Method and system for testing anti-interference performance of navigation equipment during spinning of aircraft

Abstract

The invention relates to the technical field of navigation testing, and discloses a method and a system for testing anti-interference performance of navigation equipment during spinning of an aircraft, so as to realize scene reproduction and quantitative analysis. The method comprises the following steps: synchronously acquiring a first static navigation signal received by a first reference receiver and a first dynamic navigation signal received by a second reference receiver in a section of reference flight path; replacing the second reference receiver with a tested receiver deployed on the spin test platform; the playback device reconstructs a second static navigation signal facing the first reference receiver and used for restoring the reference flight track and a second dynamic navigation signal facing the tested receiver according to the spatial position relation between the tested receiver and the first reference receiver in the testing process; in the reproduced test environment, the tested receiver solves a test track based on a reconstruction signal of playback equipment under the action of a target interference source; and analyzing the error between the test track and the reference flight track to obtain the anti-interference performance of the tested receiver.

Description

Technical Field

[0001] The present invention relates to the field of navigation testing technology, and in particular to a method and system for testing the anti-interference performance of a navigation device when an aircraft is spinning. Background Art

[0002] Some aircraft often spin during flight. However, the GNSS (Global Navigation Satellite System) anti-interference antenna arrays deployed on such aircraft spin along with the carrier, causing interference waves to overlap with the velocity of the antenna array. This poses significant challenges for both anti-interference research and testing.

[0003] Field anti-interference testing is an important means of verifying the terminal's anti-interference capability. By selecting a site with a wide field of view, good satellite reception conditions, and no strong electromagnetic interference, the authenticity and validity of the test results can be guaranteed as much as possible. At the same time, dynamic anti-interference testing can be achieved through platform-mounted methods.

[0004] However, due to the complexity and unpredictability of outdoor testing environments, scene reproduction and quantitative analysis are impossible, and testing is susceptible to constraints such as weather, cost, and safety, resulting in numerous testing uncertainties. Factors such as the direction of interference signal incidence, signal reflection and multipath, and rapid attenuation during signal propagation can significantly impact the effectiveness of anti-interference antenna testing. Summary of the Invention

[0005] The present invention aims to disclose a method and system for testing the anti-interference performance of aviation equipment when an aircraft is spinning, so as to achieve scene reproduction and quantitative analysis.

[0006] To achieve the above object, the method of the present invention comprises: Synchronously collecting, within a reference flight trajectory, a first static navigation signal received by a first reference receiver at a fixed point on the ground in communication with a satellite and a first dynamic navigation signal received by a second reference receiver in the aircraft in communication with a satellite; The second reference receiver is replaced with a receiver under test deployed on the spinning test platform, and a playback device reconstructs a second static navigation signal for the first reference receiver and a second dynamic navigation signal for the receiver under test for restoring the reference flight trajectory based on the spatial positional relationship between the receiver under test and the first reference receiver in the test environment. A target interference source is deployed around the receiver under test. During the test, the playback device sends the reconstructed second static navigation signal and the second dynamic navigation signal to the first reference receiver and the receiver under test in a spinning state in a time sequence; then, according to the second dynamic navigation signal received by the receiver under test and the output signal after the first reference receiver processes the input second static navigation signal, a test trajectory is calculated based on the carrier phase difference technology, and then the error between the test trajectory and the reference flight trajectory is analyzed to obtain the anti-interference performance of the receiver under test.

[0007] Preferably, the present invention further comprises: when analyzing the anti-interference performance of the receiver under test, combining the satellite receiving state of the receiver under test and the error between the test trajectory and the reference flight trajectory in a weighted sum manner.

[0008] Preferably, the receiver under test of the present invention is deployed on a spinning test platform; and during the test process, the spinning test platform, the target interference source, the first reference receiver and the receiver under test are deployed in the same darkroom environment.

[0009] Preferably, the reference flight trajectory of the present invention is calibrated by the first reference receiver and the second reference receiver based on carrier phase difference technology.

[0010] Preferably, the target interference source generation mechanism described in the present invention comprises: inputting parameter information of the target interference source at the interference source control terminal, then transmitting this parameter information to a corresponding vector signal generator, which then, after switch control processing, outputs the information to an interference antenna with adjustable azimuth and elevation angles. Optionally, there are at least two interference antennas, each corresponding to one vector signal generator, and each interference antenna is arranged on an elliptical or circular trajectory centered on the receiver under test and meeting far-field conditions.

