Fairing optimization design method, device and equipment and computer readable storage medium

Abstract

According to the fairing optimization design method, device and equipment and the computer readable storage medium, the self-separation aerodynamic force theoretical value of the fairing subjected to optimization design under the separation working condition is calculated through optimization design of the sweepforward profile appearance of the fairing and based on a simulation calculation means; and if the self-separation aerodynamic force theoretical value is smaller than the self-separation aerodynamic force design required value, the forward-swept profile appearance of the fairing is repeatedly optimized and designed until the self-separation aerodynamic force theoretical value is larger than or equal to the self-separation aerodynamic force design required value. An additional fairing separation mechanical actuating mechanism is not needed, the negative mass of the fairing is reduced, and therefore the performance of the aircraft is improved. By optimizing the shape of the sweepforward profile of the fairing, self-separation aerodynamic fairing bodies of different sizes can be designed, and the self-separation aerodynamic force requirements under different separation working conditions are met. The problems that an additional fairing separation mechanical action mechanism is needed for traditional fairing separation, and the defects of poor stability and complexity exist are solved.

Description

Technical Field

[0001] This application relates to the field of aerodynamic layout design, specifically to a fairing optimization design method, apparatus, device, and computer-readable storage medium. Background Technology

[0002] Fairings are used in aircraft to interact with the air in a unique way, ensuring that the airflow is directed in the most efficient direction and improving flight efficiency. The fairing is jettisoned after the aircraft reaches a certain altitude and is safely separated via a mechanical mechanism after reaching the optimal ignition point. As a crucial aerodynamic component, the fairing plays a key role in multiple fields, demonstrating its wide-ranging value in protecting payloads and optimizing aerodynamic performance.

[0003] In related technologies, fairing separation requires an additional fairing separation mechanical action mechanism to increase the separation aerodynamic force and ensure fairing separation. However, the separation mechanical action mechanism has the disadvantages of poor stability and complexity, and increases the weight of the aircraft. Summary of the Invention

[0004] This application provides a fairing optimization design method, apparatus, device, and computer-readable storage medium, which can solve the technical problem in the related art that fairing separation requires an additional fairing separation mechanical action mechanism to increase the separation aerodynamic force of fairing separation. However, the separation mechanical action mechanism has the disadvantages of poor stability and complexity, and increases the weight of the aircraft.

[0005] In a first aspect, embodiments of this application provide a fairing optimization design method, the fairing optimization design method comprising: The forward-swept surface shape of the fairing was optimized, and the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions was calculated based on simulation calculation methods. If the theoretical value of the self-separating aerodynamic force is less than the design requirement value of the self-separating aerodynamic force, the forward sweep profile of the fairing is repeatedly optimized until the theoretical value of the self-separating aerodynamic force is greater than or equal to the design requirement value of the self-separating aerodynamic force.

[0006] In conjunction with the first aspect, in one embodiment, the optimized design of the fairing's forward-swept surface profile includes: The length of the fairing's forward sweep line was increased.

[0007] In conjunction with the first aspect, in one embodiment, the optimized design of the fairing's forward-swept surface profile includes: Increase the forward sweep angle of the fairing.

[0008] In conjunction with the first aspect, in one embodiment, the optimized design of the fairing's forward-swept surface profile includes: Increase the curvature of the fairing's outline.

[0009] In conjunction with the first aspect, in one embodiment, before optimizing the forward-swept surface shape of the fairing and calculating the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions based on simulation calculations, the method further includes: Based on the separation Mach number and angle of attack of the fairing, the self-separation aerodynamic design requirements of the fairing are determined.

[0010] In conjunction with the first aspect, in one embodiment, before determining the self-separation aerodynamic design requirements of the fairing based on the fairing's separation Mach number and angle of attack, the method further includes: Based on the aircraft's trajectory, speed, altitude, and control capabilities, the separation Mach number and angle of attack of the fairing are determined while meeting design quality and strength requirements.

[0011] Secondly, embodiments of this application provide a fairing optimization design apparatus, the fairing optimization design apparatus comprising: The fairing optimization module is used to optimize the design of the forward-swept surface shape of the fairing and calculate the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions based on simulation calculation methods. The judgment module is used to repeatedly optimize the design of the forward-swept surface shape of the fairing if the theoretical value of the self-separating aerodynamic force is less than the design requirement value of the self-separating aerodynamic force, until the theoretical value of the self-separating aerodynamic force is greater than or equal to the design requirement value of the self-separating aerodynamic force.

