, flight attitude;

[0027] The first height and the second height are fused to obtain a fused height;

[0028] Control the flight of the aircraft based on the fused altitude and related flight information.

[0029] In a third aspect, an embodiment of the present application provides an aircraft simulation test device, comprising:

[0030] The control module is used to control the flight of the aircraft based on a first altitude; the first altitude is determined by the altimeter based on a transmission signal and a simulated echo signal, and the simulated echo signal is obtained by the altimeter simulation test equipment performing echo simulation processing on the transmission signal emitted by the altimeter.

[0031] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which implements the steps of the method of the second aspect when the computer program is executed by a processor.

[0032] The beneficial effects of the technical solution provided by the embodiment of the present application are:

[0033] The altimeter of the embodiment of the present application is connected to the altimeter simulation test device. Since the altimeter simulation test device can perform echo simulation processing on the transmission signal emitted by the altimeter to obtain a simulated echo signal, the altimeter can determine the first altitude based on the transmission signal and the simulated echo signal sent by the altimeter simulation test device. The altimeter is connected to the flight control device, so that the flight control device can control the flight of the aircraft based on the first altitude. Therefore, the embodiment of the present application can send the first altitude of the altimeter to the flight control device, that is, the height measurement data of the altimeter can be involved in the calculation of the flight control program, so as to realize the simulation test of the aircraft under the condition of the altimeter participating, and improve the effectiveness and fidelity of the simulation test of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in describing the embodiments of the present application are briefly introduced below.

[0035] Figure 1 A schematic diagram of the structure of a first aircraft simulation test system provided in an embodiment of the present application;

[0036] Figure 2 A schematic diagram of the structure of a second aircraft simulation test system provided in an embodiment of the present application;

[0037] Figure 3 A schematic diagram of the structure of an altimeter simulation test device provided in an embodiment of the present application;

[0038] Figure 4 A schematic diagram of the structure of a third aircraft simulation test system provided in an embodiment of the present application;

[0039] Figure 5 A flowchart of an aircraft simulation test method provided in an embodiment of the present application;

[0040] Figure 6 A schematic diagram of the structure of an aircraft simulation test device provided in an embodiment of the present application;

[0041] Figure 7 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application.

[0042] Reference numerals:

[0043] 10- Aircraft simulation test system;

[0044] 110-altimeter simulation test equipment, 111-real-time simulator, 112-echo simulator, 113-host computer, 114-DC power supply;

[0045] 120 - altimeter;

[0046] 130-Flight control equipment;

[0047] 140-Combined navigation equipment. DETAILED DESCRIPTION

[0048] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0049] It will be understood by those skilled in the art that, unless specifically stated, the singular forms "one", "said", and "the" used herein may also include plural forms. It should be further understood that the terms "including" and "comprising" used in the embodiments of the present application refer to that the corresponding features can be implemented as the presented features, information, data, steps, operations, elements and / or components, but do not exclude the implementation as other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. It should be understood that when we say that an element is "connected" or "coupled" to another element, the one element may be directly connected or coupled to the other element, or it may refer to that the one element and the other element establish a connection relationship through an intermediate element. In addition, the "connection" or "coupling" used herein may include wireless connection or wireless coupling. The term "and / or" used herein indicates at least one of the items defined by the term, for example, "A and / or B" indicates that it is implemented as "A", or is implemented as "A", or is implemented as "A and B".

[0050] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0051] First, several terms involved in this application are introduced and explained:

[0052] Radio altimeter: A device that measures the height of an object above the ground;

[0053] Radio altimeter target echo simulator: a device used to simulate the radio altimeter's target height echo signal on the ground or sea surface;

[0054] VxWorks real-time simulator: a simulator that uses the VxWorks real-time operating system;

[0055] Semi-physical simulation: a simulation technology that introduces part of the simulation object into the simulation loop through physical simulation;

[0056] Supersonic cruise target: A training device capable of achieving supersonic cruise.

[0057] In the relevant technology, the radio altimeter (altimeter for short) is a key component for obtaining altitude information during the flight of a supersonic cruise target (target for short), and is mainly composed of a transmitting antenna, a receiving antenna, a transceiver component, a signal processing component, an electrical interface, etc. During the flight of the target, the altimeter transmits radio wave signals to the ground or sea surface through the transmitting antenna. A part of the radio wave signals is reflected by the ground or sea surface and received by the receiving antenna. The signal processing component calculates the distance between the aircraft and the ground or sea surface based on information such as the signal difference frequency and time delay.

