CN116008674A - Electromagnetic environment testing method and system for aircraft - Google Patents
Electromagnetic environment testing method and system for aircraft Download PDFInfo
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- CN116008674A CN116008674A CN202310058859.7A CN202310058859A CN116008674A CN 116008674 A CN116008674 A CN 116008674A CN 202310058859 A CN202310058859 A CN 202310058859A CN 116008674 A CN116008674 A CN 116008674A
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Abstract
The invention discloses an electromagnetic environment testing method and system for an aircraft. The method comprises the following steps: a fence area, i.e. a safety area of the aircraft, is determined by means of the profile parameters of the aircraft, and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area. Generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point. The health threat of the testers exposed in the strong electromagnetic environment for a long time can be avoided, meanwhile, the test time of the test system is shortened, and the test efficiency is improved. On the other hand, the second direction is adjusted so that the radio frequency signal transmitting antenna can be located at the optimal test point, and the test accuracy is improved.
Description
Technical Field
The invention relates to the technical field of electromagnetic compatibility of aircrafts, in particular to an electromagnetic environment testing method and system of an aircraft.
Background
With the development of aviation technology, in particular to new technologies such as composite materials and the like, the new technologies are increasingly applied to the civil aviation field, and the new technologies bring unprecedented challenges to electromagnetic protection of airplanes. To demonstrate the effectiveness of civil aircraft in protecting against electromagnetic environments, an aircraft must be tested for validation. The civil aircraft all-electromechanical magnetic environment test is carried out in an external field, and has the characteristics of a large number of test instruments, long test time consumption, a large number of test staff, complex test conditions and the like.
By adopting the traditional scheme, the test antenna is required to be manually moved frequently in the test process, the height and polarization of the test antenna are adjusted, and the working efficiency is low. Taking the cockpit as an example, the electromagnetic irradiation angles of the cockpit have 6 different irradiation angles by comprehensively considering the test efficiency and the test coverage, and each irradiation angle needs to be tested for multiple times, so that a platform needs to be manually moved to a designated test point, a large amount of manpower is consumed, and the test efficiency is lower. Besides the cockpit, all cabins of the whole aircraft are required to be tested in sequence, and the total working conditions are more than 560.
The traditional scheme is inconvenient in measuring the irradiation angle. When the traditional method is used for testing, a mode of manually fixing the point on the ground is adopted, and specific angles are selected to irradiate the aircraft; in the test process, the irradiation angle needs to be continuously adjusted and the positioning needs to be carried out again. However, the mobile platform is controlled automatically to designate the position, and because the mobile platform has a certain physical size, even if the mobile platform reaches the radio frequency signal transmitting point during automatic test, the carried radio frequency signal transmitting antenna cannot be positioned at the optimal test position, so that the test data is inaccurate.
Disclosure of Invention
The invention provides an electromagnetic environment testing method and system for an aircraft, which can effectively solve the problem that the test data are inaccurate because a mobile platform has a certain physical size at present and cannot be positioned at an optimal test position even if the mobile platform reaches a radio frequency signal transmitting point during automatic test.
According to an aspect of the invention, there is provided a method of testing the electromagnetic environment of an aircraft, the method comprising: acquiring profile parameters of the aircraft; generating a fence area based on the profile parameters; determining at least one measurement target point on the aircraft and generating at least one radio frequency signal emission point outside the fence area associated with the at least one measurement target point; generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path; when the mobile platform is positioned at the radio frequency signal transmitting point, adjusting the position parameter of the radio frequency signal transmitting antenna to a preset position; and driving a mobile platform carrying a radio frequency signal transmitting antenna to move along the moving path, and transmitting a preset radio frequency signal to a measurement target point corresponding to each radio frequency signal transmitting point at each radio frequency signal transmitting point according to preset test parameters.
Further, when the mobile platform is located at the radio frequency signal transmitting point, adjusting the position parameter of the radio frequency signal transmitting antenna to a preset position includes: controlling the radio frequency signal transmitting antenna to move back and forth in a first direction through a first adjusting operation; and controlling the radio frequency signal transmitting antenna to move back and forth in a second direction through a first adjusting operation, wherein the first direction and the second direction are mutually perpendicular.
Further, the driving the mobile platform carrying the rf signal transmitting antenna to move along the moving path, and transmitting the predetermined rf signal to the measurement target point corresponding to each rf signal transmitting point at each rf signal transmitting point according to the preset test parameters sequentially includes: generating a test curve according to the received data; and determining whether the test curve is abnormal or not according to the slope and/or the value of the test curve in a preset angle range.
Further, the generating the fence area based on the profile parameters comprises the steps of calculating a safe distance according to the preset moving speed and/or positioning accuracy of the moving platform; and taking an area formed after the area corresponding to the profile parameter is extended as the fence area based on the safety distance.
Further, the generating at least one radio frequency signal emission point outside the fence area associated with the at least one measurement target point comprises: and forming a target circular track by taking the position of each measurement target point as the circle center, arranging at least two marking points on the target circular track at equal intervals, and taking the marking points outside the fence area as the radio frequency signal emission points associated with the measurement target points.
Further, the determining at least one measurement target point on the aircraft comprises: and acquiring at least one of a head area, a tail area, a flank area and a fuselage area of the aircraft as a set area, so as to select the at least one measurement target point from the set area.
