Method and device for reconstructing total temperature and static temperature of airplane

Abstract

The invention belongs to the technical field of flight control, and particularly relates to an aircraft total static temperature reconstruction method and device, and the method comprises the steps: S1, obtaining static pressure information collected by an aircraft total static pressure system; s2, determining the current air pressure height of the aircraft according to the static pressure information; s3, the static temperature Ts is determined according to the air pressure height Hp, and when Hp is smaller than or equal to 11000 m, Ts is equal to 216.65-6.5 (Hp / 1000-11); when Hp is greater than 11000 m and less than or equal to 20000 m, Ts is equal to 216.65 K; and S4, determining the total temperature Tt according to the static temperature Ts. The total temperature and the static temperature of the airplane can be quickly obtained, and the flight safety is ensured.

Description

Technical Field

[0001] The present application belongs to the field of flight control technology, and in particular relates to a method and device for reconstructing aircraft total and static temperatures. Background Art

[0002] Total temperature is the temperature when the compressed air is blocked to zero speed relative to the aircraft's speed. Static temperature is the temperature of the atmosphere at the aircraft's flight altitude without being disturbed by the aircraft, representing the static atmospheric temperature outside the aircraft. Since adiabatic compression produces additional temperature, the total temperature is higher than the static temperature. Usually, total temperature information is used for aircraft icing protection control, and static temperature information is used for cabin temperature control and true airspeed calculation.

[0003] In modern aircraft, the temperature information of the incoming air is generally collected by the total temperature sensor and transmitted to the air data computer, which then calculates the static temperature in combination with the Mach number. In addition, the static temperature combined with the Mach number can be used to calculate the true airspeed for use in the aircraft navigation system and flight control system.

[0004] When the air inlet of the total temperature sensor is frozen or blocked, the total temperature information will be invalid, which will in turn cause the static temperature to fail, and will further affect the true airspeed output by the atmospheric data system to deviate from the actual value. When the total temperature and static temperature information on the aircraft is lost, it will affect the flight mission. Summary of the invention

[0005] In order to solve the above problems, the present application provides a method and device for reconstructing the total temperature and static temperature of an aircraft, which solves the problem that the total temperature and static temperature information cannot be obtained when the total temperature sensor fails.

[0006] The first aspect of the present application provides a method for reconstructing the total static temperature of an aircraft, mainly comprising:

[0007] Step S1, obtaining static pressure information collected by the aircraft total static pressure system;

[0008] Step S2, determining the current pressure altitude of the aircraft according to the static pressure information;

[0009] Step S3, determining the static temperature Ts according to the air pressure height Hp:

[0010] When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11);

[0011] When 11000m<Hp≤20000m, Ts=216.65K;

[0012] Step S4, determining the total temperature Tt according to the static temperature Ts.

[0013] Preferably, after step S1, the method further includes correcting the collected static pressure information according to the static pressure source position error.

[0014] Preferably, step S4 further comprises:

[0015] Step S41, calculating the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system;

[0016] Step S42: determine the total temperature Tt by the following formula:

[0017] Tt=Ts*(1+0.2M 2 ).

[0018] The second aspect of the present application provides an aircraft total temperature static temperature reconstruction device, which mainly includes:

[0019] Static pressure collection module, used to obtain static pressure information collected by the aircraft total static pressure system;

[0020] A pressure altitude calculation module, used to determine the current pressure altitude of the aircraft according to the static pressure information;

[0021] The static temperature calculation module is used to determine the static temperature Ts according to the air pressure height Hp:

[0022] When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11);

[0023] When 11000m<Hp≤20000m, Ts=216.65K;

[0024] The total temperature calculation module is used to determine the total temperature Tt according to the static temperature Ts.

[0025] Preferably, the static pressure acquisition module includes a correction unit for correcting the collected static pressure information according to a static pressure source position error.

[0026] Preferably, the total temperature calculation module includes:

[0027] A flight Mach number calculation unit is used to calculate the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system;

[0028] The total temperature calculation unit is used to determine the total temperature Tt by the following formula:

[0029] Tt=Ts*(1+0.2M 2 ).

[0030] A third aspect of the present application provides a computer device, including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the aircraft total temperature static temperature reconstruction method as described above.

[0031] A fourth aspect of the present application provides a readable storage medium, wherein the readable storage medium stores a computer program, wherein the computer program is used to implement the aircraft total temperature static temperature reconstruction method as described above when executed by a processor.

[0032] This application can quickly obtain the total temperature and static temperature of the aircraft, ensuring flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a flow chart of a preferred embodiment of the aircraft total temperature and static temperature reconstruction method of the present application.

[0034] Figure 2 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0036] The first aspect of the present application provides a method for reconstructing the total static temperature of an aircraft, such as Figure 1 As shown, it mainly includes:

[0037] Step S1, obtaining static pressure information collected by the aircraft total static pressure system;

[0038] Step S2, determining the current pressure altitude of the aircraft according to the static pressure information;

[0039] Step S3, determining the static temperature Ts according to the air pressure height Hp:

[0040] When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11);

[0041] When 11000m<Hp≤20000m, Ts=216.65K;

[0042] Step S4, determining the total temperature Tt according to the static temperature Ts.

[0043] This application is mainly used for the reconstruction of the total temperature and static temperature when the total temperature sensor fails. This is because when the total temperature sensor is normal, the atmospheric data computer receives the total pressure Pt and static pressure Ps provided by the total static pressure system, and receives the total temperature information Tt transmitted by the total temperature sensor. The Mach number M can be obtained based on the total pressure Pt and static pressure Ps; the static temperature Ts can be obtained based on the Mach number M and the total temperature Tt; the true vacuum speed Vt can be obtained based on the static temperature Ts and the Mach number M. When the total temperature sensor fails, the atmospheric data computer cannot receive the normal total temperature Tt information, and therefore cannot output accurate static temperature Ts information, and further cannot output accurate true vacuum speed Vt information.

