Data prediction method and device of radio altimeter, equipment and storage medium

Abstract

The invention provides a data prediction method and device for a radio altimeter, equipment and a storage medium. The method comprises the following steps: acquiring measurement data of a radio altimeter of an aircraft, and determining first height information of the aircraft based on the measurement data; acquiring wind field data, temperature data and air pressure data of the aircraft, and determining second height information, third height information and fourth height information based on the wind field data, the temperature data and the air pressure data; and determining final height information of the aircraft based on the first height information, the second height information, the third height information and the fourth height information. In the mode, an information fusion scheme can be provided by combining wind field data, temperature data and air pressure data on the basis of the height measurement function of the radio altimeter, measurement data of a single altimeter sensor is corrected, height measurement under the condition of data loss of the altimeter is realized, and the continuity and effectiveness of the data are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a data prediction method, device, equipment and storage medium for a radio altimeter. Background Art

[0002] Currently, a radio altimeter is an indispensable aircraft navigation sensor. However, under the influence of actual use environment interference, the radio altimeter may lose data or fail to give effective output data within its altitude measurement range, thereby affecting navigation accuracy and even flight safety. Summary of the Invention

[0003] In view of this, the purpose of the present invention is to provide a data prediction method, device, equipment and storage medium for a radio altimeter, so as to propose an information fusion scheme by combining wind field data, temperature data and air pressure data on the basis of the altitude measurement function of the radio altimeter, correct the measurement data of a single altimeter sensor, realize altitude measurement under the condition of altimeter data loss, and improve the continuity and effectiveness of the data.

[0004] In a first aspect, an embodiment of the present invention provides a data prediction method for a radio altimeter. The method includes: obtaining measurement data of a radio altimeter of an aircraft, and determining first altitude information of the aircraft based on the measurement data; obtaining wind field data, temperature data and air pressure data of the aircraft, and respectively determining second altitude information, third altitude information and fourth altitude information based on the wind field data, temperature data and air pressure data; and determining final altitude information of the aircraft based on the first altitude information, second altitude information, third altitude information and fourth altitude information.

[0005] In an optional embodiment of the present application, the step of determining the final altitude information of the aircraft based on the first altitude information, second altitude information, third altitude information and fourth altitude information includes: determining whether the measurement data of the radio altimeter at the current moment is invalid; if the measurement data of the radio altimeter at the current moment is invalid, determining the final altitude information of the aircraft at the current moment based on the first altitude information, second altitude information, third altitude information and fourth altitude information at the previous moment, and the second altitude information, third altitude information and fourth altitude information at the current moment.

[0006] In an optional embodiment of the present application, after the step of determining whether the measurement data of the radio altimeter at the current moment is invalid, the method further includes: if the measurement data of the radio altimeter at the current moment is valid, taking the altitude information at the current moment as the final altitude information of the aircraft at the current moment.

[0007] In an alternative embodiment of the present application, the step of determining whether the measurement data of the radio altimeter at the current moment is invalid includes: if the measurement data of the radio altimeter at the current moment is lost, determining that the measurement data of the radio altimeter at the current moment is invalid; if the measurement data of the radio altimeter at the current moment is not lost, determining that the measurement data of the radio altimeter at the current moment is valid.

[0008] In an alternative embodiment of the present application, the step of determining the final altitude information of the aircraft at the current moment based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information at the previous moment, and the second altitude information, the third altitude information, and the fourth altitude information at the current moment includes: taking the difference between the second altitude information at the current moment and the second altitude information at the previous moment as the second altitude change information; taking the difference between the third altitude information at the current moment and the third altitude information at the previous moment as the third altitude change information; taking the difference between the fourth altitude information at the current moment and the fourth altitude information at the previous moment as the fourth altitude change information; determining the final altitude change information based on the second altitude change information, the third altitude change information, and the fourth altitude change information; and taking the sum of the final altitude change information and the first altitude information at the previous moment as the final altitude information of the aircraft at the current moment.