Further, the generating a moving path according to the position of the at least one radio frequency signal transmitting point includes: acquiring the current position of the mobile platform; and determining the moving path based on a preset path optimization algorithm according to the current position of the moving platform and the positions of all the radio frequency signal transmitting points, wherein the moving path is the shortest path passing through all the radio frequency signal transmitting points, and the moving path is positioned outside the fence area.
Further, the method further comprises: at each radio frequency signal transmitting point, the mobile platform transmits a low frequency radio frequency signal and a high frequency radio frequency signal to a corresponding measurement target point; and/or at each radio frequency signal transmitting point, the mobile platform transmits a horizontal polarization radio frequency signal and a vertical polarization radio frequency signal to a corresponding measurement target point.
According to another aspect of the invention, there is provided an electromagnetic environment testing system for an aircraft, the system comprising: the mobile platform is internally provided with at least one cavity; a controller disposed within the cavity, the controller comprising a memory for storing instructions and data and a processor for performing the steps in the electromagnetic environment testing method of the aircraft of any one of claims 1-6.
Further, the system further comprises: the antenna lifting platform is arranged on the surface of the mobile platform, which is away from the ground; the radio frequency signal transmitting antenna is arranged at the top of the antenna lifting platform; the effective height of the antenna lifting platform is adjustable, so that the radio frequency transmitting antenna can transmit radio frequency signals to the aircraft at different preset heights.
Further, the system further comprises: the radio frequency transmitting assembly is arranged in the cavity and is electrically connected with the radio frequency transmitting antenna through a cable so as to drive the radio frequency signal transmitting antenna to transmit the preset radio frequency signal, wherein the antenna lifting platform is provided with a hollow part so as to accommodate the cable.
Further, the system further comprises: the mobile platform comprises a first battery assembly and a second battery assembly, wherein the first battery assembly is electrically connected with a driving mechanism of the mobile platform, and the second battery assembly is electrically connected with the radio frequency emitting assembly, and the first battery assembly and the second battery assembly are mutually independent.
Further, the system further comprises: the first laser radar and the second laser radar are respectively arranged at two sides of the mobile platform, and the first laser radar and the second laser radar are used for acquiring the outline parameters of the aircraft in a target scene.
Further, the system further comprises: the first positioning antenna and the second positioning antenna are respectively arranged on two sides of the mobile platform, and the first positioning antenna and the second positioning antenna are used for determining the position of the mobile platform based on a dual-mode differential mode.
Further, the system further comprises: the first anti-collision rod and the second anti-collision rod are respectively arranged on two opposite side edges of the movable platform.
The advantage of the invention is that a fence area, i.e. a safety area of the aircraft, is determined by the profile parameters of the aircraft and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area. Generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point. The health threat of the testers exposed in the strong electromagnetic environment for a long time can be avoided, meanwhile, the test time of the test system is shortened, and the test efficiency is improved. On the other hand, the second direction is adjusted so that the radio frequency signal transmitting antenna can be located at the optimal test point, and the test accuracy is improved.
Drawings
The technical solution and other advantageous effects of the present invention will be made apparent by the following detailed description of the specific embodiments of the present invention with reference to the accompanying drawings.
Fig. 1 is a flowchart of steps of an electromagnetic environment testing method for an aircraft according to a first embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an electromagnetic environment testing system of an aircraft according to an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of the interior of the mobile platform according to an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a folding arm antenna lifting platform according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically connected, electrically connected or can be communicated with each other; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
Referring now to fig. 1, fig. 1 is a schematic diagram illustrating a method for testing an electromagnetic environment of an aircraft according to a first embodiment of the present invention. The method comprises the following steps:
step S110: and acquiring the profile parameters of the aircraft.
For example, the outline of the aircraft is scanned according to the shape and size information of the aircraft, for example, a coordinate point of the outline of the aircraft in the coordinate system can be determined through communication with the building coordinate system.
Step S120: and generating a fence area based on the profile parameters.
Illustratively, the safe distance is calculated according to the preset moving speed and/or positioning accuracy of the moving platform, and a deceleration distance is required for the moving platform to move from a high speed to a deceleration stop due to the positioning accuracy of the moving platform itself. Therefore, in some embodiments, the distances are calculated separately in combination with the preset moving speed and/or positioning accuracy of the moving platform, and the maximum distance is used as the safety distance to ensure that there is a sufficient buffer distance between the aircraft and the moving platform.
The fence area is an area formed by extending an area corresponding to the profile parameter based on the safety distance. The fence area, i.e. the safety area of the aircraft, is preferably at a distance from any one point of the fence area to the position of the corresponding point of the aircraft contour equal to the safety distance.
Step S130: at least one measurement target point on the aircraft is determined and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area.
The measuring point is, for example, at least one of a head region, a tail region, a flank region and a fuselage region of the aircraft is acquired as a setting region, from which the at least one measuring target point is selected. In some embodiments, the aircraft is tested for electromagnetic environment in the nose region, tail region, wing region, and fuselage region, so the aircraft is configured for measurement target points in the nose region, tail region, wing region, and fuselage region.