[0058] The altimeter's height measurement capability and height measurement accuracy are important parameter indicators of the target control system. The height measurement capability refers to the range of relative altitudes measured by the altimeter, and the height measurement accuracy refers to the error of the altimeter in measuring relative altitudes. The target needs to be able to adapt to various types of complex flight environments such as plateaus, flat land, and sea surfaces. The altimeter radar signal faces different multipath effects in different scenarios, and its echo signal varies greatly, which will have a great impact on the altimeter's high measurement performance, and then directly affect the target flight stability. Therefore, before conducting a target flight test, it is necessary to test the altimeter's high measurement performance and conduct a semi-physical simulation test of the target in combination with the altimeter.

[0059] However, most of the existing semi-physical simulation tests of targets cannot be directly connected to the altimeter, so that the height measurement data of the altimeter cannot be used in the simulation experiment, which greatly reduces the effectiveness and realism of the simulation test of the aircraft.

[0060] The aircraft simulation test system, method, device and storage medium provided in this application are intended to solve the above technical problems in the prior art.

[0061] See also Figure 1 As shown, the embodiment of the present application provides a structural schematic diagram of a first aircraft simulation test system 10. The aircraft simulation test system 10 includes: an altimeter simulation test device 110, an altimeter 120 and a flight control device 130.

[0062] The altimeter simulation test device 110 is used to perform echo simulation processing on the transmission signal emitted by the altimeter 120 to obtain a simulated echo signal.

[0063] The altimeter 120 is connected to the altimeter simulation test device 110 , and the altimeter 120 is used to determine the first altitude based on the transmission signal and the simulated echo signal sent by the altimeter simulation test device 110 .

[0064] The flight control device 130 is connected to the altimeter 120 , and is used to control the flight of the aircraft based on the first altitude sent by the altimeter 120 .

[0065] Optionally, the altimeter 120 continuously sends a transmission signal and continuously sends the first altitude to the flight control device 130, so that the altimeter 120 can send the altitude data formed by the first altitude under different flight conditions to the flight control device 130 in real time, so that the altitude data of the altimeter 120 can be connected to the flight control device 130 to participate in controlling the flight altitude of the aircraft.

[0066] The altimeter 120 of the embodiment of the present application is connected to the altimeter simulation test device 110. Since the altimeter simulation test device 110 can perform echo simulation processing on the transmission signal sent by the altimeter 120 to obtain a simulated echo signal, the altimeter 120 can determine the first altitude based on the transmission signal and the simulated echo signal sent by the altimeter simulation test device 110. The altimeter 120 is connected to the flight control device 130, so that the flight control device 130 can control the flight of the aircraft based on the first altitude. Therefore, the embodiment of the present application can send the first altitude of the altimeter 120 to the flight control device 130, that is, the height measurement data of the altimeter 120 can be involved in the calculation of the flight control program, so as to realize the simulation test of the aircraft under the condition of the participation of the altimeter 120, and improve the effectiveness and fidelity of the simulation test of the aircraft.

[0067] See also Figure 2 As shown, the embodiment of the present application provides a structural schematic diagram of a second aircraft simulation test system 10. The aircraft simulation test system 10 also includes: an integrated navigation device 140. The integrated navigation device 140 is connected to the flight control device 130, and is used to send flight control information to the flight control device 130; the flight control information includes a second altitude and related flight information; the related flight information includes at least one of the following: flight speed, flight attitude; the first altitude and the second altitude are respectively measured by the altimeter and the integrated navigation device based on the same flight trajectory.

[0068] The flight control device 130 is further used to fuse the first altitude with the second altitude to obtain a fused altitude, and control the flight of the aircraft based on the fused altitude and related flight information.

[0069] The flight control device 130 can generate a flight control instruction based on the fused altitude and related flight information; the flight control instruction is used to control the flight attitude of the aircraft. The aircraft can be a rocket, a target, etc.

[0070] Optionally, the first altitude and the second altitude are respectively altitudes measured by the altimeter 120 and the integrated navigation device 140 based on the same flight track. The first altitude and the second altitude are fused to obtain a fused altitude. The fusion process may be weighted processing of the two altitudes, and different weighting coefficients are assigned to obtain the fused altitude.