[0009] In an alternative embodiment of the present application, the aircraft is provided with N sensors, where the N sensors are used to detect the wind field data, temperature data, and air pressure data of the aircraft, and the measured values of the N sensors are respectively the second altitude change information, the third altitude change information, or the fourth altitude change information, and N is greater than or equal to 3.

[0010] In an alternative embodiment of the present application, the step of determining the final altitude change information based on the second altitude change information, the third altitude change information, and the fourth altitude change information includes: taking the minimum value among the measured values of the N sensors as the optimal altitude value; determining the correlation coefficients of the N sensors based on the measured values of the N sensors, a preset resolution coefficient, and the optimal altitude value; determining the degree of association between the measured values of the N sensors and the optimal altitude value based on the correlation coefficients of the N sensors and the preset weight values of the N sensors; taking the sensor with the highest degree of association as the target sensor; and taking the difference between the measured value of the target sensor at the current moment and the measured value of the target sensor at the previous moment as the final altitude change information.

[0011] In a second aspect, an embodiment of the present invention further provides a data prediction device for a radio altimeter. The device includes: a radio altimeter measurement module, configured to obtain measurement data of the radio altimeter of the aircraft and determine first altitude information of the aircraft based on the measurement data; a multi-sensor measurement module, configured to obtain wind field data, temperature data, and air pressure data of the aircraft and determine second altitude information, third altitude information, and fourth altitude information based on the wind field data, temperature data, and air pressure data respectively; and a final altitude information determination module, configured to determine the final altitude information of the aircraft based on the first altitude information, second altitude information, third altitude information, and fourth altitude information.

[0012] In a third aspect, an embodiment of the present invention further provides an electronic device, including a processor and a memory. The memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement the above-mentioned data prediction method for a radio altimeter.

[0013] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium. The computer-readable storage medium stores computer-executable instructions, and when the computer-executable instructions are called and executed by a processor, the computer-executable instructions cause the processor to implement the above-mentioned data prediction method for a radio altimeter.

[0014] The embodiments of the present invention bring the following beneficial effects: The embodiments of the present invention provide a data prediction method, device, equipment, and storage medium for a radio altimeter. Measurement data of the radio altimeter of the aircraft is obtained, and first altitude information of the aircraft is determined based on the measurement data; wind field data, temperature data, and air pressure data of the aircraft are obtained, and second altitude information, third altitude information, and fourth altitude information are determined based on the wind field data, temperature data, and air pressure data respectively; and the final altitude information of the aircraft is determined based on the first altitude information, second altitude information, third altitude information, and fourth altitude information. In this way, on the basis of the height measurement function of the radio altimeter, an information fusion scheme can be proposed by combining wind field data, temperature data, and air pressure data to correct the measurement data of a single altimeter sensor, realize height measurement under the condition of altimeter data loss, and improve the continuity and effectiveness of the data.

[0015] Other features and advantages of the present disclosure will be described in the following description, or some features and advantages can be inferred from the description without doubt, or can be learned by implementing the above technologies of the present disclosure.

[0016] To make the above objects, features, and advantages of the present disclosure more obvious and understandable, the following specific preferred embodiments are given, and detailed descriptions are made in conjunction with the accompanying drawings as follows. Description of the Drawings

[0017] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0018] Figure 1 It is a flowchart of a data prediction method for a radio altimeter provided by an embodiment of the present invention; Figure 2 It is a flowchart of another data prediction method for a radio altimeter provided by an embodiment of the present invention; Figure 3 It is a schematic diagram of a data prediction method for a radio altimeter provided by an embodiment of the present invention; Figure 4 It is a schematic diagram of another data prediction method for a radio altimeter provided by an embodiment of the present invention; Figure 5 It is a schematic structural diagram of a data prediction device for a radio altimeter provided by an embodiment of the present invention; Figure 6 It is a schematic structural diagram of an electronic device provided by an embodiment of the present invention. Specific Embodiments

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions of the present invention with reference to the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0020] Currently, a radio altimeter obtains the true height of an aircraft relative to the ground by receiving the frequency change of a signal. However, under the influence of environmental interference, the signal-to-noise ratio of the received echo signal may be relatively low, resulting in invalid output of altimeter data, such as data loss or invalid data.

