Aircraft anti-tail-spin parachute parameter determination method, computer device and storage medium

Abstract

The invention provides an aircraft anti-tail rotation parachute parameter determination method, a computer device and a storage medium, and the method comprises the steps: obtaining a tail rotation mode of a target aircraft, and obtaining a corresponding mode coefficient according to the tail rotation mode; acquiring the distance from the tail of the target aircraft to the gravity center of the target aircraft, the tip chord length of aircraft wings, the average pneumatic chord length of the aircraft wings, the area of the aircraft wings and the extension length of the aircraft wings; obtaining an airfoil correction coefficient according to the aircraft wing tip chord length and the aircraft wing average aerodynamic chord length; according to the modal coefficient, the airfoil profile correction coefficient, the distance from the tail to the center of gravity of the aircraft, the area of the aircraft wing and the extension length of the aircraft wing, obtaining the effective circle diameter of the aircraft anti-tail spinning umbrella; and determining a target type of the anti-tail-spin parachute of the airplane, and calculating the effective circle diameter by using a calculation formula corresponding to the target type to obtain canopy size parameters of the anti-tail-spin parachute of the airplane. By applying the method, the reverse tail spinning umbrella parameter selection period can be shortened, and the research and development test cost can be reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft anti-spin parachutes, and in particular, to a method for determining parameters of an aircraft anti-spin parachute, a computer device applying the method for determining parameters of an aircraft anti-spin parachute, and a computer-readable storage medium applying the method for determining parameters of an aircraft anti-spin parachute. Background Art

[0002] When general aircraft conduct spin test flights, in order to ensure the safety of aircraft property and personnel lives, an anti-spin parachute system must be installed before the test.

[0003] When an aircraft enters a spin and conventional operations cannot recover it, the anti-spin parachute uses the aerodynamic drag obtained when it is opened and the parachute rope connected to the tail to generate additional yaw and pitch braking moments to pull the aircraft out of the spin.

[0004] When the material and structure of the anti-spin parachute are determined, the method to determine the canopy size and parachute rope length of the anti-spin parachute suitable for a certain aircraft model is to conduct a tailspin wind tunnel test on the aircraft scale model. In addition to causing a sharp increase in development costs, the shortage of wind tunnel resources will also greatly extend the development cycle. Both of these are unacceptable for general aircraft that are very sensitive to development costs and development cycles.

[0005] Therefore, it is necessary to consider a more optimized design method for anti-spin parachutes for general aircraft. Summary of the invention

[0006] The first object of the present invention is to provide a method for determining the parameters of an aircraft anti-spin parachute, which can shorten the anti-spin parachute parameter selection cycle and reduce the research and development test costs.

[0007] The second object of the present invention is to provide a computer device that can shorten the anti-spin parachute parameter selection cycle and reduce the R&D test costs.

[0008] The third object of the present invention is to provide a computer-readable storage medium that can shorten the anti-spin parachute parameter selection cycle and reduce the R&D test costs.

[0009] In order to achieve the above-mentioned first purpose, the method for determining the parameters of an aircraft anti-spin parachute provided by the present invention includes: obtaining the tailspin mode of the target aircraft, and obtaining the corresponding modal coefficient according to the tailspin mode; obtaining the distance from the tail of the target aircraft to the center of gravity of the aircraft, the chord length of the aircraft wing tip, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft and the wing span of the aircraft; obtaining the airfoil correction coefficient according to the chord length of the aircraft wing tip and the average aerodynamic chord length of the aircraft wing; obtaining the effective circle diameter of the aircraft anti-spin parachute according to the modal coefficient, the airfoil correction coefficient, the distance from the tail to the center of gravity of the aircraft, the wing area of ​​the aircraft and the wing span of the aircraft; confirming the target type of the aircraft anti-spin parachute, calculating the effective circle diameter using the calculation formula corresponding to the target type, and obtaining the canopy size parameters of the aircraft anti-spin parachute.

