Method and system for determining gravity center range of supersonic aircraft, electronic equipment and medium

Abstract

The invention belongs to the technical field of supersonic aircraft gravity center range determination, and particularly relates to a supersonic aircraft gravity center range determination method and system, electronic equipment and a medium, which comprehensively considers the longitudinal static stability margin and maneuverability of aircraft flight and reasonably determines the gravity center range of a supersonic aircraft at each flight speed. Implementation of the active gravity center control technology can be effectively supported, it is ensured that the aircraft can have the appropriate longitudinal static stability margin within different speed ranges, the flight resistance can be effectively reduced, the flight performance can be improved, fuel is saved, and the cruise range is increased.

Description

Technical Field

[0001] The present application belongs to the technical field of determining the center of gravity range of a supersonic aircraft, and specifically relates to a method, system, electronic equipment, and medium for determining the center of gravity range of a supersonic aircraft. Background Art

[0002] When supersonic aircraft, especially civil aircraft, fly at supersonic speed, the aerodynamic focus will move backward significantly and there will be zero-lift wave drag, which will cause a sudden increase in flight resistance and a significant decrease in the aircraft's lift-to-drag ratio.

[0003] Center of gravity control technology can change the center of gravity position of the aircraft as needed, so that the center of gravity and the aerodynamic focus are reasonably matched, the aircraft's lift resistance is reduced, the flight resistance is weakened, the aircraft's maneuverability is maintained during supersonic flight, the relationship between the aircraft's stability and maneuverability is better coordinated, the aircraft's flight performance is improved, fuel is saved and the cruising range is increased.

[0004] Supersonic aircraft can use active center of gravity control technology to optimize the original design center of gravity during subsonic flight to improve flight performance. During supersonic cruise, the center of gravity position is controlled to move backward as the aerodynamic focus changes, maintaining the optimal static stability margin for cruise.

[0005] In supersonic aircraft, active center of gravity control technology is used to achieve the shift of the aircraft's center of gravity by managing the balanced fuel supply system, mainly including: ① During subsonic flight, each tank group supplies fuel relative to the center of gravity to ensure the aircraft's center of gravity during subsonic flight; ② When the aircraft enters supersonic flight, the balanced fuel in the front tank group is transferred to the rear tank group to provide a balancing torque to reduce cruise resistance; ③ When the aircraft ends supersonic cruise and enters subsonic again, the fuel in the rear tank group is transferred to the front tank group as needed, or to the tank near the center of gravity of the aircraft.

[0006] From the above, it can be seen that the key to adopting active center of gravity control technology is how to appropriately determine the center of gravity range of the aircraft. In view of this, this application is proposed. Summary of the invention

[0007] The purpose of this application is to provide a method, system, electronic equipment, and medium for determining the center of gravity range of a supersonic aircraft, so as to reasonably determine the center of gravity range of the aircraft, support the implementation of active center of gravity control technology, ensure that the aircraft can have an appropriate longitudinal static stability margin within different speed ranges, and improve flight performance.

[0008] The technical solution of this application is:

[0009] On the one hand, a method for determining the center of gravity range of a supersonic aircraft is provided, comprising:

[0010] Calculation steps for the rear limit of the center of gravity for low-speed and subsonic flight: Calculate the rear limit of the center of gravity for low-speed and subsonic flight

[0011] Calculation steps for transonic and supersonic flight center of gravity rear limit: Calculate the transonic and supersonic flight center of gravity rear limit

[0012] Calculation steps for the front limit of the center of gravity at each flight speed: Calculate the front limit of the center of gravity at each flight speed

[0013] Steps for determining the center of gravity range at each flight speed: Comprehensive low-speed and subsonic flight center of gravity rear limit Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

[0014] According to at least one embodiment of the present application, in the above-mentioned method for determining the center of gravity range of a supersonic aircraft, the step of calculating the rear limit of the center of gravity of low-speed and subsonic flight is specifically as follows:

[0015] in,

[0016] It is the aerodynamic focus of the entire aircraft when the aircraft is flying at low speed and subsonic speed;

[0017] is the minimum longitudinal static stability margin.