[0021] Based on this, a data prediction method, device, equipment, and storage medium for a radio altimeter provided by an embodiment of the present invention. Considering that the measurement signal of the altimeter consists of two parts: the altitude measurement signal from the movement of the aircraft and the altitude measurement signal from the terrain undulation, the embodiment of the present invention specifically provides a data prediction method for a radio altimeter based on multi-source auxiliary information. On the basis of the altitude measurement function of the radio altimeter, an information fusion scheme is proposed by combining wind field data, temperature data, and pressure data to correct the measurement data of a single altimeter sensor, realizing altitude measurement under the condition of altimeter data loss, and improving the continuity and effectiveness of the data.

[0022] For ease of understanding of this embodiment, first, a data prediction method for a radio altimeter disclosed in an embodiment of the present invention will be introduced in detail.

[0023] Embodiment 1: An embodiment of the present invention provides a data prediction method for a radio altimeter. Refer to Figure 1 the flowchart of a data prediction method for a radio altimeter shown. The data prediction method for the radio altimeter includes the following steps: Step S102, obtain the measurement data of the radio altimeter of the aircraft, and determine the first altitude information of the aircraft based on the measurement data.

[0024] In this embodiment, the radio altimeter can determine the absolute altitude of the aircraft relative to the ground by measuring the delay between the transmitted electromagnetic wave and the received electromagnetic wave. The radio wave propagates at a constant speed in a uniform medium in a straight line. The relationship between the flight altitude H (i.e., the first altitude information), the radio wave propagation speed c, and the radio wave propagation time t is as follows: (1) The delay time t of the radio altimeter transmitted signal relative to the received signal H is: (2) Therefore, in this embodiment, the first altitude information of the aircraft can be determined based on the measurement data of the radio altimeter through formulas (1) and (2).

[0025] Step S104, obtain the wind field data, temperature data, and pressure data of the aircraft, and determine the second altitude information, the third altitude information, and the fourth altitude information based on the wind field data, temperature data, and pressure data respectively.

[0026] In this embodiment, the wind field data, temperature data, and pressure data of the aircraft can also be obtained, and the corresponding altitude information (i.e., the second altitude information, the third altitude information, and the fourth altitude information) can be determined based on the wind field data, temperature data, and pressure data respectively.

[0027] The barometric sensing element on the aircraft can sense the atmospheric pressure, while the temperature sensor can sense the ambient temperature. Generally, the atmospheric pressure decreases with the increase of the aircraft's altitude and is related to factors such as temperature, location, season, and weather. Therefore, the altitude of the aircraft can be determined according to the specific functional relationship. Assuming that the air is an ideal gas, the relationship between the atmospheric pressure and the standard pressure altitude is: (3) where: P b is the lower limit of the air pressure in the relevant altitude layer, T b is the lower limit of the atmospheric temperature in the relevant altitude layer, H b is the standard pressure altitude of the relevant altitude layer, β is the vertical change rate of the atmospheric temperature, g = 9.8 m / s2 is the gravitational acceleration, and R = 287.05 m2 / K·s2 is the air gas constant.

[0028] According to Equation (3), the altitude measurement information of the aircraft based on the air pressure and temperature is: (4) Therefore, in this embodiment, the third altitude information and the fourth altitude information can be determined based on the temperature data and the air pressure data through Equations (3) and (4) respectively. Among them, the air pressure data can be set as a fixed value when calculating the third altitude information, and the temperature data can be set as a fixed value when calculating the fourth altitude information.

[0029] The change of the wind speed with altitude is relatively significant, and the change law can be represented by the wind shear index α: (5) where H1 is the altitude at position 1, H2 is the altitude at position 2, V1 is the wind speed at altitude H1, and V2 is the wind speed at altitude H2. The wind shear index α can be determined according to the wind field data.