[0071] The embodiment of the present application can send the altitude data of the altimeter 120 to the flight control device 130, realize the fusion of altitude information of the altimeter 120 and the integrated navigation device 140, and improve the effectiveness and realism of the simulation test of the aircraft.

[0072] Optionally, the altimeter simulation test device 110 can generate a flight trajectory, the altimeter simulation test device 110 can transmit data with the combined navigation device 140 through a satellite navigation signal simulator, the satellite navigation simulator can convert the flight trajectory to obtain flight conversion information, the combined navigation device 140 receives the flight conversion information to generate flight control information, and the process of receiving the flight conversion information by the combined navigation device 140 is equivalent to the measurement of the flight trajectory by the combined navigation device 140, and the second altitude in the flight control information can be obtained.

[0073] In the related art, the conventional detection method of the radio altimeter is static detection, which simulates the ground echo delay according to the propagation delay of the signal in the delay line. The existing altimeter test system is usually based on preset parameter conditions. The echo data is calculated according to the predetermined parameters before the test, and the land or sea echo simulation is realized through continuous playback of the simulator to verify the high performance of the radio altimeter. The combination of field tests and actual aircraft flight can provide real plateau, flat land or sea target echoes, but this method has high requirements for test equipment, and will also extend the test cycle and increase the development cost.

[0074] Through research, it is found that the radio altimeter test system can send altitude simulation control instructions to the exciter through the control and analysis module. The altitude simulation control instructions include altitude value and corresponding attenuation value instructions. The exciter generates and sends altitude simulation signals to the radio altimeter. The control and analysis module receives the radio altimeter test data and completes the radio altimeter test. At the same time, the continuous wave radio altimeter test device can set any altitude within the height measurement range through the host computer software test interface, and the test device automatically realizes the detection of the continuous wave radio altimeter test performance.

[0075] However, the above existing methods are unable to verify the real-time high performance of the altimeter, and are unable to truly simulate the working state of the altimeter of the target under different dynamic flight conditions.

[0076] Based on the above considerations, the design of the altimeter simulation test equipment 110 in the embodiment of the present application can realize the simulation test of the altimeter under different dynamic flight conditions.

[0077] See also Figure 3 As shown, the embodiment of the present application provides a structural schematic diagram of an altimeter simulation test device 110. The altimeter simulation test device 110 includes: a real-time simulator 111 and an echo simulator 112.

[0078] The real-time simulator 111 is used to generate a flight trajectory based on parameter configuration information carried in the flight trajectory generation instruction when receiving the flight trajectory generation instruction, and determine the third altitude and the signal attenuation value based on the flight trajectory;

[0079] The echo simulator 112 is connected to the real-time simulator 111 and the altimeter 120 . The echo simulator 112 is used to determine the simulated echo signal based on the third altitude sent by the real-time simulator 111 , the signal attenuation value and the transmission signal sent by the altimeter 120 , and send the simulated echo signal to the altimeter 120 .

[0080] Optionally, the altimeter simulation test device 110 of the embodiment of the present application can determine a simulated echo signal through the real-time simulator 111 and the echo simulator 112, so that the altimeter 120 can obtain height measurement data.

[0081] Optionally, the aircraft simulation test system 10 also includes a satellite navigation signal simulator, which is connected to the real-time simulator 111 and the combined navigation device 140, and is used to convert the flight trajectory sent by the real-time simulator 111 to obtain flight conversion information and send it to the combined navigation device 140, so that the combined navigation device 140 generates flight control information based on the flight conversion information.

[0082] Optionally, the satellite navigation signal simulator is connected to the real-time simulator 111 via an optical fiber, and the satellite navigation signal simulator is connected to the integrated navigation device 140 via a radio frequency feeder.

[0083] See also Figure 3 As shown, the altimeter simulation test device 110 further includes: a host computer 113 .

[0084] The host computer 113 is connected to the real-time simulator 111 , and is used to send a flight trajectory generation instruction, and determine the high performance of the altimeter 120 based on the acquired first altitude and the third altitude sent by the real-time simulator 111 .

[0085] Optionally, the altimeter 120 is connected to the real-time simulator 111, and is used to send the first altitude to the real-time simulator 111, so that the real-time simulator 111 sends the first altitude to the host computer 113. As another example, the altimeter 120 is connected to the host computer 113, and is used to send the first altitude to the host computer 113.

