An aircraft flight control system and method

Abstract

The present application discloses a flight control system and method for an aircraft. The flight control system includes: an angle-of-attack detection device for obtaining the angle of attack α of the aircraft; and a calculation device that internally stores the stall warning angle of attack αsw. The calculation device is configured to compare the angle of attack α of the aircraft with the stall warning angle of attack αsw, and determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the difference between the angle of attack α of the aircraft and the stall warning angle of attack αsw, thereby solving the problem of inconsistent display in the low-speed band of the display devices on both sides of the aircraft and ensuring the problem of unsafe indication caused by a single error.

Description

Technical Field

[0001] This application relates to the technical field of flight control systems, and particularly to a flight control system and method for an aircraft. Background Art

[0002] Low-speed band indications are usually provided on the Primary Flight Display (PFD) of civil aircraft, including the minimum maneuvering speed Vman and stall warning speed Vsw indications of the aircraft, used to remind the flight crew of the speed margin of the aircraft from the stall speed Vs. The aerodynamic stall state of the aircraft is related to the flaps, slats, landing gear, engine thrust, etc. of the aircraft. The characteristic angle of attack parameter in each usage configuration can be used to characterize the aircraft approaching stall and reaching the stall state. The value of this characteristic angle of attack parameter can be obtained through flight tests. To ensure safety, Vman and Vsw can be calculated based on the angle of attack. However, in actual engineering, there are certain differences in the angle of attack data obtained by the angle of attack sensors, resulting in inconsistent low-speed band indications on the PFDs on both sides of the cockpit. Especially when the differences are large due to sensor errors, it causes trouble for pilots' operations. Summary of the Invention

[0003] The purpose of the present invention is to provide a flight control system and method for an aircraft to solve the technical problem that there are certain errors in the angle of attack data obtained by the angle of attack sensors, resulting in inconsistent low-speed band indications on the PFDs on both sides of the cockpit.

[0004] To achieve the above purpose, the present invention provides a flight control system for an aircraft, including: an angle of attack detection device for obtaining the angle of attack α of the aircraft; and a calculation device with the stall warning angle of attack αsw stored therein. The calculation device is configured to compare the angle of attack α of the aircraft with the stall warning angle of attack αsw, and determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the difference between the angle of attack α of the aircraft and the stall warning angle of attack αsw.

[0005] Further, the flight control system further includes: an airspeed detection device for obtaining the calibrated airspeed Vcas; the calculation device also stores the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2 therein; when the angle of attack α of the aircraft is less than or equal to the stall warning angle of attack αsw, the following is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman,

[0006]

[0007]

[0008] Furthermore, the flight control system further includes: an airspeed detection device for obtaining the flight airspeed Vcas; the internal of the calculation device further stores the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2; when the aircraft angle of attack α is greater than the stall warning angle of attack αsw, compare the aircraft angle of attack α with the stall angle of attack αsi, and determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the difference between the aircraft angle of attack α and the stall angle of attack αsi.

[0009] Furthermore, when the aircraft angle of attack α is less than or equal to the stall angle of attack αsi, the following formulas are used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman.

[0010]

[0011]

[0012] Furthermore, when the aircraft angle of attack α is greater than the stall angle of attack αsi, set the aircraft angle of attack α equal to the stall angle of attack αsi, and use the following formulas to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman.

[0013]

[0014]

[0015] Furthermore, the flight control system further includes: a comparison device for receiving the stall warning speed Vsw and the minimum maneuvering speed Vman, the comparison device compares the stall warning speed Vsw with a first threshold value, and determines the output value of the stall warning speed Vsw according to the difference between the stall warning speed Vsw and the first threshold value; the comparison device compares the minimum maneuvering speed Vman with a second threshold value, and determines the output value of the minimum maneuvering speed Vman according to the difference between the minimum maneuvering speed Vman and the second threshold value.

[0016] Furthermore, there are two angle-of-attack detection devices, namely a first angle-of-attack detection device and a second angle-of-attack detection device. The first angle-of-attack detection device is arranged on the first side of the aircraft, and the second angle-of-attack detection device is arranged on the second side of the aircraft. Each angle-of-attack detection device is used to obtain the angle of attack α of the aircraft on the corresponding side of the angle-of-attack detection device. There are two airspeed detection devices, namely a first airspeed detection device and a second airspeed detection device. The first airspeed detection device is arranged on the first side of the aircraft, and the second airspeed detection device is arranged on the second side of the aircraft. Each airspeed detection device is used to obtain the calibrated airspeed Vcas of the flight on the corresponding side of the airspeed detection device. There are two calculation devices, namely a first calculation device and a second calculation device. The first calculation device is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the first side of the aircraft, and the second calculation device is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the second side of the aircraft. There are two comparison devices, namely a first comparison device and a second comparison device. The first comparison device is used to compare the difference between the stall warning speed Vsw on the first side of the aircraft and the first threshold value and the difference between the minimum maneuvering speed Vman and the second threshold value. The second comparison device is used to compare the difference between the stall warning speed Vsw on the second side of the aircraft and the first threshold value and the difference between the minimum maneuvering speed Vman and the second threshold value.