For each measuring target point, a target circular track is formed by taking the position of each measuring target point as a circle center, at least two marking points are arranged on the target circular track at equal intervals, and the marking points outside the fence area are taken as the radio frequency signal emission points associated with the measuring target point. In some embodiments, each measurement target point may be equally divided into nine mark points by using its position as a center to form a target circular track, and then the mark points of the nine points outside the fence area are acquired as the radio frequency signal transmitting points associated with the measurement target point.
Step S140: when the mobile platform is positioned at the radio frequency signal transmitting point, the position parameters of the radio frequency signal transmitting antenna are adjusted to a preset position.
Illustratively, step S140 includes:
the rf signal transmitting antenna is controlled to move back and forth in a first direction by a first adjustment operation.
The rf signal transmitting antenna is controlled to move back and forth in a second direction by a first adjustment operation.
Specifically, the first direction and the second direction are perpendicular to each other, and illustratively, the first direction refers to a direction perpendicular to a plane of the mobile platform, i.e. a height direction. The second direction may be the direction of travel of the mobile platform in some embodiments.
Step S150: and driving a mobile platform carrying a radio frequency signal transmitting antenna to move along the moving path, and transmitting a preset radio frequency signal to a measurement target point corresponding to each radio frequency signal transmitting point at each radio frequency signal transmitting point according to preset test parameters.
Illustratively, step S150 includes generating a test curve from the received data.
And determining whether the test curve is abnormal or not according to the slope and/or the value of the test curve in a preset angle range.
Illustratively, the test curve is located in a two-position coordinate system, with the abscissa being the angle and the ordinate being the radiation intensity. An anomaly may occur when the slope significantly exceeds a first preset value and/or when the radiation intensity significantly exceeds a second preset value, either by manually adjusting the radio frequency signal transmitting antenna or by checking for other possible problems.
In some embodiments, the path optimization algorithm is that, according to the position corresponding to the position parameter, the position corresponding to the preset measuring point parameter closest to the position parameter is obtained, the position corresponding to the preset measuring point parameter closest to the position parameter is taken as a measuring target point, the positions of all radio frequency signal transmitting points associated with the measuring target point are obtained, according to the position parameter and the positions of all radio frequency signal transmitting points, a detection path is calculated, wherein the detection path is the shortest path of the moving platform passing through all radio frequency signal transmitting points, and is located outside the reference area, after the detection path of one measuring target point is calculated, another preset measuring point closest to the moving platform is obtained according to the position corresponding to the position of the moving platform, the other preset measuring point closest to the moving platform is taken as a new measuring target point, and all detection paths are generated and are connected to generate the moving path.
That is, when the electromagnetic environment of the aircraft is tested, the mobile platform first selects a measurement target point closest to the mobile platform, then calculates a shortest detection path of the mobile platform through all the radio frequency signal emission points, and first tests all the radio frequency signal emission points of one measurement target point and then moves the measurement target point to another measurement target point.
It should be further noted that the path optimization algorithm is only a preferred manner provided by the present invention, and is not limited to the path optimization algorithm of the present invention, for example, in some embodiments, the mobile platform first selects a radio frequency signal transmitting point, and calculates the shortest path passing through the radio frequency signal transmitting point by taking the radio frequency signal transmitting point as a starting point.
An embodiment determines a fence area, i.e. a safety area of the aircraft, from the profile parameters of the aircraft and generates at least one radio frequency signal emission point outside the fence area in association with the at least one measurement target point. Generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point. The health threat of the testers exposed in the strong electromagnetic environment for a long time can be avoided, meanwhile, the test time of the test system is shortened, and the test efficiency is improved. On the other hand, the second direction is adjusted so that the radio frequency signal transmitting antenna can be located at the optimal test point, and the test accuracy is improved.
As shown in fig. 2, the method for testing the electromagnetic environment of the aircraft according to the second embodiment of the present invention includes:
step S210: and acquiring the profile parameters of the aircraft.
For example, the outline of the aircraft is scanned according to the shape and size information of the aircraft, for example, a coordinate point of the outline of the aircraft in the coordinate system can be determined through communication with the building coordinate system.
Step S220: and generating a fence area based on the profile parameters.
Illustratively, the safe distance is calculated according to the preset moving speed and/or positioning accuracy of the moving platform, and a deceleration distance is required for the moving platform to move from a high speed to a deceleration stop due to the positioning accuracy of the moving platform itself. Therefore, in some embodiments, the distances are calculated separately in combination with the preset moving speed and/or positioning accuracy of the moving platform, and the maximum distance is used as the safety distance to ensure that there is a sufficient buffer distance between the aircraft and the moving platform.
The fence area is an area formed by extending an area corresponding to the profile parameter based on the safety distance. The fence area, i.e. the safety area of the aircraft, is preferably at a distance from any one point of the fence area to the position of the corresponding point of the aircraft contour equal to the safety distance.
Step S230: at least one measurement target point on the aircraft is determined and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area.
The measuring point is, for example, at least one of a head region, a tail region, a flank region and a fuselage region of the aircraft is acquired as a setting region, from which the at least one measuring target point is selected. In some embodiments, the aircraft is tested for electromagnetic environment in the nose region, tail region, wing region, and fuselage region, so the aircraft is configured for measurement target points in the nose region, tail region, wing region, and fuselage region.