[0030] Therefore, in this embodiment, the second altitude information can be determined based on the wind field data through Equation (5).

[0031] Step S106, determine the final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information.

[0032] Since the measurement signal of the radio altimeter is affected by the movement of the aircraft and the terrain undulation, while the wind field data, the temperature data, and the air pressure data are not affected by the terrain change but are easily affected by the atmospheric environment. Therefore, a data fusion algorithm can be used to fuse multiple measurement data (i.e., the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information) to obtain the best altitude measurement result and improve the continuity and effectiveness of the measurement data.

[0033] An embodiment of the present invention provides a data prediction method for a radio altimeter. The method includes obtaining measurement data of the radio altimeter of an aircraft, and determining first altitude information of the aircraft based on the measurement data; obtaining wind field data, temperature data, and air pressure data of the aircraft, and respectively determining second altitude information, third altitude information, and fourth altitude information based on the wind field data, temperature data, and air pressure data; and determining final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information. In this way, on the basis of the altitude measurement function of the radio altimeter, an information fusion scheme can be proposed by combining the wind field data, temperature data, and air pressure data to correct the measurement data of a single altimeter sensor, realize altitude measurement under the condition of altimeter data loss, and improve the continuity and effectiveness of the data.

[0034] Embodiment 2: This embodiment provides another data prediction method for a radio altimeter. This method is implemented on the basis of the above embodiment, and focuses on describing the specific manner of fusing various measurement data through a data fusion algorithm. Refer to Figure 2 the flowchart of another data prediction method for a radio altimeter shown in. The data prediction method for the radio altimeter includes the following steps: Step S202: Obtain measurement data of the radio altimeter of the aircraft, and determine first altitude information of the aircraft based on the measurement data.

[0035] Step S204: Obtain wind field data, temperature data, and air pressure data of the aircraft, and respectively determine second altitude information, third altitude information, and fourth altitude information based on the wind field data, temperature data, and air pressure data.

[0036] Step S206: Determine whether the measurement data of the radio altimeter at the current moment is invalid.

[0037] In this embodiment, it can be first determined whether the measurement data of the radio altimeter at the current moment is invalid.

[0038] In some embodiments, if the measurement data of the radio altimeter at the current moment is lost, it is determined that the measurement data of the radio altimeter at the current moment is invalid; if the measurement data of the radio altimeter at the current moment is not lost, it is determined that the measurement data of the radio altimeter at the current moment is valid.

[0039] According to different selected reference planes, the measurement values of the radio altimeter at the same vertical position are also different. The radio altimeter obtains the absolute altitude of the aircraft at the vertical position. In a specific environment, the signal-to-noise ratio of the echo signal received by the altimeter may be relatively poor, resulting in low receiving sensitivity and further causing the phenomenon of measurement data loss.

[0040] Step S208, if the measurement data of the radio altimeter at the current moment is invalid, determine the final altitude information of the aircraft at the current moment based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information at the previous moment, as well as the second altitude information, the third altitude information, and the fourth altitude information at the current moment.

[0041] Suppose that at the previous moment t0 when the altimeter information is lost, the altitude of the aircraft is H ALT-0 (i.e., the first altitude information at the previous moment); see Figure 3 the schematic diagram of a data prediction method of a radio altimeter shown in, at the current moment t1, the information H ALT-1 (i.e., the first altitude information at the current moment) output by the altimeter is H ALT-0 on the basis of superimposing the altitude change ΔH: (6) The embodiment of the present invention provides a multi-source altitude measurement data filling scheme. The improved multi-source altitude measurement data filling scheme proposed in this embodiment combines wind field data, temperature data, and air pressure data on the basis of the altitude measurement function of the radio altimeter to jointly obtain altitude measurement data, realizes altitude measurement under the condition of altimeter data loss, and improves the continuity and effectiveness of the data.