[0010] It can be seen from the above scheme that the method for determining the parameters of the aircraft anti-spin parachute of the present invention obtains the effective circle diameter of the aircraft anti-spin parachute by utilizing the modal coefficient, the airfoil correction coefficient, the distance from the tail to the center of gravity of the aircraft, the aircraft wing area and the aircraft wing span, and calculates the canopy size parameters of the aircraft anti-spin parachute through the effective circle diameter, thereby quickly obtaining the parameter selection of the aircraft anti-spin parachute, and there is no need to conduct long-term and high-cost tail swirl wind tunnel tests to select the parameters of the anti-spin parachute, which can shorten the parameter selection cycle of the anti-spin parachute and reduce the research and development test costs.

[0011] In a further embodiment, the airfoil correction factor is obtained by the following formula: k1 = (;0 +; 梢 ) / 2l0; where the chord length of the aircraft wing tip is l 梢 , the average aerodynamic chord length of the aircraft wing is l0.

[0012] It can be seen that when an aircraft enters a spin, the wing root usually stalls first, and the rotational driving force of the spin mainly comes from the outer wing part that has not stalled. Therefore, the airfoil correction coefficient can be obtained through the aircraft wingtip chord length and the average aerodynamic chord length of the aircraft wing to improve the accuracy of the parameters.

[0013] In a further embodiment, the effective circle diameter is obtained by the following formula: Among them, k is the modal coefficient, k1 is the airfoil correction coefficient, B is the distance from the tail to the center of gravity of the aircraft, S is the aircraft wing area, and b is the aircraft wing span.

[0014] In a further solution, the effective circle diameter is calculated using a calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute, including: the target type is a ring-seam parachute, and the canopy diameter of the aircraft anti-spin parachute is obtained by the following formula: Where d is the effective circle diameter, C D is the resistance coefficient.

[0015] In a further solution, the effective circle diameter is calculated using a calculation formula corresponding to the target type, and the step of obtaining the canopy size parameters of the aircraft anti-spin parachute includes: when the target type is a cross parachute, the canopy length of the aircraft anti-spin parachute is obtained by the following formula: Among them, d is the effective circle diameter and k2 is the aspect ratio.

[0016] It can be seen that different types of aircraft anti-spin parachutes require different parameters to be considered. Therefore, by calculating the effective circle diameter using the calculation formula corresponding to the target type, the canopy size parameters of the aircraft anti-spin parachute are obtained, which can meet the design requirements of anti-spin parachutes of various types of aircraft.

[0017] In a further scheme, after the step of obtaining the distance from the tail to the center of gravity of the target aircraft, the wingtip chord length of the aircraft, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft and the wingspan of the aircraft, it also includes: obtaining the parachute rope length of the aircraft anti-spin parachute according to the distance from the tail to the center of gravity of the aircraft.

[0018] It can be seen that if the parachute line is too short, it is easy to get entangled in the aircraft or be in the tail turbulence, making it difficult to inflate. If the parachute line is too long, the parachute will move along the spin axis above the aircraft, mainly generating a pitch moment, while the yaw moment required for spin recovery is very small, resulting in the inability to recover from the spin. Therefore, the parachute line length of the aircraft anti-spin parachute is determined by the distance from the tail to the center of gravity of the aircraft, which can optimize the accuracy of the parachute line length parameter design.

[0019] In order to achieve the second purpose of the present invention, the present invention provides a computer device including a processor and a memory, the memory stores a computer program, and when the computer program is executed by the processor, the steps of the above-mentioned method for determining parameters of an aircraft anti-spin parachute are implemented.

[0020] In order to achieve the third objective of the present invention, the present invention provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a controller, the steps of the above-mentioned method for determining parameters of an aircraft anti-spin parachute are implemented. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a flow chart of an embodiment of a method for determining parameters of an aircraft anti-spin parachute according to the present invention.

[0022] Figure 2 It is a schematic diagram of the operation of an aircraft anti-spin parachute in an embodiment of the method for determining parameters of an aircraft anti-spin parachute of the present invention.

[0023] Figure 3 It is a structural schematic diagram of an aircraft wing in an embodiment of a method for determining parameters of an aircraft anti-spin parachute of the present invention.

[0024] Figure 4It is a plan view of a cross parachute canopy in an embodiment of a method for determining parameters of an aircraft anti-spin parachute of the present invention.