For each measuring target point, a target circular track is formed by taking the position of each measuring target point as a circle center, at least two marking points are arranged on the target circular track at equal intervals, and the marking points outside the fence area are taken as the radio frequency signal emission points associated with the measuring target point. In some embodiments, each measurement target point may be equally divided into nine mark points by using its position as a center to form a target circular track, and then the mark points of the nine points outside the fence area are acquired as the radio frequency signal transmitting points associated with the measurement target point.
Step S240: generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point.
Illustratively, generating the movement path may specifically be as follows: the method comprises the steps of obtaining position parameters of the mobile platform, and determining the moving path according to the current position of the mobile platform and the positions of all radio frequency signal emission points based on a preset path optimization algorithm, wherein the moving path is the shortest path passing through all radio frequency signal emission points, and the moving path is located outside the fence area.
In some embodiments, the path optimization algorithm is that, according to the position corresponding to the position parameter, the position corresponding to the preset measuring point parameter closest to the position parameter is obtained, the position corresponding to the preset measuring point parameter closest to the position parameter is taken as a measuring target point, the positions of all radio frequency signal transmitting points associated with the measuring target point are obtained, according to the position parameter and the positions of all radio frequency signal transmitting points, a detection path is calculated, wherein the detection path is the shortest path of the moving platform passing through all radio frequency signal transmitting points, and is located outside the reference area, after the detection path of one measuring target point is calculated, another preset measuring point closest to the moving platform is obtained according to the position corresponding to the position of the moving platform, the other preset measuring point closest to the moving platform is taken as a new measuring target point, and all detection paths are generated and are connected to generate the moving path.
That is, when the electromagnetic environment of the aircraft is tested, the mobile platform first selects a measurement target point closest to the mobile platform, then calculates a shortest detection path of the mobile platform through all the radio frequency signal emission points, and first tests all the radio frequency signal emission points of one measurement target point and then moves the measurement target point to another measurement target point.
It should be further noted that the path optimization algorithm is only a preferred manner provided by the present invention, and is not limited to the path optimization algorithm of the present invention, for example, in some embodiments, the mobile platform first selects a radio frequency signal transmitting point, and calculates the shortest path passing through the radio frequency signal transmitting point by taking the radio frequency signal transmitting point as a starting point.
Step S250: at each radio frequency signal transmitting point, the mobile platform transmits a low frequency radio frequency signal and a high frequency radio frequency signal to a corresponding measurement target point.
Step S260: at each radio frequency signal emission point, the mobile platform emits a horizontally polarized radio frequency signal and a vertically polarized radio frequency signal to a corresponding measurement target point.
Illustratively, the low frequency measurement and the high frequency measurement are performed at one signal detection point, and the horizontal polarization measurement and the vertical polarization measurement are performed at one signal detection point, for more fully completing the electromagnetic environment test procedure of the aircraft.
The embodiment determines a fence area, i.e. a safety area of the aircraft, by means of the profile parameters of the aircraft and generates at least one radio frequency signal emission point outside said fence area, which is associated with said at least one measurement target point. Generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point. The health threat of the testers exposed in the strong electromagnetic environment for a long time can be avoided, meanwhile, the test time of the test system is shortened, and the test efficiency is improved.
As shown in fig. 2, fig. 3 and fig. 4, an electromagnetic environment testing system for an aircraft according to an embodiment of the present invention includes: the mobile platform 100, the controller 200, the antenna elevating platform 700, the radio frequency transmitting antenna 600, the radio frequency transmitting assembly 300, the first battery assembly 410, the second battery assembly 420, the first radar 810, the second radar 820, the first positioning antenna 910, the second positioning antenna 920, the first impact beam 510, and the second impact beam 520.
Illustratively, at least one cavity 110 is provided within the movable platform 100.
The antenna lifting platform 700 is disposed on the upper surface of the mobile platform 100, and the antenna lifting platform 700 can automatically height the rf transmitting antenna 600 according to the actual requirement during the test in the electromagnetic environment test of the aircraft, so as to realize the control of electromagnetic radiation irradiation in the vertical direction. And the antenna elevating table 700 has a hollow portion so that the cable is connected to the rf transmitting antenna 600 through the hollow portion. The antenna lifting table 700 has a hollow portion, and can protect a wire-type straight hard cable from being stepped on and being bent greatly, so that the test progress is ensured. In some embodiments, the antenna lift table 700 is a folding-arm antenna lift table, which includes a first folding arm and a second folding arm, which receive control of the controller to move the rf signal transmitting antenna back and forth in a first direction controlled by a first adjustment operation; and controlling the radio frequency signal transmitting antenna to move back and forth in a second direction through a first adjusting operation, wherein the first direction and the second direction are mutually perpendicular. The stability of the antenna elevating platform 700 is ensured, the height range of the adjustable radio frequency transmitting antenna 600 is 1.5 m-4.5 m, and the range of the second direction is 1m-4m.