[0017] Furthermore, when the stall warning speed Vsw on the first side of the aircraft output by the first calculation device is greater than the first threshold value, the stall warning speed Vsw on the second side of the aircraft output by the second calculation device is greater than the first threshold value, and the difference between the stall warning speed Vsw on the first side of the aircraft output by the first calculation device and the stall warning speed Vsw on the second side of the aircraft output by the second calculation device is less than or equal to the first voting threshold TBD1, the first comparison device and / or the second comparison device output the average value between the stall warning speed Vsw on the first side of the aircraft and the stall warning speed Vsw on the second side of the aircraft.

[0018] Furthermore, when the stall warning speed Vsw on the first side of the aircraft output by the first calculation device is less than or equal to the first threshold value, and / or the stall warning speed Vsw on the second side of the aircraft output by the second calculation device is less than or equal to the first threshold value, the first comparison device outputs the stall warning speed Vsw on the first side of the aircraft as zero, and / or the second comparison device outputs the stall warning speed Vsw on the second side of the aircraft as zero.

[0019] Further, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device is greater than the second threshold, the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device is greater than the second threshold, and the difference between the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device and the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device is less than or equal to the second voting threshold TBD2, the first comparison device and / or the second comparison device output the average value between the minimum maneuvering speed Vman on the first side of the aircraft and the minimum maneuvering speed Vman on the second side of the aircraft.

[0020] Further, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device is less than or equal to the second threshold, and / or the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device is less than or equal to the second threshold, the first comparison device outputs the minimum maneuvering speed Vman on the first side of the aircraft as zero, and / or the second comparison device outputs the minimum maneuvering speed Vman on the second side of the aircraft as zero.

[0021] To achieve the above object, the present invention further provides a flight control method for an aircraft, including the following steps: obtaining the angle of attack α of the aircraft; storing the stall warning angle of attack αsw, comparing the angle of attack α of the aircraft with the stall warning angle of attack αsw, and determining the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the difference between the angle of attack α of the aircraft and the stall warning angle of attack αsw.

[0022] Further, in the step of obtaining the angle of attack α of the aircraft, it further includes: obtaining the calibrated airspeed Vcas; in the step of storing the stall warning angle of attack αsw, it further includes: storing the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2; when the angle of attack α of the aircraft is less than or equal to the stall warning angle of attack αsw, the following formulas are used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman

[0023]

[0024]

[0025] Further, in the step of obtaining the aircraft angle of attack α, it further includes: obtaining the calibrated airspeed Vcas; in the step of storing the stall warning angle of attack αsw, it further includes: the internal of the computing device also stores the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2; when the aircraft angle of attack α is greater than the stall warning angle of attack αsw, compare the aircraft angle of attack α with the stall angle of attack αsi, and based on the difference between the aircraft angle of attack α and the stall angle of attack αsi, to determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft.

[0026] Further, when the aircraft angle of attack α is less than or equal to the stall angle of attack αsi, the following formula is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman.

[0027]

[0028]

[0029] Further, when the aircraft angle of attack α is greater than the stall angle of attack αsi, set the aircraft angle of attack α equal to the stall angle of attack αsi, and use the following formula to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman.

[0030]

[0031]

[0032] Further, after the step of storing the stall warning angle of attack αsw, it further includes: receiving the stall warning speed Vsw and the minimum maneuvering speed Vman, the comparison device compares the stall warning speed Vsw with a first threshold, and based on the difference between the stall warning speed Vsw and the first threshold, to determine the output value of the stall warning speed Vsw; the comparison device compares the minimum maneuvering speed Vman with a second threshold, and based on the difference between the minimum maneuvering speed Vman and the second threshold, to determine the output value of the minimum maneuvering speed Vman.

