Error rapid correction device for formation position keeping equipment

Abstract

The utility model discloses a rapid error correction device for formation position keeping equipment. The rapid error correction device comprises positioning equipment and correction equipment, a prism in the positioning equipment is vertically arranged right below a direction finding antenna of the onboard formation position maintaining equipment, and a total station is placed at a position where the prism can be observed through a tripod; the positioning equipment measures the coordinates of the prism through the total station and positions the placement position of the horn antenna of the external field detector; and an external field detector in the correction equipment establishes connection with the onboard formation position keeping equipment through a horn antenna, measures an angle value and an energy value of a signal sent by the onboard equipment through the horn antenna, and transmits the angle value and the energy value to the airplane, so that error correction is implemented by the airplane. According to the technical scheme provided by the utility model, the problems that an airplane needs to be dragged twice and is accurately placed at a specific position, the time consumption is too long, the efficiency is low, manual errors are easily generated and the like in actual implementation in an existing mode for carrying out error calibration on the formation position keeping equipment are solved.

Description

Technical Field

[0001] This utility model relates to, but is not limited to, the field of aircraft testing and maintenance technology, and in particular to a rapid error correction device for formation position holding equipment. Background Technology

[0002] Formation keeping equipment is primarily used for instrument formation flying between aircraft. It has the capabilities of ranging, positioning, information transmission, and proximity alerting; it can provide the lateral, longitudinal, and altitude distances of each member relative to the aircraft itself for situational information display; it can provide the lateral, longitudinal, and altitude differences between the aircraft and the lead aircraft for formation keeping; it can transmit the aircraft's speed, altitude, heading, maneuver commands, and auxiliary commands for flight coordination; and it can support the implementation of ground mission planning for formation formation. The formation keeping equipment achieves these functions by including four direction-finding antennas, which communicate with other aircraft. These four antennas are located at the nose, tail cone, and wingtips of the left and right wings, respectively, and are housed within the airframe structure such as the skin or radome.

[0003] Typically, the output results of the direction-finding antenna of the formation position-maintaining equipment will have a certain error compared with the required results. This error comes from the following two factors:

[0004] 1) Installation errors during the installation of the direction-finding antenna;

[0005] 2) The direction-finding antenna is located inside the airframe structure such as the skin or radome. The airframe structure can change the direction of signal propagation, resulting in inaccurate signals received by the direction-finding antenna.

[0006] Currently, when calibrating the formation position keeping equipment, the aircraft needs to be towed twice and placed precisely in a specific position. In practice, this is too time-consuming, inefficient, and prone to human error. Utility Model Content

[0007] The purpose of this utility model is to solve the above-mentioned technical problems. This utility model provides a rapid error correction device for formation position holding equipment, which solves the problems of existing methods for error calibration of formation position holding equipment, which require towing the aircraft twice and placing the aircraft precisely in a specific position. In actual implementation, this method is too time-consuming, inefficient, and prone to human error.

[0008] The technical solution of this utility model: This utility model embodiment provides a rapid error correction device for formation position holding equipment, including: a positioning device and a correction device;

[0009] The positioning device includes: a total station 1, a prism 13, a tripod, and a plumb line; the prism 13 is set directly below the direction-finding antenna of the formation position holding device on the aircraft by a plumb line, and the total station 1 is placed on a tripod at a position where the prism 13 can be observed, and there are no obstructions on the path between the prism 13 and the total station 1.

[0010] The positioning device is used to locate the placement position of the horn antenna 21 of the field testing instrument 14 by measuring the coordinates of the prism 13 using the total station 1.

[0011] The calibration equipment includes: an outdoor testing instrument 14 and a horn antenna 21 connected to the outdoor testing instrument 14 via a high-frequency cable 19; the outdoor testing instrument 14 is used to establish a connection with the onboard formation position maintenance equipment via the horn antenna 21 to exchange data; it is also used to measure the angle value and energy value of the signal transmitted by the airborne equipment via the horn antenna 21 and transmit them to the aircraft for error correction by the aircraft.