[0086] In some embodiments, the real-time simulator 111 is specifically used to generate a flight trajectory based on parameter configuration information through a target mathematical simulation model, determine a third height based on position information in the flight trajectory, and determine a signal attenuation value based on the third height.

[0087] Optionally, the parameter configuration information is used to generate a corresponding flight trajectory for the target mathematical simulation model. By configuring different parameter configuration information on the host computer, flight trajectories under different flight conditions can be obtained. The parameter configuration information can be used to configure interference conditions, and the generated flight trajectories are mostly typical flight trajectories.

[0088] Optionally, the real-time simulator 111 is a VxWorks real-time simulator, and the target mathematical simulation model is a target mathematical trajectory simulation model calculation software.

[0089] The embodiment of the present application utilizes the mathematical simulation model of the target, and provides the third height and signal attenuation value of the target under different dynamic conditions through the VxWorks real-time simulator to realize the real-time high performance verification of the altimeter. Moreover, the mathematical simulation model of the target in the embodiment of the present application can generate flight trajectories under various interference conditions, and can test the real-time height measurement capability and height measurement accuracy of the altimeter under different dynamic conditions.

[0090] See also Figure 4 As shown, the present embodiment provides a structural diagram of a third aircraft simulation test system 10. Figure 4 As shown, the host computer 113 includes main control software and data processing software, the real-time simulator 111 can adopt a VxWorks real-time simulator, the echo simulator 112 can adopt a radio altimeter target echo simulator, the altimeter 120 adopts a radio altimeter, and the DC power supply 114 is a DC regulated power supply.

[0091] See also Figure 4 As shown, the real-time simulator 111 is connected to the flight control device 130 , and is used to perform clock synchronization with the flight control device 130 , and receive the first altitude sent by the flight control device 130 and send the first altitude to the host computer 113 .

[0092] Specifically, the real-time simulator 111 may send the flight trajectory to the flight control device 130 , the flight control device 130 may send the flight trajectory to the integrated navigation device 140 , and the integrated navigation device 140 may determine the second altitude in the flight control information based on the flight trajectory.

[0093] The altimeter simulation test device 110 of the embodiment of the present application is connected to the flight control device 130 and can perform clock synchronization with the flight control device 130. Furthermore, the real-time simulator 111 and the flight control device 130 can perform clock synchronization and information exchange to ensure the effectiveness of the simulation test of the aircraft.

[0094] In some embodiments, the echo simulator 112 includes a scene selection module, and the scene selection module is used to select a scene, and the scene includes at least one of the following: ground surface and water surface.

[0095] The echo simulator 112 is specifically used to perform echo simulation processing on the transmitted signal based on the third height, the signal attenuation value and the selected scene to obtain a simulated echo signal; the echo simulation processing includes at least one of the following: delay processing, signal attenuation processing, and scattering information modulation; wherein, the delay processing is based on the third height to delay the transmitted signal, the signal attenuation processing is based on the signal attenuation value to attenuate the transmitted signal, and the scattering information modulation is based on the selected scene to scatter modulate the transmitted signal.

[0096] Optionally, the water surface may be a sea surface or a river surface. For example, when a transmitted signal encounters the ground or the sea surface, the signal will be scattered differently, and modulation processing can be performed on the scattering of the transmitted signal according to the scene. It takes a certain amount of time for the transmitted signal to be reflected from the ground or the sea surface, so the received echo signal will have a delay, so the transmitted signal needs to be delayed. The transmitted signal will be attenuated during the transmission process, so signal attenuation processing is required.

[0097] Optionally, the altimeter 120 is specifically used to determine the signal difference frequency information and the delay information based on the transmission signal and the simulated echo signal, and determine the first altitude based on the signal difference frequency information and the delay information;

[0098] Among them, by comparing the transmission signal and the simulated echo signal, signal difference frequency information and delay information can be obtained. The signal difference frequency information indicates the difference in frequency between the simulated echo signal and the transmission signal, and the delay information indicates the delay in signal transmission time between the simulated echo signal and the transmission signal. There will be a certain frequency difference between the frequency of the simulated echo signal and the frequency of the transmission signal, forming the signal difference frequency information. There will be a time difference between the transmission time of the transmission signal sent by the altimeter 120 and the reception time of the corresponding simulated echo signal, forming the delay information.

