Method and device for determining turning air-drop gradient of transport plane

Abstract

The invention belongs to the technical field of flight design, and particularly relates to a method and device for determining the turning air-drop gradient of a transport plane, and the method comprises the steps: S1, determining a first critical gradient angle according to the object dropping mass and the maximum lateral limited power of an air-drop guide rail; step S2, calculating a second critical slope angle according to the balance between the lateral force overturning torque and the normal force overturning torque generated by the aircraft when the aircraft turns with the slope; and S3, the smaller value in the first critical slope angle and the second critical slope angle is selected as the turning air-drop slope of the transport plane. According to the invention, safe and controllable flight of the aircraft in turning air-drop task execution can be ensured, and the safe air-drop task capability of the transport plane is improved.

Description

Technical Field

[0001] The present application belongs to the field of flight design technology, and in particular relates to a method and device for determining the slope of a transport aircraft turning and airdropping. Background Art

[0002] Transport aircraft airdrop is a representation of the aircraft's mission capability. In order to better adapt to airdrop missions in a changing environment, in addition to airdrops in level flight, the aircraft must still have airdrop capabilities under certain maneuverability. For example, during the aircraft's turning maneuvers, whether the dropped items can be safely ejected from the cabin, and whether the aircraft is safe and controllable, this series of issues needs to be technically demonstrated and analyzed to provide feasibility analysis conclusions. The expansion and improvement of transport aircraft mission capabilities is one of the issues that users are particularly concerned about. In order to better and more safely perform airdrop missions, it is necessary to clarify the critical safety indicator of turning maneuver airdrops—the turning slope limit. From the perspective of aircraft platform mission capabilities, in order to cope with wartime or changing complex environments, it is urgent to expand the airdrop capabilities in different flight states and improve the aircraft's comprehensive combat capabilities.

[0003] At present, the selection of airdrop mission status for transport aircraft in China is relatively simple, and only the aircraft's steady level flight state is considered. At this time, the aircraft's bank angle is 0°, and the aircraft is basically considered to be in stable level flight, without considering the turning and maneuvering state. Based on this consideration, it is necessary to expand the flight state of the airdrop mission and improve the adaptability of the aircraft's airdrop mission. When airdropping with a slope during a turn, excessive slope may cause the aircraft to roll over and hit the side wall of the aircraft. At the same time, there may be a jam between the cargo and the guide rail, and the center of gravity of the aircraft will move backward sharply, greatly reducing flight safety. Summary of the invention

[0004] In order to solve the above problems, the present application provides a method and device for determining the slope of a transport aircraft turning and airdropping, providing users with safety guidance for selecting the slope angle of a sloped turn and airdropping.

[0005] The first aspect of the present application provides a method for determining the slope of a transport aircraft turning airdrop, which mainly includes:

[0006] Step S1, determining a first critical slope angle according to the mass of the object to be dropped and the maximum lateral limiting force of the airdrop guide rail;

[0007] Step S2, calculating a second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated by the aircraft when turning with a slope on the object;

[0008] Step S3: Select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning and airdropping slope.

[0009] Preferably, in step S1, the first critical slope angle φ1 is calculated by the following formula:

[0010] φ1=arcsin(F lim / m h / g)*57.3;

[0011] Among them, F lim is the maximum lateral force limit of the airdrop guide rail, m h The mass of input.

[0012] Preferably, step S2 further comprises:

[0013] Step S21: Calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the height of the drop;

[0014] Step S22: Calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width;

[0015] Step S23, constructing a balance equation of the first flipping moment L1 and the second flipping moment L2: L1=L2, so as to calculate the slope of the aircraft turning, and use it as the second critical slope angle φ2:

[0016] φ2=arctan(x / h)*57.3.

[0017] Preferably, in step S21, the lateral force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: x :

[0018] F x =m h *g*sin(φ2 / 57.3).

[0019] Preferably, in step S22, the normal force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: y :

[0020] F y =m h *g*cos(φ2 / 57.3).