[0018] According to at least one embodiment of the present application, in the above-mentioned method for determining the range of the center of gravity of a supersonic aircraft, the step of calculating the rear limit of the center of gravity of transonic and supersonic flight is specifically as follows:

[0019]

[0020] in,

[0021] It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0022] It is the aerodynamic focus of the whole aircraft when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0023] is the minimum longitudinal static stability margin.

[0024] According to at least one embodiment of the present application, in the above-mentioned method for determining the center of gravity range of a supersonic aircraft, in the low-speed and subsonic flight center of gravity rear limit calculation step, and in the transonic and supersonic flight center of gravity rear limit calculation step, the minimum longitudinal static stability margin Take 5% MAC.

[0025] According to at least one embodiment of the present application, in the above-mentioned method for determining the center of gravity range of a supersonic aircraft, the step of calculating the front limit of the center of gravity at each flight speed is specifically as follows:

[0026]

[0027] in,

[0028] △ is the range of movement of the aircraft's center of gravity.

[0029] According to at least one embodiment of the present application, in the above-mentioned method for determining the center of gravity range of a supersonic aircraft, in the step of calculating the front limit of the center of gravity at each flight speed, the aircraft center of gravity movement range △ is 3% MAC.

[0030] On the other hand, a supersonic aircraft center of gravity range determination system is provided, comprising:

[0031] The module for calculating the rear limit of the center of gravity for low-speed and subsonic flight is used to calculate the rear limit of the center of gravity for low-speed and subsonic flight.

[0032] Transonic and supersonic flight center of gravity rear limit calculation module, used to calculate transonic and supersonic flight center of gravity rear limit

[0033] The module for calculating the front limit of the center of gravity at each flight speed is used to calculate the front limit of the center of gravity at each flight speed

[0034] The module for determining the center of gravity range at each flight speed is used to integrate the rear limit of the center of gravity for low-speed and subsonic flight Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

[0035] According to at least one embodiment of the present application, in the above-mentioned supersonic aircraft center of gravity range determination system, the low-speed and subsonic flight center of gravity rear limit calculation module calculates the transonic and supersonic flight center of gravity rear limit Specifically:

[0036] in,

[0037] It is the aerodynamic focus of the entire aircraft when the aircraft is flying at low speed and subsonic speed;

[0038] is the minimum longitudinal static stability margin.

[0039] According to at least one embodiment of the present application, in the above-mentioned supersonic aircraft center of gravity range determination system, in the transonic and supersonic flight center of gravity rear limit calculation module, the transonic and supersonic flight center of gravity rear limit is calculated. Specifically:

[0040]

[0041] in,

[0042] It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0043] It is the aerodynamic focus of the whole aircraft when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0044] is the minimum longitudinal static stability margin.

[0045] According to at least one embodiment of the present application, in the above-mentioned supersonic aircraft center of gravity range determination system, in the low-speed and subsonic flight center of gravity rear limit calculation module, and the transonic and supersonic flight center of gravity rear limit calculation module, the minimum longitudinal static stability margin Take 5% MAC.

[0046] According to at least one embodiment of the present application, in the above-mentioned supersonic aircraft center of gravity range determination system, in each flight speed center of gravity front limit calculation module, the center of gravity front limit of each flight speed is calculated. Specifically:

[0047]

[0048] in,

[0049] △ is the range of movement of the aircraft's center of gravity.

[0050] According to at least one embodiment of the present application, in the above-mentioned supersonic aircraft center of gravity range determination system, in each flight speed center of gravity front limit calculation module, the aircraft center of gravity movement range △ is 3% MAC.

[0051] Another aspect provides an electronic device, comprising:

[0052] processor;

[0053] A memory stores a computer program, wherein the computer program is configured to implement any of the above-mentioned methods for determining the center of gravity range of a supersonic aircraft when executed by the processor.

[0054] On the other hand, an electronic medium is provided, which is a computer-readable storage medium. The computer-readable storage medium stores a computer program. When the computer program is executed by a processor, it can implement any of the above-mentioned methods for determining the center of gravity range of a supersonic aircraft.

