Method and apparatus for calculating aircraft position information, and device and storage medium

Abstract

The present application relates to the technical field of avionics. Provided are a method and apparatus for calculating aircraft position information, and a device and a storage medium, which are used for improving the calculation accuracy of aircraft position information. The method mainly comprises: acquiring first Gaussian plane coordinates and second Gaussian plane coordinates which respectively correspond to two pieces of distance measure equipment (DME), and acquiring a first horizontal projection distance and a second horizontal projection distance between the two pieces of DME and an aircraft slant range respectively; calculating Gaussian plane projection coordinates of an aircraft on the basis of the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance and the second horizontal projection distance; and performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft, so as to obtain the current longitude and latitude coordinates of the aircraft.

Description

Method, device, equipment and storage medium for calculating aircraft position information Technical Field

[0001] The present application relates to the field of avionics technology, and in particular to a method, device, equipment, and storage medium for calculating aircraft position information. Background Art

[0002] The radio navigation system uses radio technology to measure navigation parameters and is a widely used navigation system. The radio navigation module is mainly composed of VOR (Very High Frequency Omnidirectional Range) and DME (distance measure equipment), which can independently provide position and orientation information to the aircraft. The main function of the distance measurer is to provide the pilot with the slant distance from the aircraft to the ground DME station. It consists of two parts: a ground-based distance measuring beacon and an airborne receiver. The slant distance from the aircraft to the ground beacon is measured through a query and response method. Similar to a satellite navigation system, the best navigation station must first be selected, and then the aircraft is located based on the navigation station. The DME / DME positioning method uses two or more DMEs for positioning. The aircraft's own position is calculated based on the measured distance from the aircraft to the navigation station and the position information of the ground DME station.

[0003] When performing radio navigation DME / DME mode position calculations, the algorithms within the flight management system's DME / DME navigation calculation module largely determine the accuracy of the position calculations. With the continuous upgrading of airborne navigation equipment, the accuracy of DME navigation stations has greatly improved. Therefore, high-precision positioning algorithms are crucial to improving DME / DME navigation positioning accuracy.

[0004] Currently, DME / DME radio navigation position calculations often use an Earth-centered, Earth-fixed coordinate system to calculate the geometric relationship between navigation station range measurements and known parameters such as aircraft altitude. By solving the aircraft's position coordinates in the Earth-centered, Earth-fixed coordinate system and converting the results to latitude, longitude, and altitude coordinates, the aircraft's current position is determined. Because the Earth is a complex sphere with an irregular surface, traditional methods use the average Earth radius as a constant value for calculations and ignore navigation station and aircraft altitude information. While this approach may ultimately meet the RNP requirement of less than 2nm, it introduces significant unnecessary errors. Furthermore, as latitude increases, the actual Earth radius decreases, differing from the equatorial radius by more than 20km. Continuing to use a fixed Earth radius value will further increase positioning errors. To address the significant errors associated with traditional methods, the Earth-centered, Earth-fixed coordinate system, based on the WGS84 ellipsoid, can approximate the Earth's radius at that latitude based on known latitude information and the ellipsoid's flattening. However, this approximation inevitably introduces significant errors. Furthermore, the Earth radius at the aircraft's current location cannot be accurately calculated, further increasing positioning errors.

[0005] Summary of the Invention

[0006] Embodiments of the present application provide a method, apparatus, computer device, and storage medium for calculating aircraft position information, which are used to improve the calculation accuracy of aircraft position information.

[0007] An embodiment of the present invention provides a method for calculating aircraft position information, the method comprising:

[0008] Obtain first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to the two distance measuring machines (DMEs), respectively; and obtain first horizontal projection distances and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively;

[0009] Calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0010] Performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0011] An embodiment of the present invention provides a device for calculating aircraft position information, the device comprising:

[0012] An acquisition module is configured to acquire first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to two distance measuring machines (DMEs), and acquire first horizontal projection distances and second horizontal projection distances of slant ranges between the two DMEs and the aircraft, respectively.

[0013] a calculation module, configured to calculate the Gaussian plane projection coordinates of the aircraft based on the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0014] The inverse calculation module is used to perform Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0015] A computer program product includes a computer program, wherein the computer program implements the above-mentioned method for calculating aircraft position information when executed by a processor.