[0012] Optionally, in the error quick correction device for formation position holding equipment as described above, the total station 1 includes: a handle 2, a battery compartment 3, a base 4, a foot screw 5, a base fixing screw 6, an operating interface 7, a horizontal fine-motion turntable 8, a vertical fine-motion turntable 9, an objective lens 10, and a coarse sight 12.

[0013] The base 4 of the total station 1 is connected to the bottom of the total station 1 by multiple base fixing screws 6. The total station 1 is connected to the tripod through the base 4 at its bottom. The level of the total station 1 is adjusted by multiple leveling screws 5 set at the bottom of the base 4. A level is set on the base 4. A lifting handle 2 is set on the top of the total station 1.

[0014] The total station 1 has a battery compartment 3 on its lower side for storing batteries, and an operation interface 7 on its lower front for operating the total station 1. The objective lens 10 is installed in the open area in the middle of the total station 1 and is connected to the horizontal fine adjustment dial 8 and the vertical fine adjustment dial 9, so that the horizontal and vertical angles of the objective lens 10 can be finely adjusted by the horizontal fine adjustment dial 8 and the vertical fine adjustment dial 9, respectively. The coarse aiming device 12 is located on the top of the objective lens 10.

[0015] The total station 1 is used to aim at the position of the prism 13 through the coarse aiming device 12, and then to fine-tune the objective lens 10 by using the horizontal fine-motion turntable 8 and the vertical fine-motion turntable 9 to initially align it with the prism 13. Thus, by operating the operation interface 7, the objective lens 10 is accurately aligned with the prism 13, so that the coordinates of the prism 13 relative to the total station 1 can be observed through the objective lens 10.

[0016] Optionally, in the error rapid correction device for formation position holding equipment as described above,

[0017] The alignment requirements for the objective lens 10 and the prism 13 are as follows: the objective lens 10 is accurately aligned with the center of the prism 13 in order to observe the coordinates of the prism 13 relative to the total station 1, and after the objective lens 10 and the prism 13 are aligned, they are used to automatically track the prism 13 in real time.

[0018] Optionally, in the error rapid correction device for formation position holding equipment as described above, the total station 1 further includes: target illumination light 11;

[0019] The target illumination light 11 is positioned on the upper side of the objective lens 10 and is oriented in the same direction as the objective lens 10. It is used to assist the illumination prism 13 in improving visibility when the external environment is dark.

[0020] Optionally, in the error rapid correction device for formation position holding equipment as described above,

[0021] The front end of the field tester 14 is provided with a display screen 16 and an operation panel 15. The top of the field tester 14 is provided with a charging interface 17 and a high-frequency cable interface 18. The field tester 14 is charged by an external 220V power supply through the charging interface 17 and the power cord. The field tester 14 is connected to the horn antenna 21 through the high-frequency cable interface 18 and the high-frequency cable 19.

[0022] Optionally, in the error quick correction device for formation position holding equipment as described above, the correction device further includes: a telescopic tripod 20;

[0023] The horn antenna 21, which is connected to the field test instrument 14 via a high-frequency cable 19, is mounted on a telescopic tripod 20. The telescopic tripod 20 can display the telescopic range and is used to raise the horn antenna 21 to the same height as the onboard detection and direction-finding antenna.

[0024] Optionally, in the above-described error rapid correction device for formation position holding equipment, the on-board formation position holding equipment has a total of 4 direction-finding antennas, which are respectively arranged at the nose, tail cone, and wingtips of the left and right wings.

[0025] By sequentially placing prism 13 directly below each of the four direction-finding antennas, the four direction-finding antennas currently corresponding to the placement of prism 13 are taken as the current direction-finding antennas to be tested, and the error correction of the current direction-finding antennas to be tested is completed by the calibration device.