[0012] In conjunction with the second aspect, in one embodiment, the fairing optimization module is also used to lengthen the forward sweep line length of the fairing.

[0013] Thirdly, embodiments of this application provide a fairing optimization design device, which includes a processor, a memory, and a fairing optimization design program stored in the memory and executable by the processor. When the fairing optimization design program is executed by the processor, it implements the steps of the fairing optimization design method as described in some of the above embodiments.

[0014] Fourthly, embodiments of this application provide a computer-readable storage medium storing a fairing optimization design program, wherein when the fairing optimization design program is executed by a processor, it implements the steps of the fairing optimization design method as described in some of the above embodiments.

[0015] The beneficial effects of the technical solutions provided in this application include: By optimizing the forward-swept surface shape of the fairing and calculating the theoretical value of the self-separation aerodynamic force under separation conditions using simulation, the forward-swept surface shape of the fairing is repeatedly optimized until the theoretical value is greater than or equal to the design requirement. This eliminates the need for an additional fairing separation mechanical actuation mechanism, reducing the fairing's negative mass and thus improving aircraft performance. Optimizing the forward-swept surface shape allows for the design of fairings with varying self-separation aerodynamic forces to meet different separation conditions. This avoids the need for additional fairing separation mechanical actuation mechanisms, which increase the separation aerodynamic force and suffer from poor stability and complexity, while also increasing the aircraft's weight. Attached Figure Description

[0016] Figure 1 This is a flowchart illustrating an embodiment of the fairing optimization design method of this application; Figure 2 This is a structural schematic diagram of the nose section of an aircraft without a fairing, according to an embodiment of this application. Figure 3 This is a structural schematic diagram of the nose section of an aircraft with a fairing according to an embodiment of this application; Figure 4 This is a front view structural diagram of the fairing according to an embodiment of this application; Figure 5 This is a side view of the fairing structure according to an embodiment of this application; Figure 6 This is a top view of the fairing structure according to an embodiment of this application; Figure 7 This is a schematic diagram of the fairing separation process according to an embodiment of this application; Figure 8 The surface pressure cloud map of the fairing at a separation altitude of 20km, Mach number 6, and angle of attack of -8° is shown in the embodiment of this application. Figure 9 This is a schematic diagram of the hardware structure of the fairing optimization design device involved in the embodiments of this application; In the diagram: 1. Aircraft; 2. Fairing; 21. Forward sweep line; 22. Forward sweep profile; 23. Outline; 24. Explosive bolt; 25. Shaft. Detailed Implementation

[0017] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present application.

[0018] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0019] It is important to understand that, as shown in Table 1 below, the nose drag of aircraft 1 without fairing 2 and with fairing 2 is compared. It can be seen that the nose drag with fairing 2 is reduced by a maximum of 54% and an average of 36% compared with that without fairing 2. The fairing 2 has a significant effect on reducing the nose drag of aircraft 1, which shows the importance of fairing 2.

[0020] Table 1

[0021] in, Figure 2 This is a structural diagram of the nose section of an aircraft without a fairing. Figure 3 The diagram shows the structural outline of the nose of the aircraft with fairing. Explosive bolts 24 are arranged at the intersection of the forward sweep line 21 and the aerodynamic compression surface of the aircraft 1. A rotating shaft 25 is arranged at the bottom of the air intake lip of the aircraft 1. When the fairing 2 reaches the separation condition, the explosive bolts 24 are unlocked. Under the action of the self-separation aerodynamic force, the fairing 2 rotates around the rotating shaft 25 to a certain angle and then disengages from the rotating shaft 25. Under the action of the self-separation aerodynamic force, the fairing 2 achieves safe separation from the air intake.