[0016] The present invention provides a method, apparatus, computer device, and storage medium for calculating aircraft position information. The method first obtains first and second Gaussian plane coordinates corresponding to two distance measuring devices (DMEs), respectively; and obtains first and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively. The Gaussian plane projection coordinates of the aircraft are then calculated based on the first and second Gaussian plane coordinates, the first and second horizontal projection distances; and finally, Gaussian coordinate inverse calculation is performed on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft. Compared to the prior art method of calculating aircraft position using an Earth-centered, Earth-fixed coordinate system, the present application calculates the aircraft's position by combining the Gaussian plane coordinates of the two DMEs and the aircraft's altitude, thereby improving the accuracy of aircraft position information calculation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] FIG1 is a flow chart of a method for calculating aircraft position information provided by this application;

[0018] FIG2 is a flow chart of an architecture of a method for calculating aircraft position information provided by the present application;

[0019] FIG3 is a geometric diagram of a horizontally positioned DME / DME provided in this application;

[0020] FIG4 is a block diagram of the DME / DME mode position calculation provided by this application;

[0021] FIG5 is a schematic diagram of the structure of a device for calculating aircraft position information provided by the present application;

[0022] FIG6 is a schematic diagram of a computer device provided in this application. DETAILED DESCRIPTION

[0023] In order to better understand the above technical solution, the technical solution of the embodiment of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiment of the present application and the specific features in the embodiment are detailed descriptions of the technical solution of the embodiment of the present application, rather than limitations on the technical solution of the present application. In the absence of conflict, the embodiment of the present application and the technical features in the embodiment can be combined with each other.

[0024] In this embodiment, in order to better understand the calculation method of aircraft position information, the relevant parameters involved in this embodiment are described below, as follows:

[0025] 1) Aircraft position parameters B, L, and H represent latitude, longitude, and altitude respectively;

[0026] 2) Equatorial radius (semi-major axis) of the reference ellipsoid: a = 6378137 m;

[0027] 3) Polar radius (semi-minor axis) of the reference ellipsoid: b = 6356752.3142 m;

[0028] 4) Pi: pi = 3.1415926535897932;

[0029] 5) Flattening: f = 298.257223563;

[0030] 6) The first eccentricity of the reference ellipsoid:

[0031] 7) The first eccentricity of the reference ellipsoid:

[0032] 8) The square of the first eccentricity of the reference ellipsoid: e 2 =0.00669437999014;

[0033] 9) Meridian curvature radius:

[0034] 10) Radius of curvature of the Maoyou circle:

[0035] 11) Central meridian longitude L0: Divide the integer part of the local meridian by 6, add 1 to the integer part of the quotient, multiply the result by 6, and subtract 3 (6-degree zone).

[0036] Please refer to FIG. 1 and FIG. 2 , which illustrate a method for calculating aircraft position information provided by an embodiment of the present invention. The method specifically includes steps S101 to S103:

[0037] Step S101 : obtaining first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to two distance measuring machines (DMEs) respectively; and obtaining first horizontal projection distances and second horizontal projection distances of slant ranges between the two DMEs and the aircraft respectively.

[0038] It should be noted that when using the DME / DME system for navigation, the aircraft's distance information relative to two DME stations is required to determine its accurate position. Therefore, it is necessary to ensure that the aircraft can receive valid signals from both DME stations simultaneously. If two DME stations are available on the route, the coordinates of DME station 1 and DME station 2 (i.e., their latitude, longitude, and altitude) are obtained from the navigation database. This facilitates subsequent positioning of the aircraft based on the altitude information provided by the aircraft's altimeter and the distance information from the two DME stations.

[0039] In an optional embodiment provided in the present application, the precise navigation DME / DME mode positioning solution method must be projected on the horizontal plane, and the Gaussian projection forward formula is used to calculate the first Gaussian plane coordinates (x1, y1) and the second Gaussian plane coordinates (x2, y2) corresponding to the two DMEs respectively. In order to avoid negative numbers, this embodiment requires adding 500 km to the calculated y1 and y2 respectively, that is, y1=y1+500000, y2=y2+500000.

[0040] In this embodiment, the Gaussian projection calculation process is as follows (taking the WGS84 ellipsoid as an example), and the Gaussian projection coordinate calculation formula is shown in formula (1):

[0041] Where X is the arc length of the meridian measured from the equator; e 2 =0.00669437999014, which is the square of the first eccentricity of the WGS84 ellipsoid; ρ″=180×60×60 / pi, pi is pi; B i is the latitude of the i-th DME; η = e′cosB i , a = 6378137m is the equatorial radius of the reference ellipsoid; b = 6356752.3142m is the polar radius of the reference ellipsoid, t = tan(Rad_B i ), Rad_B i is the arc value corresponding to the latitude of the i-th DME; l i =(L i -L0) / ρ″,L i is the longitude of the ith DME, L0 is the longitude of the central meridian; L0 is calculated by dividing the integer part of the local meridian by 6, adding 1 to the integer part of the quotient, multiplying the result by 6 and subtracting 3 (6-degree zone).