[0099] Specifically, the transmission signal is a radio signal, and the altimeter 120 is a radio altimeter. The altimeter 120 continuously sends the transmission signal to the echo simulator 112 through the transmission feeder.

[0100] In some embodiments, the host computer 113 is specifically used to determine that the measurement accuracy of the altimeter 120 meets the performance requirements if the difference between the first altitude and the third altitude is within a first preset range; if the difference between the first altitude and the preset altitude is within a second preset range, then determine that the measurement capability of the altimeter 120 meets the performance requirements.

[0101] Optionally, the preset altitude is a standard altitude preset by a technician for measuring the flight altitude of the altimeter 120 .

[0102] The embodiment of the present application generates flight trajectories under various interference conditions through a target mathematical simulation model, and can test the real-time height measurement capability and height measurement accuracy of the altimeter 120 under different dynamic conditions.

[0103] Optionally, the first preset range and the second preset range can be set according to the experience of the technicians. When the first height is not much different from the third height, it means that the measurement accuracy of the altimeter 120 is high. When the first height is not much different from the preset height, it means that the first height of the altimeter 120 does not deviate from the standard height and is within the height measurement capability of the altimeter 120, meeting the height measurement capability requirements.

[0104] See also Figure 4 As shown, the main control software of the host computer 113 is used to send a flight trajectory generation instruction to the real-time simulator 111. The data processing software of the host computer 113 is used to determine the measurement performance of the altimeter 120 based on the acquired first altitude and third altitude. If the difference between the first altitude and the third altitude is within a first preset range, it is determined that the measurement accuracy of the altimeter 120 meets the performance requirements; if the difference between the first altitude and the preset altitude is within a second preset range, it is determined that the measurement capability of the altimeter 120 meets the performance requirements.

[0105] See also Figure 4 As shown, the altimeter simulation test system 10 further includes a DC power supply 114. The DC power supply 114 is connected to the altimeter 120 and is used to supply power to the altimeter 120.

[0106] Optionally, the DC power supply 114 may be a DC regulated power supply, for example, the altimeter 120 may be supplied with a voltage of 28V.

[0107] based on Figure 4 The third aircraft simulation test system 10 shown in the figure, the embodiment of the present application provides an implementation method for altimeter single machine performance test:

[0108] (1) A DC regulated power supply supplies power to the altimeter, which continuously sends a transmit signal to the radio altimeter target echo simulator through a transmit feeder.

[0109] (2) Sending a target flight trajectory generation instruction to the VxWorks real-time simulator through the master control software of the host computer 113;

[0110] (3) After the simulation starts, the VxWorks real-time simulator sends the third altitude and signal attenuation value calculated by the target mathematical simulation model to the radio altimeter target echo simulator through the serial port;

[0111] (4) The radio altimeter target echo simulator performs ground or sea surface scattering information modulation and delay processing based on the received transmission signal, the third altitude and the signal attenuation value, and sends the simulated echo signal to the radio altimeter through the receiving feeder;

[0112] (5) The radio altimeter calculates the current first altitude based on the difference frequency information and delay information between the transmitted signal and the simulated echo signal, and sends it to the VxWorks real-time simulator through the serial port;

[0113] (6) The data processing software of the host computer 113 receives the third altitude and the first altitude sent back by the VxWorks real-time simulator, and performs data processing and altimeter performance analysis.

[0114] join Figure 4 As shown in the figure, the target semi-physical simulation test is carried out on the basis of the above-mentioned altimeter single machine performance test to conduct the following simulation test:

[0115] (1) The real-time simulator 111 performs clock synchronization and information exchange with the flight control device 130.

[0116] (2) The altimeter 120 sends the altitude data to the flight control device 130 through the serial port, thereby realizing the fusion of altitude information between the altimeter 120 and the integrated navigation device 140.

[0117] Specifically, the aircraft simulation test system 10 is a semi-physical simulation system, including onboard equipment and simulation equipment. The onboard equipment includes a flight control computer, a combined navigation device 140, an altimeter 120, etc.; the simulation equipment includes a satellite navigation signal simulator, a real-time simulator 111, an echo simulator 112, etc.

[0118] The embodiment of the present application utilizes target mathematical trajectory simulation model calculation software, and provides the flight altitude trajectory and signal attenuation of the target under different scenarios and dynamic conditions through the VxWorks real-time simulator; the ground or sea surface scattering information modulation and delay processing are performed through the radio altimeter target echo simulator, and the altimeter 120 height measurement data can also be connected to the target semi-physical simulation system, forming a stable and efficient target radio altimeter real-time simulation test system, which can be used for a long time under laboratory conditions.