[0026] The beneficial effects of this utility model are as follows: This utility model provides a rapid error correction device for formation position holding equipment. The main body of the rapid error correction device includes two parts: a positioning device and a correction device. The positioning device uses a total station 1 and a prism 13 to locate the placement position of the horn antenna 21 of the field detector 14. The correction device uses the horn antenna 21 to establish a connection between the field detector 14 and the onboard formation position holding equipment for data exchange. Furthermore, the horn antenna 21 measures the angle and energy values ​​of the signals transmitted by the airborne equipment and transmits them to the aircraft for error correction. Using the rapid error correction device provided by this utility model to correct the errors of each direction-finding antenna of the formation position holding equipment, the aircraft remains in the same position throughout the correction process, avoiding the need to tow the aircraft. Since the aircraft does not need to be towed, the aircraft power supply can be changed from APU power supply to power cart power supply, thereby reducing the number of personnel required, improving work efficiency, effectively eliminating errors caused by towing the aircraft, and improving correction accuracy. Attached Figure Description

[0027] The accompanying drawings are provided to further illustrate the technical solution of this utility model and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solution of this utility model and do not constitute a limitation on the technical solution of this utility model.

[0028] Figure 1 This is a schematic diagram of the positioning device in the error rapid correction device for formation position holding equipment provided in an embodiment of the present invention;

[0029] Figure 2 This is a schematic diagram of the structure of the correction device in the error rapid correction device for formation position holding equipment provided in an embodiment of the present invention;

[0030] Figure 3 The diagram shown is a schematic representation of the principle of using the error rapid correction device provided in a few embodiments of this utility model to correct the error of the direction-finding antenna of the formation position keeping equipment on an aircraft.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. Total station, 2. Lifting handle, 3. Battery compartment, 4. Base, 5. Anchor screws, 6. Base fixing screws, 7. Operating interface, 8. Horizontal micro-motion dial, 9. Vertical micro-motion dial, 10. Objective lens, 11. Target illumination light, 12. Coarse sight, 13. Prism, 14. Field inspection instrument, 15. Operating panel, 16. Display screen, 17. Charging interface, 18. High-frequency cable interface, 19. High-frequency cable, 20. Telescopic tripod, 21. Horn antenna. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0034] The background section has already explained the function and structure of the formation position maintenance equipment, as well as the reasons for the certain error between the output results of its direction-finding antenna and the required results.

[0035] When performing error correction on formation holding equipment, a specialized field testing instrument is required. This instrument simulates another formation holding device, measuring the angle and energy values ​​of the signals transmitted by the onboard equipment. Based on the data, the onboard equipment parameters are modified to eliminate errors at the software level. The specific method is as follows:

[0036] 1) When calibrating the nose and tail cone direction-finding antennas, place the field tester antenna on the extension line of the aircraft's centerline; when calibrating the left and right wingtip direction-finding antennas, place the field tester on a straight line perpendicular to the aircraft's centerline and passing through the wingtip direction-finding antennas. There are no requirements on the distance between the field tester antenna and the direction-finding antenna being measured, but the distances of the field tester antennas in all four directions from the corresponding direction-finding antennas on the aircraft must be consistent.

[0037] 2) Set the parameters of the field detector to establish a connection with the onboard formation position maintenance equipment.

[0038] 3) Use the field detector to read the angle and energy values ​​of the received onboard signal, and transmit the received angle and energy values ​​to the onboard equipment through the field detector. The correction parameters are calculated by the onboard equipment software.

[0039] Currently, the error correction method for formation keeping equipment mainly uses inertial navigation and airport runway centerline positioning to determine the placement of the field tester antenna. The field tester then measures and calculates the data, rewriting the parameters of the onboard formation equipment. Given the runway centerline magnetic azimuth, the inertial navigation magnetic heading is compared with the runway centerline magnetic azimuth. When they are the same, the aircraft's centerline coincides with the runway centerline. The horn antenna is then placed on the runway centerline at distances of 30, 50, and 80 meters from the nose or tail cone. The field tester reads the angle and energy values ​​of the received onboard signals at these times and transmits these values ​​to the onboard equipment, completing the error correction for the nose and tail cone. By comparing the inertial navigation magnetic heading with the runway centerline magnetic azimuth, when the two are the same and the aircraft centerline differs from the runway centerline by 90°, adjustments are made so that the centerline of the last row of left and right tires of the main landing gear is 3.5m away from the runway centerline. At this time, the direction-finding antenna is located on the runway centerline, and the vertical line of the aircraft centerline where the direction-finding antennas at the left and right wingtips are located coincides with the runway centerline. The horn antenna is placed on the runway centerline at a distance of 30, 50, and 80m from the direction-finding antennas at the left and right wingtips. The angle and energy values ​​of the received onboard signals are read using an outside field detector, and the received angle and energy values ​​are transmitted to the onboard equipment through the outside field detector to complete the error correction of the left and right wingtips.