Illustratively, the radio frequency transmitting antenna 600 is disposed on top of the antenna elevating platform 700, and the electromagnetic environment test is performed on the aircraft by adjusting the antenna elevating platform 700 so that the radio frequency transmitting antenna 600 is at different heights. The radio frequency transmitting antenna 600 is a signal transmitting front end of the system, and different forms of radio frequency transmitting antennas 600 are installed, so that the radio frequency transmitting antenna 600 can cover the frequency range of 100MHz-18GHz, and the electromagnetic environment testing requirement is met. In some embodiments, the low-band rf transmit antenna 600 is in the form of a log-periodic antenna, the high-band rf transmit antenna 600 is in the form of a horn antenna, and both rf transmit antennas 600 may be mounted on the same mobile platform 100.
The rf transmitting assembly 300 is disposed in the cavity 110 and connected to the rf transmitting antenna 600 through a cable. In some embodiments, the radio frequency emitting assembly 300 is a spectrometer.
Illustratively, a first battery assembly 410 and a second battery assembly 420 are disposed in the cavity, the first battery assembly 410 is connected with the electric device of the mobile platform 100, and the second battery assembly 420 is connected with the radio frequency transmitting assembly 300, wherein the first battery assembly 410 and the second battery assembly 420 are disposed independently. The separate arrangement of the connection of the first battery assembly 410 and the electric equipment of the mobile platform 100 and the connection of the second battery assembly 420 and the radio frequency emission assembly 300 can realize that the radio frequency emission assembly 300 of the system is not affected by electromagnetic interference of an external power supply, has low-level electromagnetic radiation characteristic and ensures continuous long-time operation.
Illustratively, a first laser radar 810 and a second laser radar 820 are respectively disposed at two ends of the upper surface of the mobile platform 100, and the first laser radar 810 and the second laser radar 820 are used for acquiring profile parameters of the aircraft in a target scene. Specifically, the first lidar 810 and the second lidar 820 implement a rapid three-dimensional modeling function for the outline structure dimension profile of the aircraft and the surrounding environment based on the SLAM laser mapping function.
Illustratively, a first positioning antenna 910 and a second positioning antenna 920 are respectively disposed at two ends of the upper surface of the mobile platform 100, and the first positioning antenna 910 and the second positioning antenna 920 are used for acquiring the position parameters of the mobile platform 100. Specifically, the first positioning antenna 910 and the second positioning antenna 920 adopt a dual-GNSS differential algorithm, so as to realize a high-precision positioning function of the mobile platform 100 and ensure a test positioning precision requirement.
Illustratively, the first and second impact bars 510 and 520 are provided at both end portions of the side of the moving platform 100, respectively. The moving platform 100 is emergency braked when the first impact beam 510 of the low obstacle is impacted while the moving platform 100 is advancing, and the moving platform 100 is emergency braked when the second impact beam 520 of the low obstacle is impacted while the moving platform 100 is retreating.
In some embodiments, the mobile platform is driven by a direct current motor, and in-and-out totally-enclosed metallization processing is performed outside the direct current motor in order to reduce the influence of electromagnetic radiation of the motor on a test result to the greatest extent.
The controller is arranged in the cavity, the controller comprises a memory and a processor, the memory is used for storing instructions and data, and the processor is used for executing the first embodiment:
step S110: and acquiring the profile parameters of the aircraft.
For example, the outline of the aircraft is scanned according to the shape and size information of the aircraft, for example, a coordinate point of the outline of the aircraft in the coordinate system can be determined through communication with the building coordinate system.
Step S120: and generating a fence area based on the profile parameters.
Illustratively, the safe distance is calculated according to the preset moving speed and/or positioning accuracy of the moving platform, and a deceleration distance is required for the moving platform to move from a high speed to a deceleration stop due to the positioning accuracy of the moving platform itself. Therefore, in some embodiments, the distances are calculated separately in combination with the preset moving speed and/or positioning accuracy of the moving platform, and the maximum distance is used as the safety distance to ensure that there is a sufficient buffer distance between the aircraft and the moving platform.
The fence area is an area formed by extending an area corresponding to the profile parameter based on the safety distance. The fence area, i.e. the safety area of the aircraft, is preferably at a distance from any one point of the fence area to the position of the corresponding point of the aircraft contour equal to the safety distance.
Step S130: at least one measurement target point on the aircraft is determined and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area.
The measuring point is, for example, at least one of a head region, a tail region, a flank region and a fuselage region of the aircraft is acquired as a setting region, from which the at least one measuring target point is selected. In some embodiments, the aircraft is tested for electromagnetic environment in the nose region, tail region, wing region, and fuselage region, so the aircraft is configured for measurement target points in the nose region, tail region, wing region, and fuselage region.
For each measuring target point, a target circular track is formed by taking the position of each measuring target point as a circle center, at least two marking points are arranged on the target circular track at equal intervals, and the marking points outside the fence area are taken as the radio frequency signal emission points associated with the measuring target point. In some embodiments, each measurement target point may be equally divided into nine mark points by using its position as a center to form a target circular track, and then the mark points of the nine points outside the fence area are acquired as the radio frequency signal transmitting points associated with the measurement target point.
Step S140: when the mobile platform is positioned at the radio frequency signal transmitting point, the position parameters of the radio frequency signal transmitting antenna are adjusted to a preset position.
Illustratively, step S140 includes:
the rf signal transmitting antenna is controlled to move back and forth in a first direction by a first adjustment operation.