[0021] Preferably, the gravity acceleration is corrected by the trim height H of the aircraft:

[0022] g=9.8*6356766 2 / (6356766+H) 2 .

[0023] The second aspect of the present application provides a device for determining the slope of a transport aircraft turning airdrop, which mainly includes:

[0024] A first critical slope angle determination module, used to determine the first critical slope angle according to the mass of the dropped object and the maximum lateral limiting force of the airdrop guide rail;

[0025] A second critical slope angle determination module is used to calculate the second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated by the aircraft when turning with a slope.

[0026] The transport aircraft turning airdrop slope selection module is used to select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning airdrop slope.

[0027] Preferably, in the first critical slope angle determination module, the first critical slope angle φ1 is calculated by the following formula:

[0028] φ1=arcsin(F lim / m h / g)*57.3;

[0029] Among them, F lim is the maximum lateral force limit of the airdrop guide rail, m h The mass of input.

[0030] Preferably, the second critical slope angle determination module includes:

[0031] The first rollover moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the height of the drop;

[0032] The second turning moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width;

[0033] The balance equation solving unit is used to construct the balance equation of the first flipping moment L1 and the second flipping moment L2: L1 = L2, so as to solve the slope of the aircraft turning and use it as the second critical slope angle φ2:

[0034] φ2=arctan(x / h)*57.3.

[0035] Preferably, in the first turning moment calculation unit, the lateral force F of the object when the aircraft turns with a slope is calculated by the following formula: x :

[0036] F x =m h *g*sin(φ2 / 57.3).

[0037] Preferably, in the second turning moment calculation unit, the normal force F of the object when the aircraft turns with a slope is calculated by the following formula: y :

[0038] F y =m h *g*cos(φ2 / 57.3).

[0039] Preferably, it also includes a gravity computer correction module for correcting the gravity acceleration by the trim height H of the aircraft:

[0040] g=9.8*6356766 2 / (6356766+H) 2 .

[0041] 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 method for determining the slope of a transport aircraft turning airdrop as described above.

[0042] A fourth aspect of the present application provides a readable storage medium, which stores a computer program. When the computer program is executed by a processor, it is used to implement the method for determining the slope of a transport aircraft turning airdrop as described above.

[0043] This application can ensure safe and controllable flight during the execution of aircraft turning airdrop missions, and improve the transport aircraft's ability to perform safe airdrop missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 It is a flow chart of a preferred embodiment of the method for determining the slope of a transport aircraft turning and airdropping in the present application.

[0045] 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

[0046] 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.

[0047] The first aspect of the present application provides a method for determining the slope of a transport aircraft turning airdrop, such as Figure 1 As shown, it mainly includes:

[0048] Step S1, determining a first critical slope angle according to the mass of the dropped object and the maximum lateral limiting force of the airdrop guide rail.

[0049] This step is used to limit the maximum lateral force F of the airdrop rail. lim To solve the first critical slope angle φ1. In some optional implementations, in step S1, the first critical slope angle φ1 is calculated by the following formula: φ1 = arcsin (F lim / m h / g)*57.3; where F lim is the maximum lateral force limit of the airdrop guide rail, m h In some optional implementations, the gravity acceleration is corrected by the trim height H of the aircraft: g = 9.8 * 6356766 2 / (6356766+H) 2 .

[0050] Given the standard atmospheric conditions, a certain type of aircraft flying at an altitude of H = 1500m; the weight of the drop is 3000kg; the drop width is 1m. For example, when the maximum lateral force of the airdrop rail is F lim When the load is 400kg, the first critical slope angle φ1 is 7.7°. lim When the load is 800kg, the first critical slope angle φ1 is 15.5°. lim When the load is 1200kg, the first critical slope angle φ1 is 23.6°. lim When the load is 1600kg, the first critical slope angle φ1 is 32.2°. limWhen the load is 2000kg, the first critical slope angle φ1 is solved to be 41.8°.

[0051] Step S2, calculating a second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated on the dropped object when the aircraft turns with a slope.