[0040] When testing formation positioning equipment using the existing error correction methods, the aircraft needs to be towed twice and precisely placed in a specific position. In practice, this is too time-consuming, inefficient, and prone to human error. In addition, to avoid the problem of power vehicle cables being dragged during the aircraft towing process, the power vehicle is not used and APU power is used instead. When using APU, mechanical and specialized personnel are required throughout the process, which wastes human resources.

[0041] To address the aforementioned problems, this utility model provides a device for rapid error correction in formation position holding equipment.

[0042] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they will not be described again in some embodiments.

[0043] The error rapid correction device for formation position holding equipment provided in this embodiment of the utility model mainly includes: a positioning device and a correction device. Figure 1 This is a schematic diagram of the positioning device in the error rapid correction device for formation position holding equipment provided in an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure of the correction device in the error rapid correction device for formation position holding equipment provided in the embodiment of this utility model.

[0044] like Figure 1As shown, the positioning device in this embodiment of the present invention includes: a total station 1, a prism 13, a tripod, and a plumb line; in this embodiment of the present invention, the prism 13 is set directly below the direction-finding antenna of the onboard formation position-maintaining device by means of a plumb line, the total station 1 is placed on the tripod at a position where the prism 13 can be observed, and there is no obstruction on the path between the prism 13 and the total station 1; and the total station 1 is adjusted to be in a horizontal state.

[0045] The positioning device of this utility model uses a total station 1 to measure the coordinates of the prism 13 to locate the placement position of the horn antenna 21 of the field testing instrument 14, so that the horn antenna 21 of the calibration device can be placed at the located position for measurement during subsequent testing.

[0046] like Figure 2 As shown, the calibration device in this embodiment of the present invention includes: an outdoor testing instrument 14, and a horn antenna 21 connected to the outdoor testing instrument 14 via a high-frequency cable 19; the outdoor testing instrument 14 establishes a connection with the onboard formation position maintenance equipment via the horn antenna 21 to exchange data; and the outdoor testing instrument 14 measures the angle value and energy value of the signal sent by the airborne equipment via the horn antenna 21, and then transmits the calculated values ​​to the aircraft so that the aircraft can complete the error correction.

[0047] In one implementation of this utility model embodiment, such as Figure 1 As shown, the total station 1 includes the following components: a lifting handle 2, a battery compartment 3, a base 4, foot screws 5, a base fixing screw 6, an operating interface 7, a horizontal fine-motion dial 8, a vertical fine-motion dial 9, an objective lens 10, and a coarse sight 12.

[0048] In this implementation, the base 4 of the total station 1 is connected to the bottom of the total station 1 by multiple base fixing screws 6. The total station 1 is connected to the tripod through the base 4 at its bottom, and the level of the total station 1 is adjusted by multiple leveling screws 5 set at the bottom of the base 4. A level is set on the base 4. A lifting handle 2 is set on the top of the total station 1 to facilitate the movement of the total station 1.

[0049] In this implementation, a battery compartment 3 is provided on the lower side of the total station 1 for storing batteries, and an operation interface 7 is provided at the lower front for operating the total station 1. The objective lens 10 is installed in the open area in the middle of the total station 1 and is connected to the horizontal fine-adjustment dial 8 and the vertical fine-adjustment dial 9, so that the horizontal and vertical angles of the objective lens 10 can be finely adjusted by the horizontal fine-adjustment dial 8 and the vertical fine-adjustment dial 9, respectively. The coarse aiming device 12 is provided on the top of the objective lens 10.