[0033] The technical effect of the present invention is to provide a flight control system and method for an aircraft. It adopts a safe and reliable architecture design and two sets of independent low-speed band indicating devices, avoiding the simultaneous error of the display devices on both sides caused by a single failure of the computing device or the comparison device. The angle of attack is the most direct parameter reflecting that the aircraft is approaching or reaching the stall state. The computing device of the flight control system can obtain the characteristic zero-lift angle of attack αzl, stall warning angle of attack αsw, and stall angle of attack αs of the aircraft under different configurations through the stored database, and calculate the minimum maneuvering speed Vman and stall warning speed Vsw adapted to various configurations of the actual aircraft based on these characteristic angles of attack, so as to provide a low-speed band indication for the safety of the aircraft. The stall warning speed Vsw and minimum maneuvering speed Vman calculated based on Formulas 1-4 continuously increase as the angle of attack of the aircraft continues to increase, thus providing a low-speed indication to the pilot that the speed margin of the aircraft from stalling is decreasing. By adjusting K1, K2, and N1 in Formulas 1-4, the stall warning speed Vsw and minimum maneuvering speed Vman with different speed margins can be provided according to the characteristics of the aircraft itself. The stall warning speed Vsw and minimum maneuvering speed Vman obtained through the comparison device and its comparison and voting method can solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or airspeed detection device, and the design of the voting thresholds TBD1 and TBD2 can solve the problem that the comparison device outputs unsafe and incorrect stall warning speed Vsw and minimum maneuvering speed Vman due to the error of the detection device itself, which not only solves the problem of inconsistent low-speed band display of the display devices on both sides of the aircraft, but also ensures the problem of unsafe indication caused by a single error. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The following will combine the drawings and describe the specific embodiments of the present application in detail, making the technical solutions and other beneficial effects of the present application obvious.

[0035] Figure 1 It is a functional diagram of the flight control system provided by an embodiment of the present application.

[0036] Figure 2 It is a flowchart of the flight control method provided by an embodiment of the present application.

[0037] Figure 3 It is a flowchart of calculating the stall warning speed Vsw and the minimum maneuvering speed Vman provided by an embodiment of the present application.

[0038] Figure 4 It is a flowchart of outputting the stall warning speed Vsw provided by an embodiment of the present application.

[0039] Figure 5 It is a flowchart of outputting the minimum maneuvering speed Vman provided by an embodiment of the present application.

[0040] The identification of the components in the attached drawings is as follows:

[0041] 11. First angle-of-attack detection device; 12. Second angle-of-attack detection device;

[0042] 21. First airspeed detection device; 22. Second airspeed detection device;

[0043] 31. First calculation device; 32. Second calculation device;

[0044] 41. First comparison device; 42. Second comparison device;

[0045] 51. First display device; 52. Second display device. Detailed implementation manners

[0046] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present application.

[0047] In the description of the present application, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more, unless otherwise specifically defined.

[0048] This embodiment provides a flight control system for an aircraft, which includes an angle-of-attack detection device, a calculation device, an airspeed detection device, a comparison device, and a display device.

[0049] The angle-of-attack detection device is used to obtain the angle of attack α of the aircraft. Among them, the angle-of-attack detection device can be implemented using an angle-of-attack sensor.

[0050] The calculation device internally stores the stall warning angle of attack αsw, stores the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2. The calculation device is used to compare the angle of attack α of the aircraft with the stall warning angle of attack αsw, and determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the difference between the angle of attack α of the aircraft and the stall warning angle of attack αsw.

[0051] An airspeed detection device, which is used to obtain the flight calibrated airspeed Vcas. Among them, the airspeed detection device can adopt an air data system based on the total and static pressure measurement method.

[0052] When the angle of attack α of the aircraft is less than or equal to the stall warning angle of attack αsw, the stall warning speed Vsw and the minimum maneuvering speed Vman are calculated using Formula 1 and Formula 2 respectively.

[0053] Formula 1:

[0054] Formula 2:

[0055] When the angle of attack α of the aircraft is greater than the stall warning angle of attack αsw, the angle of attack α of the aircraft is compared with the stall angle of attack αsi, and based on the difference between the angle of attack α of the aircraft and the stall angle of attack αsi, the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft are determined.

[0056] Specifically, when the angle of attack α of the aircraft is less than or equal to the stall angle of attack αsi, the stall warning speed Vsw and the minimum maneuvering speed Vman are calculated using Formula 3 and Formula 4.

[0057] Formula 3:

[0058] Formula 4:

[0059] When the angle of attack α of the aircraft is greater than the stall angle of attack αsi, the angle of attack α of the aircraft is set equal to the stall angle of attack αsi, and the stall warning speed Vsw and the minimum maneuvering speed Vman are calculated using the above Formula 3 and Formula 4.

[0060] A comparison device, which is used to receive the stall warning speed Vsw and the minimum maneuvering speed Vman. The comparison device compares the stall warning speed Vsw with a first threshold, and based on the difference between the stall warning speed Vsw and the first threshold, determines the output value of the stall warning speed Vsw; the comparison device compares the minimum maneuvering speed Vman with a second threshold, and based on the difference between the minimum maneuvering speed Vman and the second threshold, determines the output value of the minimum maneuvering speed Vman. The output value here can be the average value or reset value of the stall warning speeds Vsw on both sides of the aircraft, the average value or reset value of the minimum maneuvering speeds Vman on both sides of the aircraft, where the reset value is preferably 0. Of course, those skilled in the art can also perform resetting according to actual needs.