[0055] This application has at least the following beneficial technical effects:

[0056] Provided are a method, system, electronic equipment, and medium for determining the center of gravity range of a supersonic aircraft, which comprehensively consider the longitudinal static stability margin and maneuverability of the aircraft flight, reasonably determine the center of gravity range of the supersonic aircraft at various flight speeds, effectively support the implementation of active center of gravity control technology, ensure that the aircraft has a suitable longitudinal static stability margin within different speed ranges, and effectively reduce flight resistance, improve flight performance, save fuel, and increase cruising range. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] Figure 1 is a schematic diagram of a method for determining a range of a supersonic aircraft center of gravity provided by an embodiment of the present application;

[0058] Figure 2 This is a schematic diagram of adjusting the range of the center of gravity of a supersonic aircraft as the speed changes, provided in an embodiment of the present application;

[0059] Figure 3 It is a schematic diagram of a supersonic aircraft center of gravity range determination system provided in an embodiment of the present application.

[0060] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0061] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0062] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0063] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0064] With the development of aircraft design, the design concept of relaxing static stability has been proposed. The so-called relaxation of static stability means relaxing the requirements for the static stability of the aircraft, designing the static stability of the aircraft to be less than the conventional requirement value, that is, the focus is close to the center of gravity. Such an aircraft is not stable enough when disturbed or maneuvering, so it must be compensated by automatic control methods. The fly-by-wire flight control system provides the possibility of relaxing static stability.

[0065] The functions of relaxing static stability in fighters and transport aircraft are not exactly the same. Relaxing static stability was first proposed for fighters because it can greatly improve the maneuverability of fighters. For transport aircraft, after relaxing static stability, the horizontal tail changes from negative skewness to positive skewness, and the total lift is the sum of the wing lift and the horizontal tail lift. The wing lift is no longer consumed in balancing the tail lift. For the same lift coefficient, the angle of attack after relaxing static stability is smaller, which will reduce lift-induced drag. At the same time, after relaxing static stability, the tail downward load required for trimming is smaller than that of ordinary aircraft, which greatly reduces the size and weight of the tail, and reduces the weight and drag of the aircraft. Relaxing static stability will improve the lift-to-drag ratio of transport aircraft, reduce drag and thus improve fuel efficiency, while reducing aircraft weight, so that the aircraft can obtain performance that is difficult to achieve or cannot be achieved at all according to conventional design technology. Relaxing static stability can also reduce the constraints on the overall layout of the aircraft, making it possible to optimize the aircraft layout design.

[0066] Taking into account the improvement of aircraft layout and performance brought by relaxed static stability, supersonic aircraft adopts relaxed static stability technology based on fly-by-wire. Taking into account the reliability of the flight control system and the high safety requirements of modern aircraft, supersonic aircraft still have a certain static stability margin after relaxing static stability, ensuring that the main aircraft at least meets the flight quality requirements of Level 2. Based on experience, it is proposed that the minimum static stability margin of supersonic aircraft is 5% MAC. Although the focus of supersonic aircraft moves backward significantly after supersonic speed, the active center of gravity control system realizes the center of gravity position moving backward with the change of focus, ensuring that the minimum static stability margin of the aircraft's rear center of gravity is 5% MAC.

[0067] Based on the above, the present application provides a method for determining the center of gravity range of a supersonic aircraft. Figure 1 shown.

[0068] Calculation steps for the rear limit of the center of gravity for low-speed and subsonic flight: Calculate the rear limit of the center of gravity for low-speed and subsonic flight

[0069] When the aircraft is flying at low speed or subsonic speed, the aerodynamic focus of the whole aircraft is Basically unchanged, based on this, while ensuring the minimum longitudinal static stability margin Under the condition of

[0070]

[0071] in,

[0072] It is the aerodynamic focus of the entire aircraft when it is flying at low speed and subsonic speed.

[0073] Minimum longitudinal static stability margin 5% MAC is acceptable.

[0074] Calculation steps for transonic and supersonic flight center of gravity rear limit: Calculate the transonic and supersonic flight center of gravity rear limit

[0075] When the aircraft is flying at transonic or supersonic speed, the aerodynamic focus of the entire aircraft As the flight speed V increases, it will move backward significantly. Based on this, while ensuring the minimum longitudinal static stability margin Under the condition of , the rear limit of the center of gravity at each speed of transonic and supersonic flight is calculated.