[0050] In this embodiment of the invention, the total station 1 is used to aim at the position of the prism 13 through the coarse aiming device 12, and then fine-tunes the objective lens 10 by using the horizontal fine-adjustment dial 8 and the vertical fine-adjustment dial 9 to initially align it with the prism 13. Then, by operating the operation interface 7, the objective lens 10 is accurately aligned with the prism 13, allowing the coordinates of the prism 13 relative to the total station 1 to be observed through the objective lens 10. In specific implementations, it is required that automatic alignment be selected through the operation interface 7 to ensure that the objective lens 10 is accurately aligned with the center of the prism 13.

[0051] The requirements state that, in this embodiment of the utility model, the objective lens 10 must be aligned with the center of the prism 13 in order to observe the coordinates of the prism 13 relative to the total station 1, and after the objective lens 10 is aligned with the prism 13, it is used to automatically track the prism 13 in real time.

[0052] Furthermore, the total station 1 in this implementation also includes: target illumination light 11; such as Figure 1 As shown, the target illumination light 11 is positioned on the upper side of the objective lens 10 and is in the same direction as the objective lens 10. It is used to assist the illumination prism 13 in improving visibility when the external environment is dark.

[0053] In one implementation of this utility model embodiment, such as Figure 2 As shown, the front end of the field tester 14 is equipped with a display screen 16 and an operation panel 15, and the top of the field tester 14 is equipped with a charging interface 17 and a high-frequency cable interface 18. The field tester 14 is charged by an external 220V power supply through the charging interface 17 and the power cord. The field tester 14 is connected to the horn antenna 21 through the high-frequency cable interface 18 and the high-frequency cable 19.

[0054] In this implementation, the display screen 16 and the operation panel 15 are used to operate the field detector 1; the field detector 1 can establish a connection with the on-board formation position maintenance equipment through the horn antenna 21 and exchange data; and the horn antenna 21 can receive signals from the formation position maintenance equipment.

[0055] Furthermore, the calibration device in this implementation also includes: a telescopic tripod 20; such as Figure 2 As shown, the horn antenna 21, which is connected to the field tester 14 via a high-frequency cable 19, is mounted on a telescopic tripod 20. The telescopic tripod 20 can display the telescopic range and is used to raise the horn antenna 21 to a height that is basically consistent with the height of the on-board detection and direction-finding antenna. For example, the horn antenna 21 can be raised to a maximum height of 7m.

[0056] It should be noted that in this embodiment of the present invention, the aircraft formation position keeping device of the object being tested has a total of 4 direction-finding antennas, which are respectively arranged at the nose, tail cone, and wingtips of the left and right wings. Therefore, when using the error rapid correction device to correct the error of the formation position keeping device, it is necessary to place the prism 13 directly below each of the 4 direction-finding antennas in sequence, and take the 4 direction-finding antennas currently corresponding to the prism 13 as the current direction-finding antennas to be tested, and cooperate with the correction device to complete the error correction of the current direction-finding antennas to be tested.

[0057] Based on the error rapid correction device for formation position holding equipment provided in the above embodiments of this utility model, this utility model also provides an error rapid correction method for formation position holding equipment. The error rapid correction method for formation position holding equipment is performed using the error rapid correction device provided in any of the above embodiments, through the following steps:

[0058] Step 1: Check that the antenna error correction device used for formation position holding equipment is in good working order and meets the functional check requirements;

[0059] Step 2: Position prism 13 vertically directly below one of the direction-finding antennas of the onboard formation holding device;

[0060] Step 3: Place the total station 1 in a position where the prism 13 can be observed, and ensure that there are no obstructions on the path between the prism 13 and the total station 1. Check that the total station 1 is well connected to the tripod, and adjust the level screws 5 to make the total station 1 reach a horizontal state.

[0061] Step 4: Start the total station 1 and use the built-in dual-distance eccentricity measurement function to measure the coordinates of the prism 13. Calculate the coordinates of the placement position of the horn antenna 21 based on the coordinates. The placement position should be 30m horizontally in front of the direction-finding antenna in theory.