[0061] In this embodiment, both the first threshold and the second threshold can be set to 0. Of course, those skilled in the art can set the first threshold and the second threshold respectively according to actual requirements. Moreover, when a fault occurs on one side of the aircraft, the average value or reset value of the stall warning speed Vsw and the average value or reset value of the minimum maneuvering speed Vman of the aircraft can be determined through the side without a fault.

[0062] It should be noted that the computing device, the comparison device, and the display device can be completely independent computers, or can be arbitrarily combined to form one or two computers. For example, the computing device, the comparison device, and the display device can form a multi-functional display integrating computing and display.

[0063] As Figure 1 shown, there are two angle-of-attack detection devices, namely a first angle-of-attack detection device 11 and a second angle-of-attack detection device 12. The first angle-of-attack detection device 11 is arranged on the first side of the aircraft, and the second angle-of-attack detection device 12 is arranged on the second side of the aircraft. Each angle-of-attack detection device is used to obtain the angle of attack α of the aircraft on the side corresponding to the angle-of-attack detection device. There are two airspeed detection devices, namely a first airspeed detection device 21 and a second airspeed detection device 22. The first airspeed detection device 21 is arranged on the first side of the aircraft, and the second airspeed detection device 22 is arranged on the second side of the aircraft. Each airspeed detection device is used to obtain the calibrated airspeed Vcas of the flight on the side corresponding to the airspeed detection device. There are two computing devices, namely a first computing device 31 and a second computing device 32. The first computing device 31 is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the first side of the aircraft, and the second computing device 32 is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the second side of the aircraft. There are two comparison devices, namely a first comparison device 41 and a second comparison device 42. The first comparison device 41 is used to compare the difference between the stall warning speed Vsw on the first side of the aircraft and the first threshold and the difference between the minimum maneuvering speed Vman and the second threshold, and the second comparison device 42 is used to compare the difference between the stall warning speed Vsw on the second side of the aircraft and the first threshold and the difference between the minimum maneuvering speed Vman and the second threshold. There are two display devices, namely a first display device 51 and a second display device 52. The first display device 51 and the second display device 52 are used to display the stall warning speed Vsw and the minimum maneuvering speed Vman on their respective sides of the aircraft.

[0064] In one embodiment, when the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 is greater than the first threshold, the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is greater than the first threshold, and the difference between the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 and the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first voting threshold TBD1, the first comparison device 41 outputs the average value between the stall warning speed Vsw of the first side of the aircraft and the stall warning speed Vsw of the second side of the aircraft, and / or the second comparison device 42 also outputs the average value between the stall warning speed Vsw of the first side of the aircraft and the stall warning speed Vsw of the second side of the aircraft. During the normal operation of the aircraft, the first display device 51 and the second display device 52 respectively display the stall warning speed Vsw output by the comparison device on their respective sides and the average value between the stall warning speeds Vsw on both sides of the aircraft, that is, the first display device 51 displays the stall warning speed Vsw output by the first comparison device 41 and the average value between the stall warning speeds Vsw on both sides of the aircraft, and the second display device 52 displays the stall warning speed Vsw output by the second comparison device 42 and the average value between the stall warning speeds Vsw on both sides of the aircraft. When a fault occurs during the normal operation of the aircraft, the pilot can determine which side of the aircraft has a fault based on the data respectively displayed by the two display devices, that is, the stall warning speed Vsw and the average value between the stall warning speeds Vsw on both sides of the aircraft, so as to quickly solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or the airspeed detection device.

[0065] In one embodiment, when the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 is less than or equal to the first threshold, and / or the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first threshold, the first comparison device 41 resets the stall warning speed Vsw of the first side of the aircraft to zero and outputs it, and / or the second comparison device 42 resets the stall warning speed Vsw of the second side of the aircraft to zero and outputs it.

[0066] Specifically, when the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 is less than or equal to the first threshold, or the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first threshold, the first comparison device 41 resets the stall warning speed Vsw of the first side of the aircraft to zero and outputs it, and the second comparison device 42 resets the stall warning speed Vsw of the second side of the aircraft to zero and outputs it. Of course, when the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 is less than or equal to the first threshold, and the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first threshold, the first comparison device 41 will reset the stall warning speed Vsw of the first side of the aircraft to zero and output it, and the second comparison device 42 will reset the stall warning speed Vsw of the second side of the aircraft to zero and output it. Simply put, when a failure occurs during the normal operation of the aircraft, if the stall warning speed Vsw output by the first computing device 31 or the second computing device 32 or both computing devices is less than or equal to the first threshold, the two comparison devices respectively reset the stall warning speed Vsw of their respective sides and then output it, so as to effectively solve the problem that the comparison device outputs an unsafe and incorrect stall warning speed Vsw due to an error in the detection device itself, thereby improving the safety performance of the aircraft. Of course, if a failure occurs on one side of the aircraft, causing the first comparison device 41 or the second comparison device 42 to malfunction, for example, after the first comparison device 41 and the second comparison device 42 respectively reset the stall warning speed Vsw of their respective sides, the data displayed by the display devices on both sides of the aircraft are inconsistent. At this time, the pilot can also judge which side of the aircraft has a failure from the data displayed by the two display devices, so as to quickly repair the aircraft.