The rf signal transmitting antenna is controlled to move back and forth in a second direction by a first adjustment operation.
Specifically, the first direction and the second direction are perpendicular to each other, and illustratively, the first direction refers to a direction perpendicular to a plane of the mobile platform, i.e. a height direction. The second direction may be the direction of travel of the mobile platform in some embodiments.
Step S150: and driving a mobile platform carrying a radio frequency signal transmitting antenna to move along the moving path, and transmitting a preset radio frequency signal to a measurement target point corresponding to each radio frequency signal transmitting point at each radio frequency signal transmitting point according to preset test parameters.
Illustratively, step S150 includes generating a test curve from the received data.
And determining whether the test curve is abnormal or not according to the slope and/or the value of the test curve in a preset angle range.
Illustratively, the test curve is located in a two-position coordinate system, with the abscissa being the angle and the ordinate being the radiation intensity. An anomaly may occur when the slope significantly exceeds a first preset value and/or when the radiation intensity significantly exceeds a second preset value, either by manually adjusting the radio frequency signal transmitting antenna or by checking for other possible problems.
Illustratively, generating the movement path may specifically be as follows: the method comprises the steps of obtaining position parameters of the mobile platform, and determining the moving path according to the current position of the mobile platform and the positions of all radio frequency signal emission points based on a preset path optimization algorithm, wherein the moving path is the shortest path passing through all radio frequency signal emission points, and the moving path is located outside the fence area.
In some embodiments, the path optimization algorithm is that, according to the position corresponding to the position parameter, the position corresponding to the preset measuring point parameter closest to the position parameter is obtained, the position corresponding to the preset measuring point parameter closest to the position parameter is taken as a measuring target point, the positions of all radio frequency signal transmitting points associated with the measuring target point are obtained, according to the position parameter and the positions of all radio frequency signal transmitting points, a detection path is calculated, wherein the detection path is the shortest path of the moving platform passing through all radio frequency signal transmitting points, and is located outside the reference area, after the detection path of one measuring target point is calculated, another preset measuring point closest to the moving platform is obtained according to the position corresponding to the position of the moving platform, the other preset measuring point closest to the moving platform is taken as a new measuring target point, and all detection paths are generated and are connected to generate the moving path.
That is, when the electromagnetic environment of the aircraft is tested, the mobile platform first selects a measurement target point closest to the mobile platform, then calculates a shortest detection path of the mobile platform through all the radio frequency signal emission points, and first tests all the radio frequency signal emission points of one measurement target point and then moves the measurement target point to another measurement target point.
It should be further noted that the path optimization algorithm is only a preferred manner provided by the present invention, and is not limited to the path optimization algorithm of the present invention, for example, in some embodiments, the mobile platform first selects a radio frequency signal transmitting point, and calculates the shortest path passing through the radio frequency signal transmitting point by taking the radio frequency signal transmitting point as a starting point.
In some embodiments, the processor may be further configured to perform the second embodiment:
step S210: and acquiring the profile parameters of the aircraft.
For example, the outline of the aircraft is scanned according to the shape and size information of the aircraft, for example, a coordinate point of the outline of the aircraft in the coordinate system can be determined through communication with the building coordinate system.
Step S220: and generating a fence area based on the profile parameters.
Illustratively, the safe distance is calculated according to the preset moving speed and/or positioning accuracy of the moving platform, and a deceleration distance is required for the moving platform to move from a high speed to a deceleration stop due to the positioning accuracy of the moving platform itself. Therefore, in some embodiments, the distances are calculated separately in combination with the preset moving speed and/or positioning accuracy of the moving platform, and the maximum distance is used as the safety distance to ensure that there is a sufficient buffer distance between the aircraft and the moving platform.
The fence area is an area formed by extending an area corresponding to the profile parameter based on the safety distance. The fence area, i.e. the safety area of the aircraft, is preferably at a distance from any one point of the fence area to the position of the corresponding point of the aircraft contour equal to the safety distance.
Step S230: at least one measurement target point on the aircraft is determined and at least one radio frequency signal emission point associated with the at least one measurement target point is generated outside the fence area.
The measuring point is, for example, at least one of a head region, a tail region, a flank region and a fuselage region of the aircraft is acquired as a setting region, from which the at least one measuring target point is selected. In some embodiments, the aircraft is tested for electromagnetic environment in the nose region, tail region, wing region, and fuselage region, so the aircraft is configured for measurement target points in the nose region, tail region, wing region, and fuselage region.
For each measuring target point, a target circular track is formed by taking the position of each measuring target point as a circle center, at least two marking points are arranged on the target circular track at equal intervals, and the marking points outside the fence area are taken as the radio frequency signal emission points associated with the measuring target point. In some embodiments, each measurement target point may be equally divided into nine mark points by using its position as a center to form a target circular track, and then the mark points of the nine points outside the fence area are acquired as the radio frequency signal transmitting points associated with the measurement target point.
Step S240: generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point.
Illustratively, generating the movement path may specifically be as follows: the method comprises the steps of obtaining position parameters of the mobile platform, and determining the moving path according to the current position of the mobile platform and the positions of all radio frequency signal emission points based on a preset path optimization algorithm, wherein the moving path is the shortest path passing through all radio frequency signal emission points, and the moving path is located outside the fence area.