[0119] The altimeter 120 of the embodiment of the present application is connected to the flight control device 130 of the target through the serial port, so that the height measurement data of the altimeter 120 and the positioning height data of the combined navigation device 140 are simultaneously involved in the calculation of the flight control program, and the semi-physical simulation test of the target under the condition of the altimeter 120 participating is realized, thereby improving the effectiveness and fidelity of the semi-physical simulation test of the target. Moreover, the altimeter performance measurement verification and the semi-physical simulation test of the target in the embodiment of the present application have accurate and reliable test results.

[0120] See also Figure 5 As shown, the present invention provides a flowchart of an aircraft simulation test method. The aircraft simulation test method is applied to the aircraft simulation test system 10 of the present invention, and includes: step S501.

[0121] S501. Control the flight of the aircraft based on a first altitude. The first altitude is determined by the altimeter 120 based on a transmission signal and a simulated echo signal. The simulated echo signal is obtained by the altimeter simulation test device 110 performing echo simulation processing on the transmission signal emitted by the altimeter 120.

[0122] The aircraft simulation test method in the embodiment of the present application uses the flight control device 130 as the execution end.

[0123] In some embodiments, in step S501, based on the first altitude, controlling the flight of the aircraft includes:

[0124] (1) Acquiring flight control information sent by the integrated navigation device 140; the flight control information includes the second altitude and related flight information; the related flight information includes at least one of the following: flight speed and flight attitude;

[0125] (2) Fusing the first height and the second height to obtain a fused height;

[0126] (3) Control the flight of the aircraft based on the fused altitude and related flight information.

[0127] The aircraft simulation test method of the embodiment of the present application is applied to the aircraft simulation test system 10 of the embodiment of the present application. For the contents not described in detail in the aircraft simulation test method, please refer to the above-mentioned aircraft simulation test system 10.

[0128] See also Figure 6 As shown, the present invention provides a schematic diagram of the structure of an aircraft simulation test device 60. The aircraft simulation test device 60 includes: a control module 610.

[0129] The control module 610 is used to control the flight of the aircraft based on a first altitude; the first altitude is determined by the altimeter 120 based on a transmission signal and a simulated echo signal, and the simulated echo signal is obtained by the altimeter simulation test equipment 110 performing echo simulation processing on the transmission signal emitted by the altimeter 120.

[0130] Optionally, the control module 610 is further configured to fuse the first altitude with the second altitude to obtain a fused altitude, and control the flight of the aircraft based on the fused altitude and related flight information.

[0131] Optionally, the control module 610 is further configured to perform clock synchronization with the real-time simulation machine 111 and send the first height to the real-time simulation machine 111 .

[0132] The device of the embodiments of the present application can execute the method provided by the embodiments of the present application, and the implementation principles are similar. The actions performed by each module in the device of each embodiment of the present application correspond to the steps in the method of each embodiment of the present application. For the detailed functional description of each module of the device, please refer to the description in the corresponding method shown in the previous text, which will not be repeated here.

[0133] An embodiment of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory, and the processor executes the above computer program to implement the steps of the method of the embodiment of the present application.

[0134] See also Figure 7 As shown, the present application embodiment provides a structural diagram of an electronic device 4000. Figure 7 As shown, the electronic device 4000 includes: a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, such as through a bus 4002. Optionally, the electronic device 4000 may also include a transceiver 4004, which may be used for data interaction between the electronic device and other electronic devices, such as data transmission and / or data reception. It should be noted that in actual applications, the transceiver 4004 is not limited to one, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present application.

[0135] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array) or other programmable logic devices, transistor logic devices, hardware components or any combination thereof. It may implement or execute various exemplary logic blocks, modules and circuits described in conjunction with the disclosure of this application. Processor 4001 may also be a combination that implements computing functions, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, etc.

[0136] The bus 4002 may include a path to transmit information between the above components. The bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus. The bus 4002 may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 7 Only one thick line is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0137] The memory 4003 may be a ROM (Read Only Memory) or other types of static storage devices that can store static information and instructions, a RAM (Random Access Memory) or other types of dynamic storage devices that can store information and instructions, or an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory) or other optical disk storage, optical disk storage (including compressed optical disk, laser disk, optical disk, digital versatile disk, Blu-ray disk, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium that can be used to carry or store computer programs and can be read by a computer, without limitation herein.