[0022] in, Figure 4 , 5 Views 6 and 6 are three-view drawings of fairing 2. Figure 7 This is a schematic diagram of the fairing 2 separation process. Figure 8 The surface pressure cloud diagram of fairing 2 shows a pressure of 5000 Pa near the forward sweep angle α, while the pressure near its lower right is 5310.34 Pa, indicating a pressure difference. This suggests that fairing 2 possesses self-separation aerodynamic forces and tends to separate from aircraft 1. Therefore, by optimizing the shape of the forward sweep surface 22 of fairing 2, the self-separation aerodynamic forces of fairing 2 can be increased, enabling safe and reliable separation of the aircraft 1's air intake without the need for an additional fairing separation mechanical actuation mechanism.

[0023] In a first aspect, embodiments of this application provide a fairing optimization design method.

[0024] In one embodiment, reference is made to Figure 1 , Figure 1 This is a flowchart illustrating the first embodiment of the fairing optimization design method of this application. Figure 1 As shown, the fairing optimization design method includes: S100: Optimize the shape of the forward swept surface 22 of the fairing 2, and calculate the theoretical value of the self-separation aerodynamic force of the optimized fairing 2 under separation conditions based on simulation calculation methods. S200: If the theoretical value of the self-separating aerodynamic force is less than the design requirement value of the self-separating aerodynamic force, repeat the optimization design of the forward swept surface 22 of the fairing 2 until the theoretical value of the self-separating aerodynamic force is greater than or equal to the design requirement value of the self-separating aerodynamic force.

[0025] In this embodiment, step S100 optimizes the shape of the forward-swept surface 22 of the fairing 2 to reduce aerodynamic drag during flight and improve the aerodynamic performance of the fairing 2 during separation. After completing the optimization design, simulation calculation methods (such as computational fluid dynamics (CFD) software) are used to simulate the aerodynamic performance of the fairing 2 under separation conditions. Through simulation calculation, the aerodynamic force experienced by the fairing 2 during separation can be obtained, i.e., the theoretical value of the self-separation aerodynamic force. This theoretical value is an important basis for evaluating whether the design of the fairing 2 meets the requirements. If the theoretical value of the self-separation aerodynamic force is less than the design requirement value, the forward-swept surface 22 shape of the fairing 2 is optimized again until the theoretical value of the self-separation aerodynamic force is greater than or equal to the design requirement value. If the theoretical value of the self-separation aerodynamic force obtained from the simulation calculation is less than the design requirement value, it indicates that the current design of the fairing 2 is insufficient to meet the aerodynamic performance requirements during separation. Therefore, the steps of S100 need to be repeated to further optimize the shape of the forward-swept surface 22 of the fairing 2. Repeated optimization design may involve multiple iterations, and simulation calculations are required after each iteration to verify whether the theoretical values ​​of the self-separation aerodynamic forces meet the requirements. However, this is a crucial step in ensuring that the fairing 2 design meets the aerodynamic performance requirements during separation. Through iteration and optimization in steps S100 and S200, a forward-swept surface 22 shape of the fairing 2 that meets the self-separation aerodynamic design requirements can be finally obtained. Such a fairing 2 can withstand sufficient aerodynamic forces during separation, ensuring successful separation from the aircraft 1.

[0026] Furthermore, in one embodiment, S100 includes the following steps: S100-1: Adjust the length of the forward sweep line 21 of the fairing 2.

[0027] In this embodiment, see Figure 3 and Figure 5Increasing the length of the sweep line 21 of the fairing 2 can positively influence the self-separation aerodynamic forces between the fairing 2 and the aircraft 1. Increasing the length of the sweep line 21 alters the aerodynamic shape of the fairing 2, enabling it to generate greater aerodynamic drag when facing airflow. This increased drag helps provide a greater self-separation aerodynamic force for the fairing 2 during separation. When airflow passes over the fairing 2, the presence of the sweep line 21 causes a separation effect at the leading edge of the fairing 2. Increasing the length of the sweep line 21 can exacerbate this separation effect, resulting in a greater self-separation aerodynamic force. Increasing the sweep line 21 may also lead to the generation of more vortices around the fairing 2. These vortices interact with the fairing 2, further increasing the self-separation aerodynamic force. Lengthening the sweep line 21 of the fairing 2 is to optimize its aerodynamic shape. The initial sweep line 21 length is determined based on the overall design and aerodynamic requirements of the fairing 2. Computational fluid dynamics (CFD) software or other simulation tools are used to evaluate the aerodynamic performance of the initial design. Based on the initial design evaluation results, the length of the forward sweep line 21 was gradually adjusted. After each adjustment, an aerodynamic performance evaluation was required to determine the impact of the adjustment on the aerodynamic performance of the fairing 2. Through multiple iterations and adjustments, the optimal forward sweep line 21 length for the aerodynamic performance of the fairing 2 was found. Optimizing the forward sweep line 21 length of the fairing 2 can improve its aerodynamic and separation performance.