[0044] After analysis, it is found that static temperature usually has a certain relationship with pressure altitude, and pressure altitude can be calculated through static pressure. For this reason, the present application can obtain the aircraft total pressure and static pressure signals based on the total static pressure system through step S1, and then can obtain the current pressure altitude by looking up the table in step S2. Then, in step S3, the present application creates a conversion relationship between pressure altitude and static temperature, calculates the corresponding static temperature based on the function of step S3, and finally in step S4, based on the original functional relationship from total temperature to static temperature, the conversion relationship from static temperature to total temperature is reversed to solve the total temperature.

[0045] In some optional implementations, step S1 further includes correcting the collected static pressure information according to the static pressure source position error.

[0046] In some optional implementations, step S4 further includes:

[0047] Step S41, calculating the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system;

[0048] Step S42: determine the total temperature Tt by the following formula:

[0049] Tt=Ts*(1+0.2M 2 ).

[0050] The second aspect of the present application provides an aircraft total temperature static temperature reconstruction device corresponding to the above method, mainly comprising:

[0051] Static pressure collection module, used to obtain static pressure information collected by the aircraft total static pressure system;

[0052] A pressure altitude calculation module, used to determine the current pressure altitude of the aircraft according to the static pressure information;

[0053] The static temperature calculation module is used to determine the static temperature Ts according to the air pressure height Hp:

[0054] When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11);

[0055] When 11000m<Hp≤20000m, Ts=216.65K;

[0056] The total temperature calculation module is used to determine the total temperature Tt according to the static temperature Ts.

[0057] In some optional implementations, the static pressure acquisition module includes a correction unit for correcting the collected static pressure information according to a static pressure source position error.

[0058] In some optional implementations, the total temperature calculation module includes:

[0059] A flight Mach number calculation unit is used to calculate the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system;

[0060] The total temperature calculation unit is used to determine the total temperature Tt by the following formula:

[0061] Tt=Ts*(1+0.2M 2 ).

[0062] In a third aspect of the present application, a computer device includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement a method for reconstructing the total static temperature of an aircraft.

[0063] In a fourth aspect of the present application, a readable storage medium stores a computer program, and when the computer program is executed by a processor, it is used to implement the aircraft total temperature static temperature reconstruction method described above. The computer readable storage medium may be included in the device described in the above embodiment; or it may exist independently without being assembled into the device. The above computer readable storage medium carries one or more programs, and when the above one or more programs are executed by the device, the data is processed according to the above method.

[0064] Reference below Figure 2 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 2 The computer device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0065] like Figure 2As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage part 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the device 400 are also stored. The CPU 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0066] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0067] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, - but not limited to - a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection with one or more conductors, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, an apparatus or a device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, an apparatus or a device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0068] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0069] The modules or units involved in the embodiments described in this application may be implemented by software or hardware. The modules or units described may also be set in a processor, and the names of these modules or units do not constitute limitations on the modules or units themselves in some cases.

[0070] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for reconstructing aircraft total temperature and static temperature, characterized in that: include: Step S1, obtaining static pressure information collected by the aircraft total static pressure system; Step S2, determining the current pressure altitude of the aircraft according to the static pressure information; Step S3, determining the static temperature Ts according to the air pressure height Hp: When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11); When 11000m<Hp≤20000m, Ts=216.65K; Step S4, determining the total temperature Tt according to the static temperature Ts.

2. The aircraft total temperature static temperature reconstruction method according to claim 1, characterized in that: After step S1, the collected static pressure information is further corrected according to the static pressure source position error.

3. The aircraft total temperature static temperature reconstruction method according to claim 1, characterized in that: Step S4 further comprises: Step S41, calculating the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system; Step S42: determine the total temperature Tt by the following formula: <h2 style=";text-align:left;direction:ltr">Tt = Ts*(1+0.2M<h2 style=";text-align:left;direction:ltr"> 2 <h2 style=";text-align:left;direction:ltr"> )。 4. An aircraft total temperature static temperature reconstruction device, characterized in that: include: Static pressure collection module, used to obtain static pressure information collected by the aircraft total static pressure system; A pressure altitude calculation module, used to determine the current pressure altitude of the aircraft according to the static pressure information; The static temperature calculation module is used to determine the static temperature Ts according to the air pressure height Hp: When Hp≤11000m, Ts=216.65-6.5(Hp / 1000-11); When 11000m<Hp≤20000m, Ts=216.65K; The total temperature calculation module is used to determine the total temperature Tt according to the static temperature Ts.

5. The aircraft total temperature static temperature reconstruction device according to claim 4, characterized in that: The static pressure acquisition module includes a correction unit for correcting the collected static pressure information according to the static pressure source position error.

6. The aircraft total temperature static temperature reconstruction device according to claim 4, characterized in that: The total temperature calculation module includes: A flight Mach number calculation unit is used to calculate the current flight Mach number M through the total pressure information and static pressure information collected by the aircraft total static pressure system; The total temperature calculation unit is used to determine the total temperature Tt by the following formula: <h2 style=";text-align:left;direction:ltr">Tt = Ts*(1+0.2M<h2 style=";text-align:left;direction:ltr"> 2 <h2 style=";text-align:left;direction:ltr"> )。 7. A computer device, characterized in that: The invention comprises a processor, a memory and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the aircraft total temperature static temperature reconstruction method according to any one of claims 1 to 3.

8. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the aircraft total temperature and static temperature reconstruction method as described in any one of claims 1 to 3.

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