[0042] It should be noted that (x i ,y i ) is the i-th Gaussian plane coordinate, i = 1 or 2. That is, the first Gaussian plane coordinate (x1, y1) and the second Gaussian plane coordinate (x2, y2) in this embodiment are both calculated by the above formula (1). When calculating different Gaussian plane coordinates, the corresponding DME latitude B needs to be entered. i and longitude L i .

[0043] In this embodiment, let:

[0044] Where AA = A*M is a series of constants. Expand the meridian curvature radius M according to Newton's binomial theorem and take the 8th order term, then we have: M = a0 - a2cos2B i +a4cos4B i -a6cos6B i +a8cos8B i , then the length of the meridian arc measured from the equator is:

[0045] Among them, a0, a2, a4, a6, and a8 are defined constants.

[0046] Let t = tan(Rad_B) and obtain the first Gaussian plane coordinates and the second Gaussian plane coordinates corresponding to the two distance measuring machines DME, including:

[0047] The coordinates of the first and second Gaussian planes are calculated using the following formulas:

[0048] In an optional embodiment provided in the present application, obtaining the first horizontal projection distance and the second horizontal projection distance of the slant range between the two DMEs and the aircraft respectively includes:

[0049] The first horizontal projection distance and the second horizontal projection distance are calculated using the following formula:

[0050] Where d1 is the first horizontal projection distance, d2 is the second horizontal projection distance, H is the aircraft height, R1 and R2 are the slant distances between the two DMEs and the aircraft respectively; H1 and H2 are the heights of the DMEs respectively.

[0051] Step S102 : calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance.

[0052] In an optional embodiment provided in the present application, calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance includes:

[0053] The Gaussian plane projection coordinates of the aircraft are calculated using the following formula: d1 2 =(x-x1) 2 +(y-y1) 2 d2 2 =(x-x2) 2 +(y-y2) 2

[0054] Wherein, (x, y) is the Gaussian plane projection coordinate of the aircraft, (x1, y1) is the first Gaussian plane coordinate, and (x2, y2) is the second Gaussian plane coordinate.

[0055] It should be noted that since there are generally two analytical solutions when solving the actual position, it is necessary to filter the Gaussian plane projection coordinates of the aircraft based on the inertial navigation data. Therefore, a valid inertial navigation position is required to carry out accurate DME / DME mode position calculation.

[0056] In this embodiment, the horizontal projection distance of the slant range between the aircraft and the two DME navigation stations and the plane coordinates of the aircraft's Gaussian coordinate projection point are calculated according to the geometric relationship in Figure 3, and the plane coordinates of the aircraft's true Gaussian coordinate projection point are screened out according to the Gaussian plane coordinates corresponding to the inertial navigation position.

[0057] Step S103 , performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0058] In an optional embodiment provided by the present application, performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft includes:

[0059] The Gauss projection inverse calculation formula is used to calculate the aircraft's geographic coordinates (B, L, H). The x used for calculation is the original value, and y = y-500000. The Gauss coordinate inverse calculation process is as follows:

[0060] in, B and L are the latitude and longitude of the aircraft respectively. t f =tan B f , η f 2 =e′cos 2 B f ,

[0061] In this embodiment, to address the large errors in position calculation based on an Earth-centered, Earth-fixed coordinate system, a DME / DME radio navigation positioning algorithm based on Gaussian projection (Gaussian plane coordinates) is employed to improve the accuracy of DME / DME radio navigation position calculations. The Gaussian plane coordinate system uses the intersection of the central meridian and the equator as the coordinate origin, the projection of the central meridian as the ordinate axis X, with the X-axis oriented northward, and the projection of the equator as the abscissa axis Y, with the Y-axis oriented eastward. Plane projection based on the Gaussian coordinate system offers advantages such as no distortion of the central meridian and no angular distortion (maintaining similar graphics).

[0062] An embodiment of the present invention provides a method for calculating aircraft position information. The method first obtains first and second Gaussian plane coordinates corresponding to two distance measuring machines (DMEs), respectively; and obtains first and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively. Then, based on the first and second Gaussian plane coordinates, the first and second horizontal projection distances, the Gaussian plane projection coordinates of the aircraft are calculated; and finally, Gaussian coordinate inverse calculation is performed on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft. Compared to the prior art method of calculating aircraft position using an Earth-centered Earth-fixed coordinate system, the present application combines the Gaussian plane coordinates of the two DMEs and the aircraft's altitude to calculate the aircraft's position, thereby improving the calculation accuracy of aircraft position information.