[0076]

[0077] in,

[0078] It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0079] It is the aerodynamic focus of the entire aircraft when the flight speed is V when the aircraft is flying at transonic or supersonic speed.

[0080] Calculation steps for the front limit of the center of gravity at each flight speed: Calculate the front limit of the center of gravity at each flight speed

[0081] The aircraft uses fuel center of gravity active control technology. Considering the aircraft center of gravity movement range is △, the center of gravity front limit of each flight speed is calculated.

[0082]

[0083] The range of movement of the aircraft center of gravity is △ 3% MAC.

[0084] Steps for determining the center of gravity range at each flight speed: Comprehensive low-speed and subsonic flight center of gravity rear limit Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

[0085] In a specific example, the method for determining the center of gravity range of a supersonic aircraft disclosed in the above embodiment is implemented as follows:

[0086] S1. The aerodynamic focus of the entire aircraft when it is flying at low speed or subsonic high speed. is 50% MAC. This focus remains unchanged when M≤0.8. Thus, under the condition of ensuring the minimum longitudinal static stability margin of 5% MAC, the rear limit of the center of gravity for low-speed and subsonic flight is calculated.

[0087] S2. Aerodynamic focus of the entire aircraft when the aircraft is flying at transonic and supersonic speeds The aerodynamic focus of the whole aircraft will move backward significantly with the flight speed. When M=0.95, the aerodynamic focus When MAC is 53% and M=1.1, the aerodynamic focus When MAC is 56% and M=1.6, the aerodynamic focus When MAC is 58% and M=1.8, the aerodynamic focus is 57% MAC. Under the condition of ensuring the minimum longitudinal static stability margin value of 5% MAC, it is calculated that when M = 0.95, the rear limit of the center of gravity is When MAC is 48% and M=1.1, the rear limit of the center of gravity is When MAC is 51% and M is 1.6, the rear limit of the center of gravity is When MAC is 53% and M is 1.8, the rear limit of the center of gravity is It is 52% MAC.

[0088] S3. The aircraft uses fuel center of gravity active control technology. Considering that the aircraft center of gravity movement range is 3% MAC, it is calculated that when M≤0.8, the center of gravity front limit When MAC is 42% and M is 0.95, the front limit of the center of gravity is When MAC is 45% and M is 1.1, the front limit of the center of gravity is When MAC is 48% and M is 1.6, the front limit of the center of gravity is When MAC is 50% and M is 1.8, the front limit of the center of gravity is It is 49% MAC.

[0089] S4, comprehensive low-speed and subsonic flight center of gravity rear limit Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed The center of gravity range of each flight speed is obtained, such as Figure 2 shown.

[0090] The method for determining the center of gravity range of a supersonic aircraft disclosed in the above embodiment comprehensively considers the longitudinal static stability margin and maneuverability of the aircraft flight, and reasonably determines the center of gravity range of the supersonic aircraft at various flight speeds. It can effectively support the implementation of active center of gravity control technology, ensure that the aircraft can have a suitable longitudinal static stability margin within different speed ranges, and effectively reduce flight resistance, improve flight performance, save fuel and increase cruising range.

[0091] On the other hand, the present application provides a system for determining the center of gravity range of a supersonic aircraft, such as Figure 3 shown.

[0092] The module for calculating the rear limit of the center of gravity for low-speed and subsonic flight is used to calculate the rear limit of the center of gravity for low-speed and subsonic flight.

[0093] When the aircraft is flying at low speed or subsonic speed, the aerodynamic focus of the whole aircraft is Basically unchanged, based on this, while ensuring the minimum longitudinal static stability margin Under the condition of

[0094]

[0095] in,

[0096] It is the aerodynamic focus of the entire aircraft when it is flying at low speed and subsonic speed.

[0097] Minimum longitudinal static stability margin 5% MAC is acceptable.

[0098] Transonic and supersonic flight center of gravity rear limit calculation module, used to calculate transonic and supersonic flight center of gravity rear limit

[0099] When the aircraft is flying at transonic or supersonic speed, the aerodynamic focus of the entire aircraft As the flight speed V increases, it will move backward significantly. Based on this, while ensuring the minimum longitudinal static stability margin Under the condition of , the rear limit of the center of gravity at each speed of transonic and supersonic flight is calculated.