[0028] Furthermore, in one embodiment, S100 includes the following steps: S100-1: Increase the sweep angle α of fairing 2.

[0029] In this embodiment, see Figure 3 Increasing the forward sweep angle α of fairing 2 alters its aerodynamic shape, thereby generating greater self-separation aerodynamic force when facing airflow. This change helps fairing 2 separate from aircraft 1 more reliably at the predetermined separation moment.

[0030] Furthermore, in one embodiment, S100 includes the following steps: S100-1: Increase the curvature of the outline 23 of the fairing 2.

[0031] In this embodiment, when the curvature of the contour line 23 of the fairing 2 increases, the interaction between its surface and the airflow also changes. This results in the fairing 2 experiencing greater aerodynamic forces during separation, thereby enhancing the self-separation effect. The increased curvature causes the airflow to generate a stronger separation effect at the trailing edge of the fairing 2, further propelling the fairing 2 to separate from the main body of the aircraft 1. This improves its aerodynamic and separation performance.

[0032] Furthermore, in one embodiment, S100 includes the following steps: S100-1: Optimize the length of the forward sweep line 21, the forward sweep angle α, and the curvature of the contour line 23 of the fairing 2 to increase the self-separation aerodynamic force of the fairing 2.

[0033] In this embodiment, S100-1 aims to increase the self-separation aerodynamic force of the fairing 2 during the separation process by optimizing the length of the forward sweep line 21, the forward sweep angle α, and the curvature of the profile line 23. The length of the forward sweep line 21 refers to the length of the portion connecting the front of the fairing 2 to the main body of the aircraft 1. By optimizing the length of the forward sweep line 21, the relative position of the fairing 2 and the main body of the aircraft 1 can be adjusted, thereby affecting the airflow on the surface of the fairing 2. The forward sweep angle α refers to the angle between the front of the fairing 2 and the main body of the aircraft 1. Increasing the forward sweep angle α may change the aerodynamic shape of the fairing 2, making it more suitable for airflow requirements. An optimized forward sweep angle α helps reduce flight drag and generates greater aerodynamic force during separation, pushing the fairing 2 to separate from the main body of the aircraft 1. The curvature of the profile line 23 refers to the degree of curvature of the surface curve of the fairing 2. By increasing the curvature of the profile line 23, the interaction between the fairing 2 and the airflow can be changed, thereby enhancing its self-separation aerodynamic force. The optimized curvature of the profile 23 helps reduce airflow separation and vortex generation on the surface of the fairing 2, thereby improving aerodynamic efficiency.

[0034] Furthermore, in one embodiment, prior to S100, the following steps are included: S000-2: Based on the separation Mach number and angle of attack of fairing 2, determine the self-separation aerodynamic design requirements of fairing 2.

[0035] In this embodiment, prior to S100, the core of step S000-2 is to determine the design requirements for the self-separation aerodynamic force of the fairing 2 based on the already determined separation Mach number and angle of attack. Mach number and angle of attack are key factors affecting the aerodynamic performance of the fairing 2. They determine the magnitude and direction of the force exerted by the airflow on the fairing 2, thus directly affecting the separation process of the fairing 2. At different Mach numbers and angles of attack, the aerodynamic forces that the fairing 2 needs to withstand will vary. Therefore, it is necessary to determine the design requirements for the self-separation aerodynamic force of the fairing 2 based on these two parameters.

[0036] Table 2

[0037] Table 2 above shows the design requirements for the self-separation aerodynamic force of the fairing 2 under different angles of attack at Mach 5. Therefore, the self-separation aerodynamic force of the fairing 2 at Mach 5 and -8° angle of attack is 1612N.