[0063] In an application scenario provided by the present invention, a model is constructed based on the calculation method of the above-mentioned aircraft position information to obtain the internal position calculation model of Figure 4. The calculation model mainly includes modules such as basic geometric parameter calculation, slant distance horizontal projection distance calculation, Gaussian coordinate forward calculation, aircraft Gaussian plane coordinate solution and screening, and Gaussian coordinate inverse calculation.

[0064] Model testing and verification of the aforementioned position calculation model were conducted. Based on the established internal position calculation model, flight data from a specific route was tested. By comparing the DME / DME positioning results with inertial navigation data, the DME / DME partial model test results shown in Table 1 below were obtained. These results demonstrate that the proposed positioning algorithm and the established algorithm model have high accuracy. Partial test results are shown in Table 1.

[0065] Table 1

[0066] It should be understood that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0067] In one embodiment, a device for calculating aircraft position information is provided. This device corresponds to the method for calculating aircraft position information in the above embodiment. As shown in FIG5 , the functional modules of the device for calculating aircraft position information are described in detail as follows:

[0068] An acquisition module 51 is configured to acquire first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to two distance measuring machines (DMEs), and to acquire first horizontal projection distances and second horizontal projection distances of slant ranges between the two DMEs and the aircraft, respectively.

[0069] a calculation module 52, configured to calculate the Gaussian plane projection coordinates of the aircraft based on the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0070] The inverse calculation module 53 is used to perform Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0071] In an optional embodiment provided by the present invention, the acquisition module 51 is specifically configured to:

[0072] The coordinates of the first and second Gaussian planes are calculated using the following formulas:

[0073] Where X is the arc length of the meridian measured from the equator, B i is the latitude of the ith DME, t = tan(Rad_B i ), Rad_B i is the arc value corresponding to the latitude of the i-th DME, l i =(L i -L0) / ρ″,L i is the longitude of the ith DME, L0 is the longitude of the central meridian, η=e′cosB i , a is the equatorial radius of the reference ellipsoid; b is the polar radius of the reference ellipsoid, (x i ,y i ) is the Gaussian plane coordinate of the i-th DME, i = 1 or 2.

[0074] In an optional embodiment provided by the present invention, the meridian arc length measured from the equator is determined by the following formula: M=a0-a2cos2B i +a4cos4B i -a6cos6B i +a8cos8Bi

[0075] Among them, a0, a2, a4, a6, and a8 are defined constants.

[0076] In an optional embodiment provided by the present invention, the acquisition module 51 is specifically configured to:

[0077] The first horizontal projection distance and the second horizontal projection distance are calculated using the following formula:

[0078] Where d1 is the first horizontal projection distance, d2 is the second horizontal projection distance, H is the aircraft height, R1 and R2 are the slant distances between the two DMEs and the aircraft respectively; H1 and H2 are the heights of the DMEs respectively.

[0079] In an optional embodiment provided by the present invention, the calculation module 52 is specifically configured to:

[0080] The Gaussian plane projection coordinates of the aircraft are calculated using the following formula: d1 2 =(x-x1) 2 +(y-y1) 2 d2 2 =(x-x2) 2 +(y-y2) 2

[0081] Wherein, (x, y) is the Gaussian plane projection coordinate of the aircraft, (x1, y1) is the first Gaussian plane coordinate, and (x2, y2) is the second Gaussian plane coordinate.

[0082] In an optional embodiment provided by the present invention, the Gaussian plane projection coordinates of the aircraft are filtered according to the inertial navigation data.

[0083] In an optional embodiment provided by the present invention, the back-calculation module 53 is specifically configured to:

[0084] in, B and L are the latitude and longitude of the aircraft respectively. t f =tan B f , η f 2 =e′cos 2 B f , To take the initial value of the iterative method, B f The value of x / a is not much different.

[0085] The specific definitions of the aircraft position information calculation device can be found in the definitions of the aircraft position information calculation method described above and will not be repeated here. Each module in the aforementioned device may be implemented in whole or in part via software, hardware, or a combination thereof. Each module may be embedded in or independent of a processor in a computer device in hardware form, or may be stored in a computer device memory in software form, allowing the processor to call and execute the corresponding operations of each module.

[0086] In one embodiment, a computer device is provided, which may be a server, and its internal structure diagram may be as shown in Figure 6. The computer device includes a processor, memory, a network interface, and a database connected via a system bus. The processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and computer program in the non-volatile storage medium. The network interface of the computer device is configured to communicate with an external terminal via a network connection. When executed by the processor, the computer program implements a method for calculating aircraft position information.