[0138] The memory 4003 is used to store the computer program for executing the embodiment of the present application, and the execution is controlled by the processor 4001. The processor 4001 is used to execute the computer program stored in the memory 4003 to implement the steps shown in the above method embodiment.

[0139] An embodiment of the present application provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the steps of the method of the embodiment of the present application are implemented.

[0140] The computer-readable medium of the present application may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0141] In an embodiment of the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, device, or device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, device, or device. The program code contained on a computer-readable medium may be transmitted using any suitable medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination of the above.

[0142] The embodiment of the present application also provides a computer program product, including a computer program, which can implement the steps and corresponding contents of the aforementioned method embodiment when executed by a processor.

[0143] It should be understood that, although each operation step is indicated by arrows in the flowchart of the embodiment of the present application, the implementation order of these steps is not limited to the order indicated by the arrows. Unless clearly stated herein, in some implementation scenarios of the embodiment of the present application, the implementation steps in each flowchart can be performed in other orders according to demand. In addition, some or all of the steps in each flowchart may include multiple sub-steps or multiple stages based on actual implementation scenarios. Some or all of these sub-steps or stages may be executed at the same time, and each sub-step or stage in these sub-steps or stages may also be executed at different times respectively. In different scenarios of execution time, the execution order of these sub-steps or stages may be flexibly configured according to demand, and the embodiment of the present application does not limit this.

[0144] In the embodiments of the present application, the term "module" or "unit" refers to a computer program or a part of a computer program that has a predetermined function and works together with other related parts to achieve a predetermined goal, and can be implemented in whole or in part by using software, hardware (such as processing circuits or memories), or a combination thereof. Similarly, a processor (or multiple processors or memories) can be used to implement one or more modules or units. In addition, each module or unit can be part of an overall module or unit that includes the function of the module or unit.

[0145] The above is only an optional implementation method for some implementation scenarios of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the solution of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. An aircraft simulation test system, characterized in that: include: The altimeter simulation test equipment comprises: a real-time simulator, which is used to generate a flight trajectory based on parameter configuration information carried in the flight trajectory generation instruction when receiving a flight trajectory generation instruction, and determine a third altitude and a signal attenuation value based on the flight trajectory; an echo simulator, which is connected to the real-time simulator and the altimeter, and is used to perform echo simulation processing on a transmission signal sent by the altimeter to obtain a simulated echo signal, including: determining the simulated echo signal based on the third altitude sent by the real-time simulator, the signal attenuation value and the transmission signal sent by the altimeter; an altimeter connected to the altimeter simulation test device, and configured to determine and send a first altitude based on the transmission signal and the simulated echo signal sent by the echo simulator; A flight control device connected to the altimeter; An integrated navigation device is connected to the flight control device and is used to send flight control information to the flight control device; the flight control information includes a second altitude and related flight information; the related flight information includes at least one of the following: flight speed and flight attitude; the first altitude and the second altitude are respectively measured by the altimeter and the integrated navigation device based on the same flight trajectory; A satellite navigation signal simulator is connected to the real-time simulator and the integrated navigation device, and is used for converting the flight trajectory sent by the real-time simulator to obtain flight conversion information and sending the information to the integrated navigation device. The integrated navigation device receives the flight conversion information and generates flight control information. The receiving process of the flight conversion information by the integrated navigation device is equivalent to the measurement of the flight trajectory by the integrated navigation device, and the second altitude in the flight control information can be obtained. The flight control device is used to fuse the first altitude and the second altitude to obtain a fused altitude, and control the flight of the aircraft based on the fused altitude and the relevant flight information.

2. The aircraft simulation test system according to claim 1, characterized in that: The altimeter simulation test equipment also includes: A host computer is connected to the real-time simulator and is used to send the flight trajectory generation instruction and determine the high performance of the altimeter based on the first altitude obtained and the third altitude sent by the real-time simulator.

3. The aircraft simulation test system according to claim 1, characterized in that: The real-time simulator is specifically used to generate a flight trajectory based on the parameter configuration information through a target mathematical simulation model, determine the third height based on the position information in the flight trajectory, and determine the signal attenuation value based on the third height.