[0025] The present invention is further described below in conjunction with the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0026] Aircraft anti-spin parachute parameter determination method embodiment:

[0027] The method for determining parameters of an aircraft anti-spin parachute of the present invention is a computer program applied to a computer device and is used for selecting parameters of an aircraft anti-spin parachute.

[0028] like Figure 1 As shown, in this embodiment, when the method for determining the parameters of the aircraft anti-spin parachute is working, step S1 is first executed to obtain the tailspin mode of the target aircraft, and the corresponding modal coefficient is obtained according to the tailspin mode. Since the aircraft has different recovery torque requirements under different tailspin modes, it is necessary to introduce modal coefficients when setting the parameters of the aircraft anti-spin parachute. The tailspin mode includes a flat spin mode and a steep spin mode, and both the flat spin mode and the steep spin mode are provided with corresponding modal coefficients, which can be pre-set according to experimental data. For example, the corresponding modal coefficient under the flat spin mode is 0.76, and the corresponding modal coefficient under the steep spin mode is 0.69.

[0029] After obtaining the modal coefficients, execute step S2 to obtain the distance from the tail to the center of gravity of the target aircraft, the wingtip chord length, the average aerodynamic chord length of the aircraft wing, the wing area and the wing span of the aircraft. The distance from the tail to the center of gravity of the target aircraft, the wingtip chord length, the average aerodynamic chord length of the aircraft wing, the wing area and the wing span of the target aircraft can be set according to the actual size of the target aircraft. Preferably, the size parameters of multiple aircraft types can be pre-set, and the corresponding size parameters can be automatically obtained according to the selected target aircraft type. See Figure 2 and Figure 3 , the distance from the tail to the center of gravity Z of the aircraft is B, and the chord length of the aircraft wing tip is l 梢 , the average aerodynamic chord length of the aircraft wing is l0. The aircraft wing tip chord length, the average aerodynamic chord length of the aircraft wing, the aircraft wing area and the aircraft wing span are the parameters of the aircraft main wing 11.

[0030] After obtaining the distance from the tail of the target aircraft to the center of gravity of the aircraft, the wingtip chord length of the aircraft, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft and the wing span of the aircraft, step S3 is executed to obtain the airfoil correction coefficient according to the wingtip chord length of the aircraft and the average aerodynamic chord length of the aircraft wing. When the aircraft enters a tailspin, the wing root usually stalls first, and the rotational driving force of the tailspin mainly comes from the outer wing part of the wing that has not stalled. Therefore, the airfoil correction coefficient is obtained by the wingtip chord length of the aircraft and the average aerodynamic chord length of the aircraft wing, which can improve the accuracy of the parameters. In this embodiment, the airfoil correction coefficient is obtained by the following formula: k1=(l0+l 梢 ) / 2l0; where the chord length of the aircraft wing tip is l 梢 , the average aerodynamic chord length of the aircraft wing is l0.

[0031] After obtaining the airfoil correction coefficient, step S4 is performed to obtain the effective circular diameter of the aircraft anti-spin parachute according to the modal coefficient, the airfoil correction coefficient, the distance from the tail to the center of gravity of the aircraft, the aircraft wing area and the aircraft wing span. The effective circular area of ​​the anti-spin parachute is one of the key factors affecting the performance of the anti-spin parachute. Generally, the larger the effective circular area, the greater the air resistance suffered by the anti-spin parachute. The effective circular area of ​​the anti-spin parachute needs to be determined according to the specific parameters of the aircraft and the use environment to ensure that enough lift and control can be provided at the critical moment to help the aircraft land safely. In order to determine the effective circular area, it is necessary to obtain the effective circular diameter of the aircraft anti-spin parachute.

[0032] In this embodiment, the effective circle diameter is obtained by the following formula: Among them, k is the modal coefficient, k1 is the airfoil correction coefficient, B is the distance from the tail to the center of gravity of the aircraft, S is the aircraft wing area, and b is the aircraft wing span.

[0033] After obtaining the effective circle diameter, step S5 is executed to confirm the target type of the aircraft anti-spin parachute, and the effective circle diameter is calculated using the calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute. Different types of aircraft anti-spin parachutes require different parameters to be considered. Therefore, by calculating the effective circle diameter using the calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute, the design requirements of various types of aircraft anti-spin parachutes can be met.