[0062] Step 5: Move the prism 13 so that its coordinates are the same as the calculated coordinates, place the horn antenna 21 in the calculated placement position, check that the horn antenna 21 is well connected to the telescopic tripod 20 and the field tester 14, and adjust the height of the horn antenna 21 so that the height of the horn antenna 21 is approximately the same as the height of the direction finding antenna of the aircraft formation position maintenance equipment.

[0063] Step 6: Start the field detector 14, adjust the parameters of the on-board formation position keeping device and the field detector 14 so that the field detector 14 can receive the signal from the on-board formation position keeping device and display that it has entered the network;

[0064] Step 7: Measure the angle and energy values ​​of the signal received from the aircraft at this time using the field detector 14, and record the data;

[0065] Step 8: Repeat steps 4 to 7 to place the horn antenna 21 at a horizontal distance of 50 and 80 m directly in front of the direction-finding antenna, respectively, to perform the measurement.

[0066] Step 9: Process the three sets of data recorded in steps 4 to 8, calculate the average value, and input the average value into the onboard equipment through the field detector 14 to complete the error correction of one direction finding antenna.

[0067] Step 10: There are a total of 4 direction-finding antennas on the aircraft formation position maintenance equipment. Repeat steps 2 to 9 until the error correction of the 4 direction-finding antennas is completed.

[0068] Step 11: Restore the aircraft to its normal operating condition and properly store the antenna error correction device used for formation position maintenance equipment.

[0069] This utility model provides a rapid error correction device for formation position holding equipment. The main body of the device comprises two parts: a positioning device and a correction device. The positioning device uses a total station 1 and a prism 13 to determine the placement position of the horn antenna 21 of the field detector 14. The correction device uses the horn antenna 21 to establish a connection between the field detector 14 and the onboard formation position holding equipment for data exchange. Furthermore, the horn antenna 21 measures the angle and energy values ​​of the signals transmitted by the airborne equipment and transmits them to the aircraft for error correction. Using this rapid error correction device to correct the errors of each direction-finding antenna of the formation position holding equipment ensures that the aircraft remains in the same position throughout the correction process, avoiding the need to tow the aircraft. Since the aircraft is not towed, the aircraft power supply can be changed from APU power to power cart power, thereby reducing the number of personnel required, improving work efficiency, effectively eliminating errors caused by towing the aircraft, and improving correction accuracy.

[0070] The following is an example illustrating how to use the error rapid correction device for formation position holding equipment provided by this utility model.

[0071] Implementation Example

[0072] like Figure 3 The diagram shown illustrates the principle of using the rapid error correction device provided in a few embodiments of this invention to correct errors in the direction-finding antenna of an aircraft formation position-keeping device. The rapid error correction method provided in this embodiment includes:

[0073] 1) Error correction was performed on the direction-finding antennas installed on the left and right wings.

[0074] like Figure 3As shown, taking the measurement of the left wing direction-finding antenna as an example, the straight line containing C and D is the straight line containing the left and right wing direction-finding antennas, and this straight line is perpendicular to the aircraft's centerline. Two points C and D are selected on this straight line (points C and D are located by the laser instrument illuminating the marked points on the wing perpendicularly). The prism 13 of the total station 1 is placed on these two measurement points, and the vertex of the two-point prism is aligned with the measurement points so that the mirror surface faces the total station 1. The total station 1 is placed at any position where all points on the straight line CD can be observed simultaneously (such as point K), and there should be no obstructions on the path.