[0067] It should be noted that the first display device 51 and the second display device 52 can be used to display the stall warning speed Vsw output by the comparison device on their respective sides and the information that the stall warning speed Vsw on both sides of the aircraft is zero. For example, the first display device 51 displays the stall warning speed Vsw output by the first comparison device 41 and the information that the stall warning speed Vsw is zero, and the second display device 52 displays the stall warning speed Vsw output by the second comparison device 42 and the information that the stall warning speed Vsw is zero.

[0068] In one embodiment, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 is greater than the second threshold, the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is greater than the second threshold, and the difference between the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 and the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second voting threshold TBD2, the first comparison device 41 outputs the average value between the minimum maneuvering speed Vman on the first side of the aircraft and the minimum maneuvering speed Vman on the second side of the aircraft, and / or the second comparison device 42 outputs the average value between the minimum maneuvering speed Vman on the first side of the aircraft and the minimum maneuvering speed Vman on the second side of the aircraft. During the normal operation of the aircraft, the first display device 51 and the second display device 52 respectively display the minimum maneuvering speed Vman output by the comparison device on their respective sides and the average value between the minimum maneuvering speed Vman on both sides of the aircraft, that is, the first display device 51 displays the minimum maneuvering speed Vman output by the first comparison device 41 and the average value between the minimum maneuvering speed Vman on both sides of the aircraft, and the second display device 52 displays the minimum maneuvering speed Vman output by the second comparison device 42 and the average value between the minimum maneuvering speed Vman on both sides of the aircraft. When a fault occurs during the normal operation of the aircraft, the pilot can determine which side of the aircraft has a fault based on the data respectively displayed by the two display devices, that is, the minimum maneuvering speed Vman and the average value between the minimum maneuvering speed Vman on both sides of the aircraft, so as to quickly solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or the airspeed detection device, thereby improving flight safety.

[0069] In one embodiment, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 is less than or equal to the second threshold, and / or the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second threshold, the first comparison device 41 outputs the minimum maneuvering speed Vman on the first side of the aircraft as zero, and / or the second comparison device 42 resets the minimum maneuvering speed Vman on the second side of the aircraft to zero and outputs it.

[0070] Specifically, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 is less than or equal to the second threshold, or the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second threshold, the first comparison device 41 resets the minimum maneuvering speed Vman on the first side of the aircraft to zero and outputs it, and the second comparison device 42 resets the minimum maneuvering speed Vman on the second side of the aircraft to zero and outputs it. Of course, when the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 is less than or equal to the second threshold, and the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second threshold, the first comparison device 41 resets the minimum maneuvering speed Vman on the first side of the aircraft to zero and outputs it, and the second comparison device 42 resets the minimum maneuvering speed Vman on the second side of the aircraft to zero and outputs it. Simply put, when a fault occurs during the normal operation of the aircraft, if the minimum maneuvering speed Vman output by the first computing device 31 or the second computing device 32 or both computing devices is less than or equal to the second threshold, the two comparison devices respectively reset the minimum maneuvering speed Vman on their respective sides and then output it, so as to effectively solve the problem that the comparison device outputs an unsafe and incorrect minimum maneuvering speed Vman due to an error in the detection device itself, thereby improving the safety performance of the aircraft. Of course, if a fault occurs on one side of the aircraft, causing the first comparison device 41 or the second comparison device 42 to malfunction, for example, after the first comparison device 41 and the second comparison device 42 respectively reset the minimum maneuvering speed Vman on their respective sides, the data displayed by the display devices on both sides of the aircraft is inconsistent. At this time, the pilot can also judge which side of the aircraft has a fault from the data respectively displayed by the two display devices, so as to quickly repair the aircraft and improve flight safety.

[0071] It should be noted that the first display device 51 and the second display device 52 can be used to display the minimum maneuvering speed Vman on each side of the aircraft and the information that the minimum maneuvering speed Vman on both sides of the aircraft is zero. For example, the first display device 51 displays the minimum maneuvering speed Vman output by the first comparison device 41 and the information that the minimum maneuvering speed Vman is zero, and the second display device 52 displays the minimum maneuvering speed Vman output by the second comparison device 42 and the information that the minimum maneuvering speed Vman is zero.