[0034] In this embodiment, the step of calculating the effective circle diameter by using the calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute includes: when the target type is a ring-seam parachute, the canopy diameter of the aircraft anti-spin parachute is obtained by the following formula: Where d is the effective circle diameter, C D The drag coefficient can be determined according to the parachute configuration and material used by the aircraft anti-spin parachute, which is a well-known technology for those skilled in the art and will not be described in detail here.

[0035] In this embodiment, the step of calculating the effective circle diameter by using the calculation formula corresponding to the target type to obtain the canopy size parameter of the aircraft anti-spin parachute also includes: when the target type is a cross parachute, the canopy length of the aircraft anti-spin parachute is obtained by the following formula: Where d is the effective circle diameter; k2 is the canopy length-to-width ratio, i.e., the ratio of canopy length to canopy width. The canopy length-to-width ratio k2 can be set according to actual needs. The canopy length w is obtained as Figure 4 As shown, the canopy width is H.

[0036] In addition, after executing step S2, obtaining the distance from the tail of the target aircraft to the center of gravity of the aircraft, the chord length of the aircraft wing tip, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft and the wing span of the aircraft, it also includes: obtaining the parachute rope length of the aircraft anti-spin parachute according to the distance from the tail to the center of gravity of the aircraft. In this embodiment, the calculation formula of the parachute rope length L is as follows: L=1.55B. This calculation formula is obtained based on experimental data. If the parachute rope is too short, it is easy to be entangled with the fuselage or be in the tail turbulence, making it difficult to inflate. If the parachute rope is too long, it will cause the parachute to move along the spin axis above the aircraft, mainly generating a pitching moment, and the yaw moment required for the tail spin recovery obtained is very small, resulting in the inability to recover from the tail spin. Therefore, the parachute rope length of the aircraft anti-spin parachute is determined by the distance from the tail to the center of gravity of the aircraft, and the accuracy of the parachute rope length parameter design can be optimized.

[0037] It can be seen from the above scheme that the method for determining the parameters of the aircraft anti-spin parachute of the present invention obtains the effective circle diameter of the aircraft anti-spin parachute by utilizing the modal coefficient, the airfoil correction coefficient, the distance from the tail to the center of gravity of the aircraft, the aircraft wing area and the aircraft wing span, and calculates the canopy size parameters of the aircraft anti-spin parachute through the effective circle diameter, thereby quickly obtaining the parameter selection of the aircraft anti-spin parachute, and there is no need to conduct long-term and high-cost tail swirl wind tunnel tests to select the parameters of the anti-spin parachute, which can shorten the parameter selection cycle of the anti-spin parachute and reduce the research and development test costs.

[0038] Computer device embodiment:

[0039] The computer device of this embodiment includes a controller, and when the controller executes a computer program, the steps in the above-mentioned aircraft anti-spin parachute parameter determination method embodiment are implemented.

[0040] For example, a computer program may be divided into one or more modules, one or more modules are stored in a memory and executed by a controller to implement the present invention. One or more modules may be a series of computer program instruction segments capable of implementing specific functions, and the instruction segments are used to describe the execution process of the computer program in a computer device.

[0041] The computer device may include, but is not limited to, a controller and a memory. Those skilled in the art will appreciate that the computer device may include more or fewer components, or a combination of certain components, or different components, for example, the computer device may also include input and output devices, network access devices, buses, etc.

[0042] For example, the controller may be a central processing unit (CPU), other general controllers, digital signal processors (DSP), application specific integrated circuits (ASIC), field programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general controller may be a microcontroller or any conventional controller, etc. The controller is the control center of the computer device, and uses various interfaces and lines to connect the various parts of the entire computer device.