[0011] To achieve the above-mentioned purpose, the present invention also discloses a system for testing the anti-interference performance of a navigation device when an aircraft is spinning, comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the processor implements the above-mentioned method when executing the computer program; namely, within a reference flight trajectory, a first static navigation signal received by a first reference receiver and a first dynamic navigation signal received by a second reference receiver are synchronously collected; the second reference receiver is replaced with a receiver under test deployed on a spinning test platform, and a playback device reconstructs a second static navigation signal facing the first reference receiver and a second dynamic navigation signal facing the receiver under test for restoring the reference flight trajectory based on the spatial positional relationship between the receiver under test and the first reference receiver during the test process; in a reproduced test environment, the receiver under test calculates a test trajectory based on the reconstructed signal of the playback device under the action of a target interference source; and then analyzes the error between the test trajectory and the reference flight trajectory to obtain the anti-interference performance of the receiver under test.

[0012] The present invention has the following beneficial effects: It can repeatedly test the anti-interference performance of the receiver under test under a reproduced reference flight trajectory under different interference sources in the test environment, ensuring the dimensional scalability of the anti-interference performance test of the receiver under test and the accuracy of the overall test.

[0013] The present invention will be described in further detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings: Figure 1 The present invention is a flowchart of a method for testing the anti-interference performance of a navigation device during an aircraft autorotation, as disclosed in an embodiment of the present invention. DETAILED DESCRIPTION

[0015] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered by the claims.

[0016] Example 1 This embodiment discloses a method for testing the anti-interference performance of a navigation device when an aircraft is spinning. Figure 1 As shown, the following steps are included: Step S1: within a reference flight trajectory, synchronously collect a first static navigation signal received by a first reference receiver at a ground point communicating with a satellite and a first dynamic navigation signal received by a second reference receiver in an aircraft communicating with a satellite.

[0017] Preferably, the reference flight trajectory in this step is calibrated using carrier phase differential technology using the first and second reference receivers. This calibration method is conventional and can be referenced in the "Rotational System Differential Positioning Test System and Method" disclosed in CN119224797B. The first reference receiver in this embodiment functions equivalently to the RTK base station in CN119224797B. Alternatively, the reference flight trajectory can be pre-planned as a known quantity. During flight, the aircraft is then ensured to follow the planned trajectory and collect the corresponding first static navigation signal and first dynamic navigation signal.

[0018] Step S2: Replace the second reference receiver with the receiver under test deployed on the spinning test platform. The playback device reconstructs a second static navigation signal for the first reference receiver and a second dynamic navigation signal for the receiver under test for restoring the reference flight trajectory based on the spatial position relationship between the receiver under test and the first reference receiver in the test environment.

[0019] In the above two steps, during signal acquisition, the antenna receives the signal, the RF module down-converts the signal, and then samples and saves the digital signal through analog-to-digital conversion; correspondingly, the signal playback process is: the reconstructed digital signal is converted into an analog signal through digital-to-analog conversion, and the RF module up-converts the signal and sends it through the antenna; usually, during the reconstruction process, the playback device uses spatial radiation, and the distance selected cannot be too far (within 10 meters).

[0020] It is worth noting that, in this embodiment, reconstruction does not restore the signal transmitted by the satellite end, but rather allows the receiving party (including the receiver under test and the first reference receiver) to receive a signal theoretically equivalent to that received during the reference flight trajectory acquisition process, thereby restoring the reference flight trajectory. This also ensures that when the anti-interference performance of the receiver under test is very good in a rotating state, the error between the test trajectory obtained in the subsequent step S3 and the reference flight trajectory will be smaller.

[0021] Among them, since the spatial position between the receiver under test and the first reference receiver is usually considered to be fixed during the test process, which is different from the dynamic spatial position between the first reference receiver and the second reference receiver in step S1, the replayed signal needs to be reconstructed; the specific reconstruction algorithm is not the focus of this embodiment and there is an existing technology that can be implemented, so it will not be elaborated.

[0022] Step S3: Deploy a target interference source around the receiver under test. During the test, the playback device sends the reconstructed second static navigation signal and the second dynamic navigation signal to the first reference receiver and the receiver under test in the spinning state in a time sequence. Then, based on the second dynamic navigation signal received by the receiver under test and the output signal after the first reference receiver processes the input second static navigation signal, a test trajectory is calculated based on the carrier phase difference technology. Then, the error between the test trajectory and the reference flight trajectory is analyzed to obtain the anti-interference performance of the receiver under test.

[0023] Preferably, the receiver under test in this embodiment is deployed on a spinning test platform. During testing, the spinning test platform, the target interference source, the first reference receiver, and the receiver under test are deployed in the same darkroom environment (or an indoor environment with a certain degree of shielding). The closer the distance between the playback device and the first reference receiver and the receiver under test, the better the effect. Furthermore, the target interference source generation mechanism in this embodiment is as follows: parameter information of the target interference source is recorded at the interference source control terminal, then transmitted to a corresponding vector signal generator, which is then processed by switch control and output to an interference antenna with adjustable azimuth and elevation angles. Optionally, there are at least two interference antennas, with one interference antenna corresponding to each vector signal generator. Each interference antenna is arranged on an elliptical or circular trajectory centered on the receiver under test and meeting far-field conditions (typically greater than 4 meters).