In some embodiments, the path optimization algorithm is that, according to the position corresponding to the position parameter, the position corresponding to the preset measuring point parameter closest to the position parameter is obtained, the position corresponding to the preset measuring point parameter closest to the position parameter is taken as a measuring target point, the positions of all radio frequency signal transmitting points associated with the measuring target point are obtained, according to the position parameter and the positions of all radio frequency signal transmitting points, a detection path is calculated, wherein the detection path is the shortest path of the moving platform passing through all radio frequency signal transmitting points, and is located outside the reference area, after the detection path of one measuring target point is calculated, another preset measuring point closest to the moving platform is obtained according to the position corresponding to the position of the moving platform, the other preset measuring point closest to the moving platform is taken as a new measuring target point, and all detection paths are generated and are connected to generate the moving path.
That is, when the electromagnetic environment of the aircraft is tested, the mobile platform first selects a measurement target point closest to the mobile platform, then calculates a shortest detection path of the mobile platform through all the radio frequency signal emission points, and first tests all the radio frequency signal emission points of one measurement target point and then moves the measurement target point to another measurement target point.
It should be further noted that the path optimization algorithm is only a preferred manner provided by the present invention, and is not limited to the path optimization algorithm of the present invention, for example, in some embodiments, the mobile platform first selects a radio frequency signal transmitting point, and calculates the shortest path passing through the radio frequency signal transmitting point by taking the radio frequency signal transmitting point as a starting point.
Step S250: at each radio frequency signal transmitting point, the mobile platform transmits a low frequency radio frequency signal and a high frequency radio frequency signal to a corresponding measurement target point.
Step S260: at each radio frequency signal emission point, the mobile platform emits a horizontally polarized radio frequency signal and a vertically polarized radio frequency signal to a corresponding measurement target point.
Illustratively, the low frequency measurement and the high frequency measurement are performed at one signal detection point, and the horizontal polarization measurement and the vertical polarization measurement are performed at one signal detection point, for more fully completing the electromagnetic environment test procedure of the aircraft.
In the embodiment, the chassis of the mobile platform has the functions of an automobile chassis, has the functions of steering, braking and bearing a load of 50kg, adopts a four-wheel-drive chassis, has the climbing capacity of 0-25 degrees, and is internally provided with a 24V lithium polymer direct current motor. The DC motor improves the driving force for the mobile chassis and has low-level radiation characteristic.
Embodiments determine a fence area, i.e. a safety area of the aircraft, from profile parameters of the aircraft and generate at least one radio frequency signal emission point outside said fence area in association with said at least one measurement target point. Generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path so as to sequentially transmit a preset radio frequency signal to a measuring target point corresponding to the radio frequency signal transmitting point at each radio frequency signal transmitting point. The health threat of the testers exposed in the strong electromagnetic environment for a long time can be avoided, meanwhile, the test time of the test system is shortened, and the test efficiency is improved.
The invention also provides a storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform the method of electromagnetic environment testing of an aircraft as described above.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by means of software plus necessary general hardware platforms, or of course may be implemented by means of hardware. Based on this understanding, the foregoing technical solution may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the respective embodiments or some parts of the embodiments.
In summary, although the present invention has been described in terms of the preferred embodiments, the preferred embodiments are not limited to the above embodiments, and various modifications and changes can be made by one skilled in the art without departing from the spirit and scope of the invention, and the scope of the invention is defined by the appended claims.
Claims (15)
1. A method of testing an electromagnetic environment of an aircraft, the method comprising:
acquiring profile parameters of the aircraft;
Generating a fence area based on the profile parameters;
determining at least one measurement target point on the aircraft and generating at least one radio frequency signal emission point outside the fence area associated with the at least one measurement target point; and
generating a moving path according to the position of the at least one radio frequency signal transmitting point, and driving a moving platform carrying a radio frequency signal transmitting antenna to move along the moving path;
when the mobile platform is positioned at the radio frequency signal transmitting point, adjusting the position parameter of the radio frequency signal transmitting antenna to a preset position;
and driving a mobile platform carrying a radio frequency signal transmitting antenna to move along the moving path, and transmitting a preset radio frequency signal to a measurement target point corresponding to each radio frequency signal transmitting point at each radio frequency signal transmitting point according to preset test parameters.
2. The method for testing the electromagnetic environment of the aircraft according to claim 1, wherein adjusting the position parameter of the rf signal transmitting antenna to a preset position when the mobile platform is located at the rf signal transmitting point comprises:
controlling the radio frequency signal transmitting antenna to move back and forth along a first direction through a first adjusting operation;
And controlling the radio frequency signal transmitting antenna to move back and forth along a second direction through a first adjusting operation, wherein the first direction and the second direction are mutually perpendicular.
3. The method according to claim 1, wherein driving the mobile platform carrying the rf signal transmitting antenna along the moving path to sequentially transmit the predetermined rf signal to the measurement target point corresponding to each rf signal transmitting point at each rf signal transmitting point according to the preset test parameters comprises:
generating a test curve according to the received data;
and determining whether the test curve is abnormal or not according to the slope and/or the value of the test curve in a preset angle range.