[0075] First, use total station 1 to measure the distance and angle values ​​to points C and D respectively. Then, set the distance between the field testing instrument antenna and the direction-finding antenna on total station 1 to 30m, 50m, and 80m (i.e., distances DE, DF, and DG in the diagram). Use the built-in dual-distance eccentricity measurement function of total station 1 to calculate the distance and angle values ​​between the placement position of the field testing instrument antenna and total station 1. To ensure measurement accuracy, select three antenna placement positions: far, medium, and near distance (i.e., positions E, F, and D in the diagram). Use total station 1 to track prism 13, and move prism 13 until the distance and angle values ​​of the prism are the same as the results calculated by the dual-distance eccentricity measurement. Place the field testing instrument antenna at this point. Set parameters on the aircraft and on the field testing instrument 14, confirm successful communication between the field testing instrument 14 and the aircraft, and use the field testing instrument 14 to measure the angle and energy values. The angle and energy values ​​at three positions (far, medium, and near) are measured, the average is taken, and the compensation parameters of the direction-finding antenna on that side are calculated by the field test instrument 14. The compensation parameters are then input into the formation position maintenance equipment on the aircraft to complete the error correction.

[0076] It should be noted that the error correction method for the right wing direction-finding antenna is the same as that for the left wing direction-finding antenna.

[0077] After the calibration is completed, place the antenna of the field inspection instrument of the formation position holding device at a distance and measure the angle value again. At this time, the measured angle value should be basically consistent with the azimuth of the direction finding antenna, indicating that the error of the direction finding antenna at the wingtip of the left and right wings has been successfully calibrated.

[0078] 2) Error correction of nose and tail cone direction-finding antennas

[0079] like Figure 3As shown, taking the measurement of the tail cone direction-finding antenna as an example, the straight line containing A and B is the straight line containing the nose and tail cone direction-finding antennas, which is the centerline of the aircraft. Two points A and B are selected on this straight line (points A and B are generally placed directly below any antenna in the middle of the fuselage). The prism 13 of the total station 1 is placed at these two points. The total station is placed at any position where all points on the straight line A and B can be observed simultaneously (such as point L). The total station is used to measure the distance and angle values ​​to points A and B respectively. Then, the distances between the field instrument antenna and the direction-finding antenna are set to 30m, 50m, and 80m on the total station (i.e., distances BH, BI, and BJ in the figure). The dual-distance eccentricity measurement function built into the total station is used to calculate the distance and angle values ​​of the field instrument antenna placement position. To ensure measurement accuracy, three antenna placement positions (i.e., positions H, I, and J in the figure) are selected: far, medium, and near distance.

[0080] Using a total station 1, track prism 13 and move prism 13 until its distance and angle values ​​match the calculated results. Place the field detection antenna at this point. Set parameters on the aircraft and on the field detection instrument 14, confirming successful communication between the field detection instrument 14 and the aircraft. Use the field detection instrument 14 to measure angle and energy values. Measure the angle and energy values ​​at three positions (far, medium, and near distance), take the average, and then use the field detection instrument to calculate the compensation parameters for the direction-finding antenna on that side. Input the compensation parameters into the formation position maintenance equipment on the aircraft to complete the error correction. The error correction method for the nose direction-finding antenna is the same as that for the tail cone direction-finding antenna.

[0081] After calibration, place the antenna of the formation position holding equipment field inspection instrument at a distance and measure the angle value again. At this time, the measured angle value should be basically consistent with the direction finding antenna in front, indicating that the direction finding antenna error of the nose and tail cone has been successfully calibrated.

[0082] Although the embodiments disclosed in this utility model are as described above, the content is only for the purpose of facilitating understanding of this utility model and is not intended to limit this utility model. Any person skilled in the art to which this utility model pertains may make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed in this utility model, but the patent protection scope of this utility model shall still be determined by the scope defined in the appended claims.

Claims

1. A rapid error correction device for formation positioning equipment, characterized in that, include: Positioning and calibration equipment; The positioning device includes: a total station (1), a prism (13), a tripod, and a plumb line; the prism (13) is set directly below the direction-finding antenna of the formation position holding device on the aircraft by means of a plumb line, and the total station (1) is placed in a position where the prism (13) can be observed by means of a tripod, and there is no obstruction on the path between the prism (13) and the total station (1); The positioning device is used to locate the placement position of the horn antenna (21) of the field test instrument (14) by measuring the coordinates of the prism (13) with a total station (1); The calibration device includes: an outdoor testing instrument (14) and a horn antenna (21) connected to the outdoor testing instrument (14) via a high-frequency cable (19); the outdoor testing instrument (14) is used to establish a connection with the onboard formation position maintenance equipment via the horn antenna (21) to exchange data; it is also used to measure the angle value and energy value of the signal sent by the airborne equipment via the horn antenna (21) and transmit them to the aircraft for error correction by the aircraft.