[0042] As Figure 3 shown, suppose that at the moment t0, the altitude information obtained from the wind field data, temperature data, and air pressure data is respectively H Wind-0 (i.e., the second altitude information at the previous moment), H Temp-0 (i.e., the third altitude information at the previous moment), and H Press-0 (i.e., the fourth altitude information at the previous moment); at the moment t1, the flight altitude information obtained from the wind field data, temperature data, and air pressure data is respectively H Wind-1 (i.e., the second altitude information at the current moment), H Temp-1 (i.e., the third altitude information at the current moment), and H Press-1 (i.e., the fourth altitude information at the current moment).

[0043] In some embodiments, the difference between the second altitude information at the current moment and the second altitude information at the previous moment can be used as the second altitude change information; the difference between the third altitude information at the current moment and the third altitude information at the previous moment can be used as the third altitude change information; the difference between the fourth altitude information at the current moment and the fourth altitude information at the previous moment can be used as the fourth altitude change information; determine the final altitude change information based on the second altitude change information, the third altitude change information, and the fourth altitude change information; and use the sum of the final altitude change information and the first altitude information at the previous moment as the final altitude information of the aircraft at the current moment.

[0044] AsFigure 3 As shown, let the height changes corresponding to the wind field data, temperature data, and barometric pressure data be denoted as ΔH Wind (i.e., the second height change information), ΔH Temp (i.e., the third height change information), and ΔH Press (i.e., the fourth height change information), respectively. Then, we have: (7) In some embodiments, if the measurement data of the radio altimeter at the current moment is valid, the height information at the current moment is used as the final height information of the aircraft at the current moment.

[0045] Reference can be made to Figure 4 the schematic diagram of another data prediction method of the radio altimeter shown, and the following flag bits are defined: a) Flag bit is 0: Use the altimeter data and external data, where the external data includes wind field data, temperature data, and barometric pressure data; b) Flag bit is 1: Judge the validity of the altimeter data. When it is judged as "valid", directly output the measurement data of the altimeter itself. When it is judged as "invalid", use the altimeter data and external data.

[0046] Furthermore, a data filling scheme under the condition of altimeter information loss is established as Figure 4 shown. When using external data, that is, applying formula (5) to obtain the altimeter output information, the actual height change ΔH should be obtained by fusing ΔH Wind , ΔH Temp and ΔH Press .

[0047] In some embodiments, the above aircraft is provided with N sensors, and the N sensors are used to detect the wind field data, temperature data, and barometric pressure data of the aircraft. The measured values of the N sensors are the second height change information, the third height change information, or the fourth height change information respectively, and N is greater than or equal to 3.

[0048] Considering that the N sensors respectively correspond to 1 local filter, for the wind field data, temperature data, and barometric pressure data, N = 3.

[0049] Let the observed value of the i-th local filter, i.e., the height of the aircraft, be Z i , then the measured values of the N sensors form Z1, Z2 ……, Z N .

[0050] In some embodiments, the minimum value among the measurement values of N sensors can be used as the optimal height value; based on the measurement values of the N sensors, a preset resolution coefficient, and the optimal height value, the correlation coefficients of the N sensors are determined; based on the correlation coefficients of the N sensors and the preset weight values of the N sensors, the correlation degree between the measurement values of the N sensors and the optimal height value is determined; the sensor with the highest correlation degree is used as the target sensor; and the difference between the measurement value of the target sensor at the current moment and the measurement value of the target sensor at the previous moment is used as the final height change information.

[0051] In this embodiment, according to the grey relational analysis method, the correlation coefficient e of the i-th sensor can be obtained i : (8) where 0 < ρ < 1, ρ is the resolution coefficient, representing the identification ability of the system. The smaller the ρ value, the greater the identification ability. Preferably, ρ = 0.5 can be taken; Z0 = min(Z1, Z2……, Z N ).

[0052] According to e i the correlation coefficient vector E is obtained: (9) Calculate the correlation degree R between the measurement value of the i-th sensor and the optimal height value Z0 i : (10) where w i is the weight value.

[0053] The larger the correlation degree R i , it indicates that the measurement value Z i of the sensor i is closer to the optimal height value Z0.