4. The aircraft simulation test system according to claim 2, characterized in that: The real-time simulator is connected to the flight control device, and is used for performing clock synchronization with the flight control device, receiving the first altitude sent by the flight control device, and sending the first altitude to the host computer.

5. The aircraft simulation test system according to claim 1, characterized in that: The echo simulator includes a scene selection module, and the scene selection module is used to select a scene, and the scene includes at least one of the following: ground surface, water surface; The echo simulator is specifically used to perform echo simulation processing on the transmission signal based on the third height, the signal attenuation value and the selected scene to obtain a simulated echo signal; the echo simulation processing includes at least one of the following: delay processing, signal attenuation processing, and scattering information modulation; Among them, the delay processing is to delay the transmission signal based on the third height, the signal attenuation processing is to attenuate the transmission signal based on the signal attenuation value, and the scattering information modulation is to scatter modulate the transmission signal based on the selected scene.

6. The aircraft simulation test system according to claim 2, characterized in that: The host computer is specifically used to determine that the measurement accuracy of the altimeter meets the performance requirements if the difference between the first altitude and the third altitude is within a first preset range; and to determine that the measurement capability of the altimeter meets the performance requirements if the difference between the first altitude and the preset altitude is within a second preset range.

7. An aircraft simulation test method, characterized in that: An aircraft simulation test system as claimed in any one of claims 1 to 6, comprising: Acquire flight control information sent by the integrated navigation device; the flight control information includes a second altitude and related flight information; the related flight information includes at least one of the following: flight speed, flight attitude; the flight control information is generated by the satellite navigation signal simulator converting the flight trajectory sent by the real-time simulator to obtain flight conversion information and sending it to the integrated navigation device, and the integrated navigation device receives the flight conversion information; the receiving process of the flight conversion information by the integrated navigation device is equivalent to the measurement of the flight trajectory by the integrated navigation device, and the second altitude in the flight control information can be obtained; The first altitude is fused with the second altitude to obtain a fused altitude; the first altitude and the second altitude are respectively measured by the altimeter and the combined navigation device based on the same flight trajectory; the first altitude is determined by the altimeter based on a transmission signal and a simulated echo signal, and the simulated echo signal is obtained by the altimeter simulation test device performing echo simulation on the transmission signal emitted by the altimeter, including: when the real-time simulator receives a flight trajectory generation instruction, it generates a flight trajectory based on the parameter configuration information carried by the flight trajectory generation instruction, and determines a third altitude and a signal attenuation value based on the flight trajectory; the echo simulator determines a simulated echo signal based on the third altitude sent by the real-time simulator, the signal attenuation value and the transmission signal sent by the altimeter; the altimeter simulation test device includes the real-time simulator and the echo simulator; The flight of the aircraft is controlled based on the fused altitude and the relevant flight information.

8. An aircraft simulation test device, characterized in that: include: A control module, used for acquiring flight control information sent by an integrated navigation device; the flight control information includes a second altitude and related flight information; the related flight information includes at least one of the following: flight speed, flight attitude; the flight control information is generated by a satellite navigation signal simulator converting a flight trajectory sent by a real-time simulator to obtain flight conversion information and sending it to the integrated navigation device, and the integrated navigation device receives the flight conversion information; the receiving process of the flight conversion information by the integrated navigation device is equivalent to the measurement of the flight trajectory by the integrated navigation device, and the second altitude in the flight control information can be obtained; The first altitude is fused with the second altitude to obtain a fused altitude; the first altitude and the second altitude are respectively measured by the altimeter and the combined navigation device based on the same flight trajectory; the first altitude is determined by the altimeter based on a transmission signal and a simulated echo signal, and the simulated echo signal is obtained by the altimeter simulation test device performing echo simulation on the transmission signal emitted by the altimeter, including: when the real-time simulator receives a flight trajectory generation instruction, it generates a flight trajectory based on the parameter configuration information carried by the flight trajectory generation instruction, and determines a third altitude and a signal attenuation value based on the flight trajectory; the echo simulator determines a simulated echo signal based on the third altitude sent by the real-time simulator, the signal attenuation value and the transmission signal sent by the altimeter; the altimeter simulation test device includes the real-time simulator and the echo simulator; The flight of the aircraft is controlled based on the fused altitude and the relevant flight information.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to claim 7 are implemented.

Images