[0100]

[0101] in,

[0102] It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V;

[0103] It is the aerodynamic focus of the entire aircraft when the flight speed is V when the aircraft is flying at transonic or supersonic speed.

[0104] The module for calculating the front limit of the center of gravity at each flight speed is used to calculate the front limit of the center of gravity at each flight speed

[0105] The aircraft uses fuel center of gravity active control technology. Considering the aircraft center of gravity movement range is △, the center of gravity front limit of each flight speed is calculated.

[0106]

[0107] The range of movement of the aircraft center of gravity is △ 3% MAC.

[0108] The module for determining the center of gravity range at each flight speed is used to integrate the rear limit of the center of gravity for low-speed and subsonic flight Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

[0109] For the supersonic aircraft center of gravity range determination system disclosed in the above embodiment, since it corresponds to the supersonic aircraft center of gravity range determination method disclosed in the above embodiment, the description is relatively simple. For specific related matters, please refer to the relevant description of the supersonic aircraft center of gravity range determination method part. Its technical effects can also refer to the technical effects of the relevant part of the supersonic aircraft center of gravity range determination method, which will not be repeated here.

[0110] In addition, those skilled in the art should also be able to realize that the various modules and units of the supersonic aircraft center of gravity range determination system disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose to use different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0111] Another aspect provides an electronic device, comprising:

[0112] processor;

[0113] A memory stores a computer program, wherein the computer program is configured to implement any of the above-mentioned methods for determining the center of gravity range of a supersonic aircraft when executed by the processor.

[0114] In some optional embodiments, the processor can be a central processing unit CPU or other form of processing unit with data processing capability and / or instruction execution capability, can be a general-purpose processor or a special-purpose processor, and can control other components in the compensation electronic device to perform the desired functions.

[0115] In some optional embodiments, the memory may include various forms of computer-readable storage media, such as volatile memory and / or non-volatile memory, the volatile memory may be a random access memory RAM and / or a cache memory cache, and the non-volatile memory may be a read-only memory ROM, a hard disk, a flash memory, etc. The memory may store a computer program, and the processor runs the computer program to implement the functions in the embodiments of the present application and / or other desired functions. In addition, various application programs and various data may also be stored.

[0116] In some optional embodiments, the processor and the memory may be connected via a bus system, which may be a serial or parallel communication bus or the like.

[0117] It should be noted that, for the sake of clarity and brevity, not all components of the electronic device are shown in the above embodiments. To implement the necessary functions of the electronic device, technicians in the field can provide and set other components not shown according to specific needs.

[0118] For the electronic device disclosed in the above embodiment, since its processor can implement any of the above-mentioned methods for determining the center of gravity range of a supersonic aircraft when executing the computer program stored in its memory, its technical effects can be correspondingly referred to the technical effects of the above-mentioned method for determining the center of gravity range of a supersonic aircraft, and will not be repeated here.

[0119] On the other hand, an electronic medium is provided, which is a computer-readable storage medium. The computer-readable storage medium stores a computer program. When the computer program is executed by a processor, it can implement any of the above-mentioned methods for determining the center of gravity range of a supersonic aircraft.

[0120] In some optional embodiments, the computer-readable storage medium may include a memory card of a smartphone, a storage component of a tablet computer, a hard disk of a personal computer, a random access memory RAM, a read-only memory ROM, an erasable programmable read-only memory EPROM, a portable compact disk read-only memory CD-ROM, flash memory, or any combination of the above storage media, or other applicable storage media.

[0121] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for determining the center of gravity range of a supersonic aircraft, characterized in that: include: Calculation steps for the rear limit of the center of gravity for low-speed and subsonic flight: Calculate the rear limit of the center of gravity for low-speed and subsonic flight Calculation steps for transonic and supersonic flight center of gravity rear limit: Calculate the transonic and supersonic flight center of gravity rear limit Calculation steps for the front limit of the center of gravity at each flight speed: Calculate the front limit of the center of gravity at each flight speed Steps for determining the center of gravity range at each flight speed: Comprehensive low-speed and subsonic flight center of gravity rear limit Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

2. The method for determining the center of gravity range of a supersonic aircraft according to claim 1, characterized in that: The calculation steps for the rear center of gravity limit of low-speed and subsonic flight are as follows: in, It is the aerodynamic focus of the entire aircraft when the aircraft is flying at low speed and subsonic speed; is the minimum longitudinal static stability margin.