4. The method of electromagnetic environment testing of an aircraft of claim 1, wherein the generating a fence area based on the profile parameters comprises:
calculating a safety distance according to the preset moving speed and/or the positioning accuracy of the moving platform; and
and taking an area formed after the area corresponding to the profile parameter is extended as the fence area based on the safety distance.
5. The method of electromagnetic environment testing of an aircraft according to claim 1, wherein said generating at least one radio frequency signal emission point associated with said at least one measurement target point outside said fence area comprises:
And forming a target circular track by taking the position of each measurement target point as the circle center, arranging at least two marking points on the target circular track at equal intervals, and taking the marking points outside the fence area as the radio frequency signal emission points associated with the measurement target points.
6. The method of claim 5, wherein the determining at least one measurement target point on the aircraft comprises:
and acquiring at least one of a head area, a tail area, a flank area and a fuselage area of the aircraft as a set area, so as to select the at least one measurement target point from the set area.
7. The method of claim 1, wherein generating a movement path from the location of the at least one radio frequency signal emission point comprises:
acquiring the current position of the mobile platform;
and determining the moving path based on a preset path optimization algorithm according to the current position of the moving platform and the positions of all the radio frequency signal transmitting points, wherein the moving path is the shortest path passing through all the radio frequency signal transmitting points, and the moving path is positioned outside the fence area.
8. The method of electromagnetic environment testing of an aircraft according to any one of claims 1-7, further comprising:
at each radio frequency signal transmitting point, the mobile platform transmits a low frequency radio frequency signal and a high frequency radio frequency signal to a corresponding measurement target point; and/or
At each radio frequency signal emission point, the mobile platform emits a horizontally polarized radio frequency signal and a vertically polarized radio frequency signal to a corresponding measurement target point.
9. An electromagnetic environment testing system for an aircraft, comprising:
the mobile platform is internally provided with at least one cavity;
a controller disposed within the cavity, the controller comprising a memory for storing instructions and data and a processor for performing the steps in the electromagnetic environment testing method of the aircraft of any one of claims 1-8.
10. The electromagnetic environment testing system of an aircraft of claim 9, further comprising:
the antenna lifting platform is arranged on the surface of the mobile platform, which is away from the ground;
the radio frequency signal transmitting antenna is arranged at the top of the antenna lifting platform;
The antenna lifting platform comprises a first folding arm and a second folding arm, and the first folding arm and the second folding arm receive the control of the controller so as to control the radio frequency signal transmitting antenna to move back and forth in a first direction through a first adjusting operation;
and controlling the radio frequency signal transmitting antenna to move back and forth in a second direction through a first adjusting operation, wherein the first direction and the second direction are mutually perpendicular.
11. The electromagnetic environment testing system of an aircraft of claim 10, further comprising:
the radio frequency transmitting assembly is arranged in the cavity and is electrically connected with the radio frequency transmitting antenna through a cable so as to drive the radio frequency signal transmitting antenna to transmit the preset radio frequency signal, wherein the antenna lifting platform is provided with a hollow part so as to accommodate the cable.
12. The electromagnetic environment testing system of an aircraft of claim 11, further comprising:
the mobile platform comprises a first battery assembly and a second battery assembly, wherein the first battery assembly is electrically connected with a driving mechanism of the mobile platform, and the second battery assembly is electrically connected with the radio frequency emission assembly, and the first battery assembly and the second battery assembly are mutually independent.
13. The electromagnetic environment testing system of an aircraft of claim 12, further comprising:
the first laser radar and the second laser radar are respectively arranged at two sides of the mobile platform, and the first laser radar and the second laser radar are used for acquiring the outline parameters of the aircraft in a target scene.
14. The electromagnetic environment testing system of an aircraft of claim 9, further comprising:
the first positioning antenna and the second positioning antenna are respectively arranged on two sides of the mobile platform, and the first positioning antenna and the second positioning antenna are used for determining the position of the mobile platform based on a dual-mode differential mode.
15. The electromagnetic environment testing system of an aircraft of claim 9, further comprising:
the first anti-collision rod and the second anti-collision rod are respectively arranged on two opposite side edges of the movable platform.
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| CN202310058859.7A CN116008674A (en) | 2023-01-13 | 2023-01-13 | Electromagnetic environment testing method and system for aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116435751A (en) * | 2023-06-13 | 2023-07-14 | 南京纳特通信电子有限公司 | Motion transfer device and motion transfer method |
| CN117517847A (en) * | 2024-01-04 | 2024-02-06 | 南京纳特通信电子有限公司 | Miniaturized movable K-band broadband radiation testing system and method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116435751A (en) * | 2023-06-13 | 2023-07-14 | 南京纳特通信电子有限公司 | Motion transfer device and motion transfer method |
| CN116435751B (en) * | 2023-06-13 | 2023-09-15 | 南京纳特通信电子有限公司 | Motion transfer device and motion transfer method |
| CN117517847A (en) * | 2024-01-04 | 2024-02-06 | 南京纳特通信电子有限公司 | Miniaturized movable K-band broadband radiation testing system and method |
| CN117517847B (en) * | 2024-01-04 | 2024-04-09 | 南京纳特通信电子有限公司 | Miniaturized movable K-band broadband radiation testing system and method |
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