[0052] This step is used to calculate the second critical slope angle based on the overturning moment. In some optional embodiments, step S2 further includes:

[0053] Step S21: Calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the drop height, F x =m h *g*sin(φ2 / 57.3);

[0054] Step S22: Calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width, F y =m h *g*cos(φ2 / 57.3);

[0055] Step S23, constructing a balance equation of the first flipping moment L1 and the second flipping moment L2: L1=L2, so as to calculate the slope of the aircraft turning, and use it as the second critical slope angle φ2:

[0056] φ2=arctan(x / h)*57.3.

[0057] In this embodiment, when the throwing height is 1m, the calculated second critical slope angle φ2 is 45°, when the throwing height is 1.2m, the calculated second critical slope angle φ2 is 45°, when the throwing height is 1m, the calculated second critical slope angle φ2 is 39.8°, when the throwing height is 1.4m, the calculated second critical slope angle φ2 is 35.5°, when the throwing height is 1.6m, the calculated second critical slope angle φ2 is 32°, and when the throwing height is 1.8m, the calculated second critical slope angle φ2 is 29.1°.

[0058] Step S3: Select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning and airdropping slope.

[0059] This application proposes a method for determining the slope limit of a transport aircraft's turning airdrop, which makes up for the previous shortcoming of incomplete selection of the transport aircraft's airdrop mission status; provides a valuable design theory analysis method for the design of various aircraft airdrop missions and the design of safe flight posture boundaries for turning airdrops with slope states; and greatly improves the applicability of transport aircraft airdrop missions.

[0060] The second aspect of the present application provides a device for determining the slope of a transport aircraft turning airdrop corresponding to the above method, mainly comprising:

[0061] A first critical slope angle determination module, used to determine the first critical slope angle according to the mass of the dropped object and the maximum lateral limiting force of the airdrop guide rail;

[0062] A second critical slope angle determination module is used to calculate the second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated by the aircraft when turning with a slope.

[0063] The transport aircraft turning airdrop slope selection module is used to select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning airdrop slope.

[0064] In some optional implementations, in the first critical slope angle determination module, the first critical slope angle φ1 is calculated by the following formula:

[0065] φ1=arcsin(F lim / m h / g)*57.3;

[0066] Among them, F lim is the maximum lateral force limit of the airdrop guide rail, m h The mass of input.

[0067] In some optional implementations, the second critical slope angle determination module includes:

[0068] The first rollover moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the height of the drop;

[0069] The second turning moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width;

[0070] The balance equation solving unit is used to construct the balance equation of the first flipping moment L1 and the second flipping moment L2: L1 = L2, so as to solve the slope of the aircraft turning and use it as the second critical slope angle φ2:

[0071] φ2=arctan(x / h)*57.3.

[0072] In some optional embodiments, in the first flipping moment calculation unit, the lateral force F of the object when the aircraft turns with a slope is calculated by the following formula: x :

[0073] F x =m h *g*sin(φ2 / 57.3).

[0074] In some optional embodiments, in the second flipping moment calculation unit, the normal force F of the object when the aircraft turns with a slope is calculated by the following formula: y :

[0075] F y =m h *g*cos(φ2 / 57.3).

[0076] In some optional embodiments, a gravity computer correction module is further included, which is used to correct the gravity acceleration by the trim height H of the aircraft:

[0077] g=9.8*6356766 2 / (6356766+H) 2 .

[0078] 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 determining the slope of a transport aircraft turning and airdropping.

[0079] 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 above-mentioned method for determining the slope of a transport aircraft turning airdrop. The computer-readable storage medium may be included in the device described in the above-mentioned embodiment; or it may exist independently without being assembled into the device. The above-mentioned computer-readable storage medium carries one or more programs, and when the above-mentioned one or more programs are executed by the device, the data is processed according to the above-mentioned method.

[0080] 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 2The 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.

[0081] like Figure 2 As 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.

[0082] 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.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] 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 determining the slope of a transport aircraft turning and airdropping, characterized in that: include: Step S1, determining a first critical slope angle according to the mass of the object to be dropped and the maximum lateral limiting force of the airdrop guide rail; Step S2, calculating a second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated by the aircraft when turning with a slope on the object; Step S3: Select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning and airdropping slope.