[0038] Furthermore, in one embodiment, prior to S000, the following steps are included: S000-1: Based on the trajectory, speed, altitude, and control capabilities of aircraft 1, determine the separation Mach number and angle of attack of fairing 2 while meeting design quality and strength requirements.

[0039] In this embodiment, the flight trajectory determines the flight path of the aircraft 1 in the air, which directly affects the environmental conditions during the separation of the fairing 2. Flight speed (usually expressed as Mach number, i.e., the ratio of flight speed to the local speed of sound) is one of the key factors in determining the separation conditions. At different speeds, the force exerted by the airflow on the fairing 2 will vary significantly. Flight altitude affects atmospheric density and temperature, thus influencing the aerodynamic performance of the fairing 2 and the separation process. The control capabilities of the aircraft 1, including its attitude adjustment, speed control, and stability, have a significant impact on the separation process of the fairing 2. Therefore, based on the trajectory, speed, altitude, and control capabilities of the aircraft 1, the separation Mach number and angle of attack of the fairing 2 are determined while meeting the design quality and strength requirements.

[0040] Secondly, this application also provides a fairing optimization design device, which includes: a fairing optimization module, which is used to optimize the design of the forward swept surface 22 of the fairing 2 and calculate the theoretical value of the self-separation aerodynamic force of the optimized fairing 2 under separation conditions based on simulation calculation methods; and a judgment module, which is used to repeatedly optimize the design of the forward swept surface 22 of the fairing 2 if the theoretical value of the self-separation aerodynamic force is less than the design requirement value of the self-separation aerodynamic force, until the theoretical value of the self-separation aerodynamic force is greater than or equal to the design requirement value of the self-separation aerodynamic force.

[0041] Furthermore, in one embodiment, the fairing optimization module is also used to lengthen the sweep line 21 of the fairing 2.

[0042] The functions of each module in the fairing optimization design device correspond to the steps in the fairing optimization design method embodiment, and their functions and implementation processes will not be described in detail here.

[0043] Thirdly, embodiments of this application provide a fairing optimization design device, which can be a device with data processing capabilities such as a personal computer (PC), a laptop computer, or a server.

[0044] Reference Figure 9 , Figure 9 This is a schematic diagram of the hardware structure of the fairing optimization design device involved in the embodiments of this application. In the embodiments of this application, the fairing optimization design device may include a processor, a memory, a communication interface, and a communication bus.

[0045] The communication bus can be of any type and is used to interconnect the processor, memory, and communication interface.

[0046] The communication interface includes input / output (I / O) interfaces, physical interfaces, and logical interfaces used for interconnecting components within the fairing optimization design equipment, as well as interfaces used for interconnecting the fairing optimization design equipment with other devices (such as other computing devices or user equipment). Physical interfaces can be Ethernet interfaces, fiber optic interfaces, ATM interfaces, etc.; user equipment can be displays, keyboards, etc.

[0047] Memory can be various types of storage media, such as random access memory (RAM), read-only memory (ROM), non-volatile RAM (NVRAM), flash memory, optical storage, hard disk, programmable ROM (PROM), erasable PROM (EPROM), electrically erasable PROM (EEPROM), etc.

[0048] The processor can be a general-purpose processor, which can call the fairing optimization design program stored in the memory and execute the fairing optimization design method provided in the embodiments of this application. For example, the general-purpose processor can be a central processing unit (CPU). The method executed when the fairing optimization design program is called can be referred to in the various embodiments of the fairing optimization design method of this application, and will not be repeated here.

[0049] Those skilled in the art will understand that Figure 9 The hardware structure shown does not constitute a limitation of this application and may include more or fewer components than shown, or combine certain components, or have different component arrangements.

[0050] Fourthly, embodiments of this application also provide a readable storage medium.

[0051] The present application has a readable storage medium storing a fairing optimization design program, wherein when the fairing optimization design program is executed by a processor, it implements the steps of the fairing optimization design method as described above.

[0052] The method implemented when the fairing optimization design procedure is executed can be referred to in various embodiments of the fairing optimization design method of this application, and will not be repeated here.

[0053] It should be noted that the sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0054] The terms "comprising" and "having," and any variations thereof, in the specification, claims, and accompanying drawings of this application are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to such process, method, product, or apparatus. The terms "first," "second," and "third," etc., are used to distinguish different objects, etc., and do not indicate a sequence, nor do they limit "first," "second," and "third" to different types.