[0054] Finally, the sensor with the largest correlation degree is selected as the target sensor to determine the final height change information ΔH, and substituting it into formula (6) to obtain the measured height value as the final height information.

[0055] The embodiment of the present invention provides a multi-sensor fusion algorithm based on grey relational analysis. The measurement accuracies and usage conditions of wind field data, temperature data, and air pressure data are all different. The multi-sensor fusion algorithm based on grey relational analysis proposed in this embodiment can obtain the superposition height change value most suitable for the current flight conditions, and then correct the measurement data of a single altimeter sensor.

[0056] In summary, the above method provided by the embodiments of the present invention specifically provides a radio altimeter data prediction method based on multi-source auxiliary information. On the basis of the altitude measurement function of the radio altimeter, an information fusion scheme is proposed by combining wind field data, temperature data, and air pressure data to correct the measurement data of a single altimeter sensor, realizing altitude measurement under the condition of altimeter data loss, and improving the continuity and effectiveness of the data.

[0057] Embodiment 3: Corresponding to the above method embodiment, the embodiment of the present invention provides a data prediction device for a radio altimeter. Refer to Figure 5 the structural schematic diagram of a data prediction device for a radio altimeter shown in a radio altimeter measurement module 51, configured to obtain the measurement data of the radio altimeter of the aircraft, and determine the first altitude information of the aircraft based on the measurement data; a multi-sensor measurement module 52, configured to obtain the wind field data, temperature data, and air pressure data of the aircraft, and determine the second altitude information, the third altitude information, and the fourth altitude information based on the wind field data, temperature data, and air pressure data respectively; a final altitude information determination module 53, configured to determine the final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information.

[0058] The embodiment of the present invention provides a data prediction device for a radio altimeter, which obtains the measurement data of the radio altimeter of the aircraft, and determines the first altitude information of the aircraft based on the measurement data; obtains the wind field data, temperature data, and air pressure data of the aircraft, and determines the second altitude information, the third altitude information, and the fourth altitude information based on the wind field data, temperature data, and air pressure data respectively; determines the final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information. In this way, on the basis of the altitude measurement function of the radio altimeter, an information fusion scheme can be proposed by combining wind field data, temperature data, and air pressure data to correct the measurement data of a single altimeter sensor, realizing altitude measurement under the condition of altimeter data loss, and improving the continuity and effectiveness of the data.

[0059] The above final altitude information determination module is configured to determine whether the measurement data of the radio altimeter at the current moment is invalid; if the measurement data of the radio altimeter at the current moment is invalid, determine the final altitude information of the aircraft at the current moment based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information at the previous moment, and the second altitude information, the third altitude information, and the fourth altitude information at the current moment.

[0060] The above-mentioned final altitude information determination module is further configured to use the altitude information at the current moment as the final altitude information of the aircraft at the current moment if the measurement data of the radio altimeter at the current moment is valid.

[0061] The above-mentioned final altitude information determination module is configured to determine that the measurement data of the radio altimeter at the current moment is invalid if the measurement data of the radio altimeter at the current moment is lost; and determine that the measurement data of the radio altimeter at the current moment is valid if the measurement data of the radio altimeter at the current moment is not lost.

[0062] The above-mentioned final altitude information determination module is configured to use the difference between the second altitude information at the current moment and the second altitude information at the previous moment as the second altitude change information; use the difference between the third altitude information at the current moment and the third altitude information at the previous moment as the third altitude change information; use the difference between the fourth altitude information at the current moment and the fourth altitude information at the previous moment as the fourth altitude change information; determine the final altitude change information based on the second altitude change information, the third altitude change information, and the fourth altitude change information; and use the sum of the final altitude change information and the first altitude information at the previous moment as the final altitude information of the aircraft at the current moment.

[0063] The above-mentioned aircraft is provided with N sensors, and the N sensors are used to detect the wind field data, temperature data, and air pressure data of the aircraft. The measured values of the N sensors are respectively the second altitude change information, the third altitude change information, or the fourth altitude change information, and N is greater than or equal to 3.