2. The error rapid correction device for formation position holding equipment according to claim 1, characterized in that, The total station (1) includes: a handle (2), a battery compartment (3), a base (4), foot screws (5), a base fixing screw (6), an operating interface (7), a horizontal fine-motion dial (8), a vertical fine-motion dial (9), an objective lens (10), and a coarse sight (12); The base (4) of the total station (1) is connected to the bottom of the total station (1) by multiple base fixing screws (6). The total station (1) is connected to the tripod through the base (4) at its bottom. The level of the total station (1) is adjusted by multiple leveling screws (5) set at the bottom of the base (4). A level is set on the base (4). A lifting handle (2) is set on the top of the total station (1). The total station (1) has a battery compartment (3) on its lower side for storing batteries, and an operation interface (7) on its lower front for operating the total station (1) via the operation interface (7); the objective lens (10) is installed in the open area in the middle of the total station (1) and is connected to the horizontal fine adjustment dial (8) and the vertical fine adjustment dial (9) to finely adjust the horizontal and vertical angles of the objective lens (10) respectively via the horizontal fine adjustment dial (8) and the vertical fine adjustment dial (9); the coarse aiming device (12) is located on the top of the objective lens (10); The total station (1) is used to aim at the position of the prism (13) through the coarse aiming device (12), and then to fine-tune the objective lens (10) by using the horizontal fine-adjustment dial (8) and the vertical fine-adjustment dial (9) to initially align it with the prism (13). Thus, by operating the operation interface (7), the objective lens (10) is accurately aligned with the prism (13) so that the coordinates of the prism (13) relative to the total station (1) can be observed through the objective lens (10).

3. The error rapid correction device for formation position holding equipment according to claim 2, characterized in that, The alignment requirements of the objective lens (10) and the prism (13) are as follows: the objective lens (10) is accurately aligned with the center of the prism (13) to observe the coordinates of the prism (13) relative to the total station (1), and after the objective lens (10) and the prism (13) are aligned, they are used to automatically track the prism (13) in real time.

4. The error rapid correction device for formation position holding equipment according to claim 2, characterized in that, The total station (1) also includes: target illumination light (11); The target illumination light (11) is positioned on the upper side of the objective lens (10) and is in the same direction as the objective lens (10). It is used to assist the illumination prism (13) in improving visibility when the external environment is dark.

5. The error rapid correction device for a formation position holding device according to any one of claims 1 to 4, characterized in that, The front end of the field tester (14) is provided with a display screen (16) and an operation panel (15). The top of the field tester (14) is provided with a charging interface (17) and a high-frequency cable interface (18). The field tester (14) is connected to a 220V power supply through the charging interface (17) and the power cord to charge the device. The field tester (14) is connected to the horn antenna (21) through the high-frequency cable interface (18) and the high-frequency cable (19).

6. The error rapid correction device for formation position holding equipment according to claim 5, characterized in that, The calibration device also includes: a telescopic tripod (20); The horn antenna (21) connected to the field tester (14) via a high-frequency cable (19) is mounted on a telescopic tripod (20); the telescopic tripod (20) can display the telescopic amount and is used to raise the horn antenna (21) to the same height as the on-board detection direction finding antenna.

7. The error rapid correction device for a formation position holding device according to any one of claims 1 to 4, characterized in that, The onboard formation position maintaining equipment has four direction-finding antennas, which are respectively located at the nose, tail cone, and wingtips of the left and right wings. By placing the prism (13) directly below each of the four direction-finding antennas in sequence, the four direction-finding antennas currently corresponding to the prism (13) are taken as the current direction-finding antennas to be tested, and the error correction of the current direction-finding antennas to be tested is completed by the calibration device.

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