[0072] In this embodiment, the first voting threshold TBD1 and the second voting threshold TBD2 are related to the measurement errors and installation errors of the angle-of-attack detection device and the airspeed detection device. The maximum errors of Vsw and Vman on both sides under various flight conditions (speed, angle of attack) and flight configurations (flap and slat retracted, landing gear down, etc.) are obtained through analysis and calculation based on the actual errors, and are stored in the database of the comparison device. The comparison device can obtain the settings of the first voting threshold TBD1 and the second voting threshold TBD2 under a certain flight condition and flight configuration by querying the database.

[0073] When the stall warning speed Vsw or the minimum maneuvering speed Vman on both sides of the aircraft is zero, the first display device 51 and the second display device 52 will not display the low-speed band. When the stall warning speed Vsw and the minimum maneuvering speed Vman on both sides of the aircraft are both non-zero, the first display device 51 and the second display device 52 will display the low-speed band.

[0074] The flight control system provided in this embodiment adopts a safe and reliable architecture design and two sets of independent low-speed band indication devices, which avoid the simultaneous errors of the display devices on both sides caused by a single failure of the calculation device or the comparison device. The angle of attack is the most direct parameter reflecting that the aircraft is approaching or reaching the stall state. The calculation device of the flight control system can obtain the characteristic zero-lift angle of attack αzl, the stall warning angle of attack αsw, and the stall angle of attack αs i of the aircraft under different configurations through the stored database, and calculate the minimum maneuvering speed Vman and the stall warning speed Vsw adapted to various actual aircraft configurations based on these characteristic angles of attack, so as to provide a safe low-speed band indication for the aircraft. The stall warning speed Vsw and the minimum maneuvering speed Vman calculated based on Formulas 1-4 continuously increase as the angle of attack of the aircraft continues to increase, thus providing the pilot with a low-speed indication that the speed margin of the aircraft from stalling is decreasing. By adjusting K1, K2, and N1 in Formulas 1-4, the stall warning speed Vsw and the minimum maneuvering speed Vman with different speed margins can be provided according to the characteristics of the aircraft itself. The stall warning speed Vsw and the minimum maneuvering speed Vman obtained through the comparison device and its comparison and voting method can solve the inconsistency problem caused by the detection errors or installation errors of the angle-of-attack detection device or the airspeed detection device, and the design of the voting thresholds TBD1 and TBD2 can solve the problem that the comparison device outputs unsafe and incorrect stall warning speeds Vsw and minimum maneuvering speeds Vman due to errors in the detection device itself, which not only solves the problem of inconsistent low-speed band display of the display devices on both sides of the aircraft, but also ensures the problem of unsafe indication caused by a single error.

[0075] Combined Figure 1 As shown, the working state of a flight control system for an aircraft provided in this embodiment is specifically as follows:

[0076] Both the first angle-of-attack detection device 11 and the second angle-of-attack detection device 12 can be implemented using angle-of-attack sensors. Both the first airspeed detection device 21 and the second airspeed detection device 22 can adopt an air data system based on the total and static pressure measurement method. The first computing device 31, the second computing device 32, the first comparison device 41, the second comparison device 42, the first display device 51, and the second display device 52 can all be completely independent computers, or they can be arbitrarily combined to form one or two computers. For example, the first computing device 31, the second computing device 32, the first comparison device 41, the second comparison device 42, the first display device 51, and the second display device 52 can form a multifunctional display integrating computing and display.

[0077] Formula 1:

[0078] Formula 2:

[0079] Formula 3:

[0080] Formula 4:

[0081] The characteristic zero-lift angle of attack αzl, stall warning angle of attack αsw, and stall angle of attack αs for different configurations are obtained through aircraft wind tunnel tests or actual flight tests. The speed at which the aircraft reaches the stall angle of attack is called the stall speed Vs. The K1, K2, and N1 in the calculation formulas for the stall warning speed Vsw and the minimum maneuvering speed Vman can be set according to the expected speed margin provided. Taking the aircraft stall speed Vs as the benchmark, setting N1 = 0.8, K1 = 0.8, and K2 = 0.67 can provide a 10% speed margin for the stall warning speed Vsw relative to the stall speed, and a 20% speed margin for the minimum maneuvering speed Vman relative to the stall warning speed Vsw.