[0024] Preferably, the rotation speed of the spinning test platform can also be adjusted by control instructions. In this embodiment, when analyzing the anti-interference performance of the receiver under test, the satellite reception state of the receiver under test and the error between the test trajectory and the reference flight trajectory are combined in a weighted sum manner.

[0025] In summary, it is obvious to those skilled in the art that the variables of the test environment of this embodiment include: reconstructed signal power, the number of interference sources, the direction and elevation angle of the interference antenna, the frequency, amplitude, phase and other parameters of the interference signal generator to determine the type of interference (such as: broadband, narrowband, pulse, swept frequency, etc.), the rotational speed of the receiver under test in the spinning speed measurement platform, etc.; thereby, when analyzing the anti-interference performance of the receiver under test, its performance under different test environments is comprehensively considered to ensure the dimensional scalability of the anti-interference performance test and the accuracy of the overall test.

[0026] Example 2 This embodiment discloses a system for testing the anti-interference performance of a navigation device during an aircraft spin. The system includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the method corresponding to the above embodiment is implemented. Specifically, within a reference flight trajectory, a first static navigation signal received by a first reference receiver and a first dynamic navigation signal received by a second reference receiver are synchronously acquired. The second reference receiver is replaced with a receiver under test deployed on a spinning test platform. A playback device reconstructs a second static navigation signal for the first reference receiver and a second dynamic navigation signal for the receiver under test, used to restore the reference flight trajectory, based on the spatial positional relationship between the receiver under test and the first reference receiver during the test. In a replicated test environment, the receiver under test calculates a test trajectory based on the reconstructed signal of the playback device under the action of a target interference source. The error between the test trajectory and the reference flight trajectory is then analyzed to obtain the anti-interference performance of the receiver under test.

[0027] In summary, the methods and systems disclosed in the above embodiments of this embodiment respectively have at least the following beneficial effects: It can repeatedly test the anti-interference performance of the receiver under test under a reproduced reference flight trajectory under different interference sources in the test environment, ensuring the dimensional scalability of the anti-interference performance test of the receiver under test and the accuracy of the overall test.

[0028] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A method for testing the anti-interference performance of a navigation device during an aircraft spin, characterized in that: include: Synchronously collecting, within a reference flight trajectory, a first static navigation signal received by a first reference receiver at a fixed point on the ground in communication with a satellite and a first dynamic navigation signal received by a second reference receiver in the aircraft in communication with a satellite; The second reference receiver is replaced with a receiver under test deployed on the spinning test platform, and a playback device reconstructs a second static navigation signal for the first reference receiver and a second dynamic navigation signal for the receiver under test for restoring the reference flight trajectory based on the spatial positional relationship between the receiver under test and the first reference receiver in the test environment. A target interference source is deployed around the receiver under test. During the test, the playback device sends the reconstructed second static navigation signal and the second dynamic navigation signal to the first reference receiver and the receiver under test in a spinning state in a time sequence; then, according to the second dynamic navigation signal received by the receiver under test and the output signal after the first reference receiver processes the input second static navigation signal, a test trajectory is calculated based on the carrier phase difference technology, and then the error between the test trajectory and the reference flight trajectory is analyzed to obtain the anti-interference performance of the receiver under test.

2. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 1, characterized in that: Also includes: When analyzing the anti-interference performance of the receiver under test, the satellite receiving state of the receiver under test and the error between the test trajectory and the reference flight trajectory are combined in a weighted sum manner.

3. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 1 or 2, characterized in that: The receiver under test is deployed on a spinning test platform.

4. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 3, wherein: During the test, the spin test platform, the target interference source, the first reference receiver and the receiver under test are deployed in the same darkroom environment.

5. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 4, characterized in that: The reference flight trajectory is calibrated by the first reference receiver and the second reference receiver based on carrier phase difference technology.

6. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 5, characterized in that: The generation mechanism of the target interference source is: The parameter information of the target interference source is entered at the interference source control end, and then sent to the corresponding vector signal generator, and then processed by the switch control and output to the interference antenna with adjustable azimuth and pitch angles.

7. The method for testing the anti-interference performance of a navigation device during an aircraft spin according to claim 6, characterized in that: The number of interference antennas is at least two, and one interference antenna corresponds to one vector signal generator. Each interference antenna is arranged on an elliptical or circular track centered on the receiver under test and meeting far-field conditions.

8. A system for testing the anti-interference performance of a navigation device during an aircraft spin, comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, characterized in that: When the processor executes the computer program, the method according to any one of claims 1 to 7 is implemented.

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