3. The method for determining the center of gravity range of a supersonic aircraft according to claim 2, characterized in that: The calculation steps for the rear center of gravity limit of transonic and supersonic flight are as follows: in, It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V; It is the aerodynamic focus of the whole aircraft when the aircraft is flying at transonic or supersonic speed and the flight speed is V; is the minimum longitudinal static stability margin.

4. The method for determining the center of gravity range of a supersonic aircraft according to claim 3, characterized in that: Minimum longitudinal static stability margin in the low-speed and subsonic flight center of gravity rear limit calculation step, transonic and supersonic flight center of gravity rear limit calculation step Take 5% MAC.

5. The method for determining the center of gravity range of a supersonic aircraft according to claim 4, characterized in that: The calculation steps for the front limit of the center of gravity at each flight speed are as follows: in, △ is the range of movement of the aircraft's center of gravity.

6. The method for determining the center of gravity range of a supersonic aircraft according to claim 5, characterized in that: In the calculation step of the forward limit of the center of gravity at each flight speed, the aircraft center of gravity movement range △ is taken as 3% MAC.

7. A supersonic aircraft center of gravity range determination system, characterized in that: include: The module for calculating the rear limit of the center of gravity for low-speed and subsonic flight is used to calculate the rear limit of the center of gravity for low-speed and subsonic flight. Transonic and supersonic flight center of gravity rear limit calculation module, used to calculate transonic and supersonic flight center of gravity rear limit The module for calculating the front limit of the center of gravity at each flight speed is used to calculate the front limit of the center of gravity at each flight speed The module for determining the center of gravity range at each flight speed is used to integrate the rear limit of the center of gravity for low-speed and subsonic flight Transonic and supersonic flight center of gravity rear limit And the front limit of the center of gravity at each flight speed Obtain the center of gravity range for each flight speed.

8. The supersonic aircraft center of gravity range determination system according to claim 7, characterized in that: In the low-speed and subsonic flight center of gravity rear limit calculation module, the transonic and supersonic flight center of gravity rear limit is calculated Specifically: in, It is the aerodynamic focus of the entire aircraft when the aircraft is flying at low speed and subsonic speed; is the minimum longitudinal static stability margin.

9. The supersonic aircraft center of gravity range determination system according to claim 8, characterized in that: In the transonic and supersonic flight center of gravity rear limit calculation module, the transonic and supersonic flight center of gravity rear limit is calculated. Specifically: in, It is the rear limit of the center of gravity when the aircraft is flying at transonic or supersonic speed and the flight speed is V; It is the aerodynamic focus of the whole aircraft when the aircraft is flying at transonic or supersonic speed and the flight speed is V; is the minimum longitudinal static stability margin.

10. The supersonic aircraft center of gravity range determination system according to claim 9, characterized in that: Minimum longitudinal static stability margin in the low-speed and subsonic flight center of gravity rear limit calculation module and the transonic and supersonic flight center of gravity rear limit calculation module Take 5% MAC.

11. The supersonic aircraft center of gravity range determination system according to claim 10, characterized in that: In the calculation module for the front limit of the center of gravity of each flight speed, the front limit of the center of gravity of each flight speed is calculated Specifically: in, △ is the range of movement of the aircraft's center of gravity.

12. The supersonic aircraft center of gravity range determination system according to claim 11, characterized in that: In the center of gravity front limit calculation module for each flight speed, the aircraft center of gravity movement range △ is taken as 3% MAC.

13. An electronic device, characterized in that: include: processor; A memory storing a computer program, wherein the computer program is configured to implement the method for determining the center of gravity range of a supersonic aircraft as claimed in claim 1 when executed by the processor.

14. An electronic medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method for determining the center of gravity range of a supersonic aircraft according to claim 1 can be implemented.

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