[0082] The first voting threshold TBD1 and the second voting threshold TBD2 under the first comparison device 41 and the second comparison device 42 are related to the measurement errors and installation errors of the first angle of attack detection device 11, the second angle of attack detection device 12, the first airspeed detection device 21, and the second airspeed detection device 22. Considering conservatively, based on the maximum tolerances of the product and manufacturing installation, the maximum speed error generated under different speed and angle of attack flight conditions can be analyzed and calculated. For example, when the aircraft is flying at an angle of attack of 6 degrees and a speed of 200 knots in a certain configuration, the zero-lift angle of attack αzl = 0 degrees, the stall warning angle of attack αsw = 9 degrees, and the stall angle of attack αsi = 11 degrees in this configuration. The maximum measurement and installation error of the first angle of attack detection device 11 is 0.5 degrees, the maximum measurement and installation error of the second angle of attack detection device 12 is -0.5 degrees, the maximum error generated by the measurement and installation of the first airspeed detection device 21 is 2 knots, and the maximum error generated by the measurement and installation of the second airspeed detection device 22 is -2 knots. Then, according to Formulas 1 and 3, the maximum difference in the stall warning speed Vsw between the left and right sides of the aircraft under this condition is 16.9 knots, and the maximum difference in the minimum maneuvering speed Vman is 18.5 knots. Therefore, the first voting threshold TBD1 can be set to 16.9 knots, and the second voting threshold TBD2 can be set to 18.5 knots. In this flight state, the stall warning speed Vsw output by the first comparison device 41 and the second comparison device 42 is 163 knots, and the minimum maneuvering speed Vman is 178 knots.

[0083] Therefore, this embodiment can provide stall warning speed Vsw and minimum maneuvering speed Vman indications with different speed margins according to the characteristics of the aircraft itself; the stall warning speed Vsw and minimum maneuvering speed Vman obtained through the comparison device and its comparison and voting method can solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or airspeed detection device, and the design of the voting thresholds TBD1 and TBD2 can solve the problem that the comparison device outputs unsafe and incorrect stall warning speed Vsw and minimum maneuvering speed Vman due to errors in the detection device itself, which not only solves the problem of inconsistent display in the low-speed band of the display devices on both sides of the aircraft but also ensures the problem of unsafe indication caused by a single error.

[0084] As Figure 2 shown, this embodiment provides a flight control method for an aircraft, including the following steps:

[0085] S1) Obtain the angle of attack α of the aircraft;

[0086] S2) Store the stall warning angle of attack αsw, compare the angle of attack α of the aircraft with the stall warning angle of attack αsw, and determine the stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft according to the error between the angle of attack α of the aircraft and the stall warning angle of attack αsw;

[0087] S3) Receive the stall warning speed Vsw and the minimum maneuvering speed Vman. The comparison device compares the stall warning speed Vsw with a first threshold, and determines the output value of the stall warning speed Vsw according to the difference between the stall warning speed Vsw and the first threshold. The comparison device compares the minimum maneuvering speed Vman with a second threshold, and determines the output value of the minimum maneuvering speed Vman according to the difference between the minimum maneuvering speed Vman and the second threshold.

[0088] The stall warning speed Vsw and the minimum maneuvering speed Vman of the aircraft are included in the following formulas:

[0089] Formula 1:

[0090] Formula 2:

[0091] Formula 3:

[0092] Formula 4:

[0093] In step S1), it further includes: obtaining the flight calibrated airspeed Vcas.

[0094] In step S2), it further includes: storing the zero-lift angle of attack αzl, the stall angle of attack αsi, the stall warning angle of attack safety margin coefficient N1, the stall warning speed safety margin coefficient K1, and the minimum maneuvering speed safety margin coefficient K2.

[0095] As Figure 3 shown, step S2) includes the following steps:

[0096] S21) If the angle of attack α of the aircraft is greater than the stall warning angle of attack αsw, then execute step S22); otherwise, execute step S23).

[0097] S22) If the angle of attack α of the aircraft is greater than the stall angle of attack αsi, then execute step S24); otherwise, execute step S25).

[0098] S23) Calculate the stall warning speed Vsw and the minimum maneuvering speed Vman respectively using Formula 1 and Formula 2.

[0099] S24) Set the angle of attack α of the aircraft equal to the stall angle of attack αsi, and execute step S25).

[0100] S25) Calculate the stall warning speed Vsw and the minimum maneuvering speed Vman respectively using Formula 3 and Formula 4.