[0064] The above-mentioned final altitude information determination module is configured to use the minimum value among the measured values of the N sensors as the optimal altitude value; determine the correlation coefficients of the N sensors based on the measured values of the N sensors, a preset resolution coefficient, and the optimal altitude value; determine the correlation degree between the measured values of the N sensors and the optimal altitude value based on the correlation coefficients of the N sensors and the preset weight values of the N sensors; use the sensor with the highest correlation degree as the target sensor; and use the difference between the measured value of the target sensor at the current moment and the measured value of the target sensor at the previous moment as the final altitude change information.

[0065] Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working process of the above-described data prediction device of the radio altimeter can refer to the corresponding process in the embodiments of the foregoing data prediction method of the radio altimeter, which will not be elaborated herein.

[0066] Embodiment 4: The embodiment of the present invention further provides an electronic device for running the above-mentioned data prediction method of the radio altimeter; see Figure 6Schematic structural diagram of an electronic device shown. The electronic device includes a memory 100 and a processor 101. Among them, the memory 100 is used to store one or more computer instructions, and the one or more computer instructions are executed by the processor 101 to implement the data prediction method of the above radio altimeter.

[0067] Furthermore, Figure 6 The electronic device shown also includes a bus 102 and a communication interface 103. The processor 101, the communication interface 103, and the memory 100 are connected through the bus 102.

[0068] Among them, the memory 100 may include a high-speed random access memory (RAM, Random Access Memory), and may also include a non-volatile memory, such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 103 (which can be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. can be used. The bus 102 can be an ISA bus, a PCI bus, an EISA bus, etc. The bus can be divided into an address bus, a data bus, a control bus, etc. For the convenience of representation, Figure 6 only a bidirectional arrow is used in the figure, but it does not mean that there is only one bus or one type of bus.

[0069] The processor 101 may be an integrated circuit chip with the ability to process signals. In the implementation process, each step of the above method can be completed by the integrated logic circuit of the hardware in the processor 101 or the instructions in the form of software. The above-mentioned processor 101 may be a general-purpose processor, including a central processing unit (CPU for short), a network processor (NP for short), etc.; it may also be a digital signal processor (DSP for short), an application specific integrated circuit (ASIC for short), a field-programmable gate array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute each method, step, and logic block diagram disclosed in the embodiments of the present invention. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present invention can be directly embodied as being executed and completed by the hardware decoding processor, or executed and completed by the combination of the hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory 100, and the processor 101 reads the information in the memory 100 and combines its hardware to complete the steps of the method in the foregoing embodiments.

[0070] The embodiments of the present invention also provide a computer-readable storage medium. The computer-readable storage medium stores computer-executable instructions. When the computer-executable instructions are called and executed by the processor, the computer-executable instructions cause the processor to implement the above-mentioned data prediction method of the radio altimeter. For the specific implementation, reference can be made to the method embodiments, and details are not described herein again.

[0071] The computer program product of the data prediction method, device, equipment, and storage medium of the radio altimeter provided by the embodiments of the present invention includes a computer-readable storage medium storing program code. The instructions included in the program code can be used to execute the method in the foregoing method embodiments. For the specific implementation, reference can be made to the method embodiments, and details are not described herein again.

[0072] Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the above-described system and / or device can refer to the corresponding processes in the foregoing method embodiments, and details are not described herein again.

[0073] In addition, in the description of the embodiments of the present invention, unless otherwise clearly defined and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be a direct connection or an indirect connection through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0074] If a function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods in the various embodiments of the present invention. The aforementioned storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs that can store program codes.