[0043] The memory can be used to store computer programs and / or modules. The controller realizes various functions of the computer device by running or executing the computer programs and / or modules stored in the memory, and calling the data stored in the memory. For example, the memory can mainly include a program storage area and a data storage area, wherein the program storage area can store an operating system, an application required for at least one function (such as a sound receiving function, a sound conversion to text function, etc.), etc.; the data storage area can store data created according to the use of the mobile phone (such as audio data, text data, etc.), etc. In addition, the memory can include a high-speed random access memory, and can also include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (FlashCard), at least one disk storage device, a flash memory device, or other volatile solid-state storage devices.

[0044] Computer readable storage medium embodiment:

[0045] If the module integrated in the computer device of the above embodiment 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 this understanding, the implementation of all or part of the process in the above aircraft anti-spin parachute parameter determination method embodiment can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium. When the computer program is executed by the controller, the steps of the above aircraft anti-spin parachute parameter determination method embodiment can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in the form of source code, object code, executable file or some intermediate form. The storage medium may include: any entity or device capable of carrying computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media does not include electrical carrier signals and telecommunications signals.

[0046] It should be noted that the above are only preferred embodiments of the present invention, but the design concept of the invention is not limited thereto, and any non-substantial modifications made to the present invention using this concept also fall within the protection scope of the present invention.

Claims

1. A method for determining parameters of an aircraft anti-spin parachute, characterized in that: include: Acquire a spin mode of the target aircraft, and obtain corresponding modal coefficients according to the spin mode; Obtaining the distance from the tail to the center of gravity of the target aircraft, the wingtip chord length of the aircraft, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft, and the wingspan of the aircraft; Obtaining an airfoil correction coefficient according to the wing tip chord length of the aircraft and the average aerodynamic chord length of the aircraft wing; Obtaining the effective circle diameter of the aircraft anti-spin parachute according to the modal coefficient, the airfoil correction coefficient, the distance from the tail to the center of gravity of the aircraft, the wing area of ​​the aircraft and the wing span of the aircraft; The target type of the aircraft anti-spin parachute is confirmed, and the effective circle diameter is calculated using a calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute.

2. The method for determining parameters of an aircraft anti-spin parachute according to claim 1, characterized in that: The airfoil correction factor is obtained by the following formula: k1=(l0+lt) / 2l0; Among them, the chord length of the aircraft wing tip is ltip, and the average aerodynamic chord length of the aircraft wing is l0.

3. The method for determining parameters of an aircraft anti-spin parachute according to claim 1, characterized in that: The effective circle diameter is obtained by the following formula: Wherein, k is the modal coefficient, k1 is the airfoil correction coefficient, B is the distance from the tail to the center of gravity of the aircraft, S is the wing area of ​​the aircraft, and b is the wing span of the aircraft.

4. The method for determining parameters of an aircraft anti-spin parachute according to claim 1, characterized in that: The step of calculating the effective circle diameter by using the calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute comprises: The target type is a ring-seam parachute, and the canopy diameter of the aircraft anti-spin parachute is obtained by the following formula: Where, d is the effective circle diameter, C D is the resistance coefficient.

5. The method for determining parameters of an aircraft anti-spin parachute according to claim 1, characterized in that: The step of calculating the effective circle diameter by using the calculation formula corresponding to the target type to obtain the canopy size parameters of the aircraft anti-spin parachute comprises: The target type is a cross parachute, and the canopy length of the aircraft anti-spin parachute is obtained by the following formula: Wherein, d is the effective circle diameter, and k2 is the aspect ratio of the canopy.

6. The method for determining parameters of an aircraft anti-spin parachute according to any one of claims 1 to 5, characterized in that: After the step of obtaining the distance from the tail to the center of gravity of the target aircraft, the wingtip chord length of the aircraft, the average aerodynamic chord length of the aircraft wing, the wing area of ​​the aircraft, and the wing span of the aircraft, the method further includes: The parachute rope length of the anti-spin parachute of the aircraft is obtained according to the distance from the tail to the center of gravity of the aircraft.

7. A computer device comprising a processor and a memory, characterized in that: The memory stores a computer program, and when the computer program is executed by the processor, the steps of the method for determining parameters of an aircraft anti-spin parachute as claimed in any one of claims 1 to 6 are implemented.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by the controller, the steps of the method for determining parameters of an aircraft anti-spin parachute as claimed in any one of claims 1 to 6 are implemented.

Images