[0087] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the following steps are performed:

[0088] Obtain first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to the two distance measuring machines (DMEs), respectively; and obtain first horizontal projection distances and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively;

[0089] Calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0090] Performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0091] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0092] Obtain first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to the two distance measuring machines (DMEs), respectively; and obtain first horizontal projection distances and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively;

[0093] Calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0094] Performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0095] In one embodiment, a computer program product is provided, the computer program product comprising a computer program, the computer program being executed by a processor to implement the following steps:

[0096] Obtain first Gaussian plane coordinates and second Gaussian plane coordinates corresponding to the two distance measuring machines (DMEs), respectively; and obtain first horizontal projection distances and second horizontal projection distances of the slant ranges between the two DMEs and the aircraft, respectively;

[0097] Calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance;

[0098] Performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

[0099] Those skilled in the art will appreciate that all or part of the processes in the above-mentioned embodiments can be implemented by instructing the relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0100] Those skilled in the art will clearly understand that for the sake of convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.

[0101] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention, and should all be included in the scope of protection of the present invention.

Claims

1. A method for calculating aircraft position information, characterized in that: The method comprises: Obtain the first Gaussian plane coordinates and the second Gaussian plane coordinates corresponding to the two distance measuring machines DME respectively; and obtain the first horizontal projection distance and the second horizontal projection distance of the two DMEs and the aircraft slant range respectively; Calculate the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance; The Gaussian coordinates of the Gaussian plane projection coordinates of the aircraft are inversely calculated to obtain the current latitude and longitude coordinates of the aircraft.

2. The method according to claim 1, characterized in that The obtaining of the first Gaussian plane coordinates and the second Gaussian plane coordinates respectively corresponding to the two distance measuring machines DME comprises: The first Gaussian plane coordinates and the second Gaussian plane coordinates are calculated by the following formula: Where X is the arc length of the meridian measured from the equator, B i is the latitude of the ith DME, t = tan(Rad_B i ), Rad_B i is the radian value corresponding to the latitude of the i-th DME, l i =(L i -L0) / ρ″,L i is the longitude of the ith DME, L0 is the longitude of the central meridian, η=e′cosB i , a is the equatorial radius of the reference ellipsoid; b is the polar radius of the reference ellipsoid, (x i ,y i ) is the Gaussian plane coordinate of the i-th DME, i = 1 or 2.

3. The method according to claim 2, characterized in that The arc length of the meridian measured from the equator is determined by the following formula: M=a0-a2cos2B i +a4cos4B i -a6cos6B i +a8cos8B i Among them, a0, a2, a4, a6, and a8 are defined constants.

4. The method according to claim 1, characterized in that: The method of obtaining the first horizontal projection distance and the second horizontal projection distance of the slant range between the two DMEs and the aircraft respectively comprises: The first horizontal projection distance and the second horizontal projection distance are calculated by the following formula: Wherein, d1 is the first horizontal projection distance, d2 is the second horizontal projection distance, H is the aircraft height, R1 and R2 are the slant distances between the two DMEs and the aircraft respectively; H1 and H2 are the heights of the DMEs respectively.

5. The method according to claim 2, characterized in that: Calculating the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance includes: The Gaussian plane projection coordinates of the aircraft are calculated by the following formula: d1 2 =(x-x1) 2 +(y-y1) 2 d2 2 =(x-x2) 2 +(y-y2) 2 Among them, (x, y) is the Gaussian plane projection coordinates of the aircraft, (x1, y1) is the first Gaussian plane coordinates, and (x2, y2) is the second Gaussian plane coordinates.

6. The method according to claim 4, characterized in that The method further comprises: The Gaussian plane projection coordinates of the aircraft are filtered according to the inertial navigation data.

7. The method according to claim 3, characterized in that Performing Gaussian coordinate inversion on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft includes: in, B and L are the latitude and longitude of the aircraft respectively. t f =tanB f , or f 2 =e′cos 2 B f , 8. A device for calculating aircraft position information, characterized in that: The device comprises: An acquisition module is used to acquire the first Gaussian plane coordinates and the second Gaussian plane coordinates corresponding to the two distance measuring machines DME respectively; and to acquire the first horizontal projection distance and the second horizontal projection distance of the slant range between the two DMEs and the aircraft respectively; a calculation module, configured to calculate the Gaussian plane projection coordinates of the aircraft according to the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance, and the second horizontal projection distance; The inverse calculation module is used to perform Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft to obtain the current latitude and longitude coordinates of the aircraft.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the method for calculating the aircraft position information according to any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method for calculating the aircraft position information according to any one of claims 1 to 7 is implemented.

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