[0055] In the description of the embodiments of this application, terms such as "exemplary," "for example," or "for instance" are used to indicate examples, illustrations, or explanations. Any embodiment or design described as "exemplary," "for example," or "for instance" in the embodiments of this application should not be construed as being more preferred or advantageous than other embodiments or designs. Specifically, the use of terms such as "exemplary," "for example," or "for instance" is intended to present the relevant concepts in a concrete manner.

[0056] In the description of the embodiments of this application, unless otherwise stated, " / " means "or". For example, A / B can mean A or B. The "and / or" in the text is merely a description of the relationship between related objects, indicating that there can be three relationships. For example, A and / or B can mean: A exists alone, A and B exist simultaneously, and B exists alone. In addition, in the description of the embodiments of this application, "multiple" means two or more.

[0057] In some processes described in the embodiments of this application, multiple operations or steps are included in a specific order. However, it should be understood that these operations or steps may not be executed in the order they appear in the embodiments of this application, or they may be executed in parallel. The sequence number of the operation is only used to distinguish different operations, and the sequence number itself does not represent any execution order. In addition, these processes may include more or fewer operations, and these operations or steps may be executed sequentially or in parallel, and these operations or steps may be combined.

[0058] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) as described above, and includes several instructions to cause a terminal device to execute the methods described in the various embodiments of this application.

[0059] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A fairing optimization design method, characterized in that, The fairing optimization design method includes: The forward-swept surface shape of the fairing was optimized, and the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions was calculated based on simulation calculation methods. If the theoretical value of the self-separating aerodynamic force is less than the design requirement value of the self-separating aerodynamic force, the forward sweep profile of the fairing is repeatedly optimized until the theoretical value of the self-separating aerodynamic force is greater than or equal to the design requirement value of the self-separating aerodynamic force.

2. The fairing optimization design method as described in claim 1, characterized in that, The optimized design of the fairing's forward-swept surface profile includes: The length of the fairing's forward sweep line was increased.

3. The fairing optimization design method as described in claim 1, characterized in that, The optimized design of the fairing's forward-swept surface profile includes: Increase the forward sweep angle of the fairing.

4. The fairing optimization design method as described in claim 1, characterized in that, The optimized design of the fairing's forward-swept surface profile includes: Increase the curvature of the fairing's outline.

5. The fairing optimization design method as described in claim 1, characterized in that, Before optimizing the forward-swept surface shape of the fairing and calculating the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions based on simulation calculations, the following steps are also included: Based on the separation Mach number and angle of attack of the fairing, the self-separation aerodynamic design requirements of the fairing are determined.

6. The fairing optimization design method as described in claim 5, characterized in that, Before determining the self-separation aerodynamic design requirements of the fairing based on the separation Mach number and angle of attack of the fairing, the following steps are also included: Based on the aircraft's trajectory, speed, altitude, and control capabilities, the separation Mach number and angle of attack of the fairing are determined while meeting design quality and strength requirements.

7. A fairing optimization design device, characterized in that, The fairing optimization design device includes: The fairing optimization module is used to optimize the design of the forward-swept surface shape of the fairing and calculate the theoretical value of the self-separation aerodynamic force of the optimized fairing under separation conditions based on simulation calculation methods. The judgment module is used to repeatedly optimize the design of the forward-swept surface shape of the fairing if the theoretical value of the self-separating aerodynamic force is less than the design requirement value of the self-separating aerodynamic force, until the theoretical value of the self-separating aerodynamic force is greater than or equal to the design requirement value of the self-separating aerodynamic force.

8. The fairing optimization design device as described in claim 7, characterized in that, The fairing optimization module is also used to lengthen the forward sweep line of the fairing.

9. A fairing optimization design device, characterized in that, The fairing optimization design device includes a processor, a memory, and a fairing optimization design program stored in the memory and executable by the processor, wherein when the fairing optimization design program is executed by the processor, it implements the steps of the fairing optimization design method as described in any one of claims 1 to 6.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a fairing optimization design program, wherein when the fairing optimization design program is executed by a processor, it implements the steps of the fairing optimization design method as described in any one of claims 1 to 6.

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