[0075] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0076] Finally, it should be noted that the above-described embodiments are only specific embodiments of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting them. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: any person skilled in the art within the technical scope disclosed by the present invention can still modify the technical solutions recorded in the foregoing embodiments, or can easily think of changes, or make equivalent replacements for some of the technical features; and these modifications, changes, or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A data prediction method for a radio altimeter, characterized in that, The method includes: Obtaining measurement data of a radio altimeter of an aircraft, and determining first altitude information of the aircraft based on the measurement data; Obtaining wind field data, temperature data, and air pressure data of the aircraft, and determining second altitude information, third altitude information, and fourth altitude information based on the wind field data, the temperature data, and the air pressure data respectively; Determining final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information.

2. The method according to claim 1, wherein The step of determining final altitude information of the aircraft based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information includes: Determining whether the measurement data of the radio altimeter at the current moment is invalid; If the measurement data of the radio altimeter at the current moment is invalid, determining the final altitude information of the aircraft at the current moment based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information at the previous moment, and the second altitude information, the third altitude information, and the fourth altitude information at the current moment.

3. The method according to claim 2, wherein After the step of determining whether the measurement data of the radio altimeter at the current moment is invalid, the method further includes: If the measurement data of the radio altimeter at the current moment is valid, using the altitude information at the current moment as the final altitude information of the aircraft at the current moment.

4. The method according to claim 2, characterized in that, The step of determining whether the measurement data of the radio altimeter at the current moment is invalid includes: If the measurement data of the radio altimeter at the current moment is lost, determining that the measurement data of the radio altimeter at the current moment is invalid; If the measurement data of the radio altimeter at the current moment is not lost, determining that the measurement data of the radio altimeter at the current moment is valid.

5. The method according to claim 2, wherein The step of determining the final altitude information of the aircraft at the current moment based on the first altitude information, the second altitude information, the third altitude information, and the fourth altitude information at the previous moment, and the second altitude information, the third altitude information, and the fourth altitude information at the current moment includes: Using the difference between the second altitude information at the current moment and the second altitude information at the previous moment as second altitude change information; Using the difference between the third altitude information at the current moment and the third altitude information at the previous moment as third altitude change information; Using the difference between the fourth altitude information at the current moment and the fourth altitude information at the previous moment as fourth altitude change information; Determining final altitude change information based on the second altitude change information, the third altitude change information, and the fourth altitude change information; Using the sum of the final altitude change information and the first altitude information at the previous moment as the final altitude information of the aircraft at the current moment.

6. The method according to claim 5, wherein The aircraft is provided with N sensors, and the N sensors are used to detect the wind field data, temperature data and air pressure data of the aircraft. The measured values of the N sensors are respectively the second height change information, the third height change information or the fourth height change information, and N is greater than or equal to 3.

7. The method according to claim 6, wherein The step of determining the final height change information based on the second height change information, the third height change information and the fourth height change information includes: Taking the minimum value among the measured values of the N sensors as the optimal height value; Determining the correlation coefficients of the N sensors based on the measured values of the N sensors, a preset resolution coefficient and the optimal height value; Determining the correlation degree between the measured values of the N sensors and the optimal height value based on the correlation coefficients of the N sensors and the preset weight values of the N sensors; Taking the sensor with the highest correlation degree as the target sensor; Taking the difference between the measured value of the target sensor at the current moment and the measured value of the target sensor at the previous moment as the final height change information.

8. A data prediction device for a radio altimeter, characterized in that, The device includes: A radio altimeter measurement module, configured to obtain the measurement data of the radio altimeter of the aircraft and determine the first height information of the aircraft based on the measurement data; A multi-sensor measurement module, configured to obtain the wind field data, temperature data and air pressure data of the aircraft, and determine the second height information, the third height information and the fourth height information based on the wind field data, the temperature data and the air pressure data respectively; A final height information determination module, configured to determine the final height information of the aircraft based on the first height information, the second height information, the third height information and the fourth height information.

9. An electronic device, characterized in that, It includes a processor and a memory. The memory stores computer-executable instructions that can be executed by the processor. The processor executes the computer-executable instructions to implement the data prediction method of the radio altimeter according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions. When the computer-executable instructions are called and executed by the processor, the computer-executable instructions cause the processor to implement the data prediction method of the radio altimeter according to any one of claims 1 to 7.

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