2. The method for determining the slope of a transport aircraft turning and airdropping according to claim 1, characterized in that: In step S1, the first critical slope angle φ1 is calculated by the following formula: φ1=arcsin(F lim / m h / g)*57.3; Among them, F lim is the maximum lateral force limit of the airdrop guide rail, m h The mass of input.

3. The method for determining the slope of a transport aircraft turning and airdropping according to claim 2, characterized in that: Step S2 further comprises: Step S21: Calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the height of the drop; Step S22: Calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width; Step S23, constructing a balance equation of the first flipping moment L1 and the second flipping moment L2: L1=L2, so as to calculate the slope of the aircraft turning, and use it as the second critical slope angle φ2: φ2=arctan(x / h)*57.

3.

4. The method for determining the slope of a transport aircraft turning and airdropping according to claim 3, characterized in that: In step S21, the lateral force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: x : F x =m h *g*sin(φ2 / 57.3)。 5. The method for determining the slope of a transport aircraft turning and airdropping according to claim 3, characterized in that: In step S22, the normal force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: y : F y =m h *g*cos(φ2 / 57.3)。 6. The method for determining the slope of a transport aircraft turning and airdropping according to claim 2, characterized in that: The gravity acceleration is corrected by the aircraft's trim height H: g=9.8*6356766 2 / (6356766+H) 2 。 7. A device for determining the slope of a transport aircraft turning and airdropping, characterized in that: include: A first critical slope angle determination module, used to determine the first critical slope angle according to the mass of the dropped object and the maximum lateral limiting force of the airdrop guide rail; A second critical slope angle determination module is used to calculate the second critical slope angle according to the balance between the lateral force turning moment and the normal force turning moment generated by the aircraft when turning with a slope. The transport aircraft turning airdrop slope selection module is used to select the smaller value between the first critical slope angle and the second critical slope angle as the transport aircraft turning airdrop slope.

8. The device for determining the slope of a transport aircraft turning and airdropping according to claim 7, characterized in that: In the first critical slope angle determination module, the first critical slope angle φ1 is calculated by the following formula: φ1=arcsin(F lim / m h / g)*57.3; Among them, F lim is the maximum lateral force limit of the airdrop guide rail, m h The mass of input.

9. The device for determining the slope of a transport aircraft turning and airdropping according to claim 8, characterized in that: The second critical slope angle determination module includes: The first rollover moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope x The first turning moment L1 generated: L1 = F x *h / 2; where h is the height of the drop; The second turning moment calculation unit is used to calculate the lateral force F of the object when the aircraft turns with a slope y The second turning moment L2 generated: L2 = F y *x / 2; where x is the object width; The balance equation solving unit is used to construct the balance equation of the first flipping moment L1 and the second flipping moment L2: L1 = L2, so as to solve the slope of the aircraft turning and use it as the second critical slope angle φ2: φ2=arctan(x / h)*57.

3.

10. The device for determining the slope of a transport aircraft turning and airdropping according to claim 9, characterized in that: In the first turning moment calculation unit, the lateral force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: x : F x =m h *g*sin(φ2 / 57.3)。 11. The device for determining the slope of a transport aircraft turning and airdropping according to claim 9, characterized in that: In the second turning moment calculation unit, the normal force F of the object thrown when the aircraft turns with a slope is calculated by the following formula: y : F y =m h *g*cos(φ2 / 57.3)。 12. The device for determining the slope of a transport aircraft turning and airdropping according to claim 8, characterized in that: It also includes a gravity computer correction module, which is used to correct the gravity acceleration through the aircraft's trim height H: g=9.8*6356766 2 / (6356766+H) 2 。 13. A computer device, characterized in that: The method 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 method for determining the slope of a transport aircraft turning airdrop as described in any one of claims 1 to 6.

14. 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 method for determining the slope of a transport aircraft turning and airdropping as described in any one of claims 1-6.

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