[0101] It should be noted that in combination withFigure 1 As shown, there are two angle-of-attack detection devices, namely the first angle-of-attack detection device 11 and the second angle-of-attack detection device 12. The first angle-of-attack detection device 11 is arranged on the first side of the aircraft, and the second angle-of-attack detection device 12 is arranged on the second side of the aircraft. Each angle-of-attack detection device is used to obtain the angle of attack α of the aircraft on the corresponding side of the angle-of-attack detection device. There are two airspeed detection devices, namely the first airspeed detection device 21 and the second airspeed detection device 22. The first airspeed detection device 21 is arranged on the first side of the aircraft, and the second airspeed detection device 22 is arranged on the second side of the aircraft. Each airspeed detection device is used to obtain the calibrated airspeed Vcas of the flight on the corresponding side of the airspeed detection device. There are two calculation devices, namely the first calculation device 31 and the second calculation device 32. The first calculation device 31 is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the first side of the aircraft. The second calculation device 32 is used to calculate the stall warning speed Vsw and the minimum maneuvering speed Vman on the second side of the aircraft. There are two comparison devices, namely the first comparison device 41 and the second comparison device 42. The first comparison device 41 is used to compare the difference between the stall warning speed Vsw on the first side of the aircraft and the first threshold value, and the difference between the minimum maneuvering speed Vman and the second threshold value. The second comparison device 42 is also used to compare the difference between the stall warning speed Vsw on the second side of the aircraft and the first threshold value, and the difference between the minimum maneuvering speed Vman and the second threshold value. The display devices are two, namely the first display device 51 and the second display device 52. The first display device 51 and the second display device 52 are used to display the stall warning speed Vsw and the minimum maneuvering speed Vman on their respective sides of the aircraft.

[0102] In step S3), it specifically includes a stall warning speed Vsw output step S31) and a minimum maneuvering speed Vman output step S32). The execution order of step S31) and step S32) can be executed simultaneously, or step S31) can be executed first and then step S32). Of course, step S32) can also be executed first and then step S31). Here, no special limitation is made.

[0103] As Figure 4 shown, step S31) specifically includes the following steps:

[0104] S311) If the stall warning speed Vsw output by the first calculation device 31 is greater than the first threshold value, then step S312) is executed; otherwise, step S313) is executed.

[0105] S312) If the stall warning speed Vsw output by the second computing device 32 is greater than the first threshold, step S314) is executed; otherwise, step S313) is executed.

[0106] S313) When the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 is less than or equal to the first threshold, and / or the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first threshold, the first comparison device 41 resets the stall warning speed Vsw of the first side of the aircraft to zero and outputs it, and / or the second comparison device 42 resets the stall warning speed Vsw of the second side of the aircraft to zero and outputs it. Wherein, the first display device 51 and the second display device 52 can be used to display the stall warning speed Vsw output by the comparison device on each side and the information that the stall warning speed Vsw on both sides of the aircraft is zero. For example, the first display device 51 displays the stall warning speed Vsw output by the first comparison device 41 and the information that the stall warning speed Vsw is zero, and the second display device 52 displays the stall warning speed Vsw output by the second comparison device 42 and the information that the stall warning speed Vsw is zero.

[0107] S314) Determine whether the difference between the stall warning speeds Vsw output by the first computing device 31 and the second computing device 32 is not greater than (i.e., less than or equal to) the first voting threshold TBD1. If so, step S315) is executed; otherwise, step S313) is executed.

[0108] S315) When the difference between the stall warning speed Vsw of the first side of the aircraft output by the first computing device 31 and the stall warning speed Vsw of the second side of the aircraft output by the second computing device 32 is less than or equal to the first voting threshold TBD1, the first comparison device 41 outputs the average value between the stall warning speed Vsw of the first side of the aircraft and the stall warning speed Vsw of the second side of the aircraft, and / or the second comparison device 42 both outputs the average value between the stall warning speed Vsw of the first side of the aircraft and the stall warning speed Vsw of the second side of the aircraft. During the normal operation of the aircraft, the first display device 51 and the second display device 52 respectively display the stall warning speed Vsw output by the comparison device on their respective sides and the average value between the stall warning speeds Vsw on both sides of the aircraft, that is, the first display device 51 displays the stall warning speed Vsw output by the first comparison device 41 and the average value between the stall warning speeds Vsw, and the second display device 52 displays the stall warning speed Vsw output by the second comparison device 42 and the average value between the stall warning speeds Vsw. When a fault occurs during the normal operation of the aircraft, the flight crew can determine which side of the aircraft has a fault based on the data respectively displayed by the two display devices, that is, the stall warning speed Vsw and the average value between the stall warning speeds Vsw on both sides of the aircraft, so as to quickly solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or the airspeed detection device.

[0109] As Figure 5 shown, step S32) specifically includes the following steps:

[0110] S321) If the minimum maneuvering speed Vman output by the first computing device 31 is greater than the second threshold, step S322) is executed; otherwise, step S323) is executed.

[0111] S322) If the minimum maneuvering speed Vman output by the second computing device 32 is greater than the second threshold, step S324) is executed; otherwise, step S323) is executed.

[0112] S323) When the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 is less than or equal to the second threshold, and / or when the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second threshold, the first comparison device 41 outputs the minimum maneuvering speed Vman on the first side of the aircraft as zero, and / or the second comparison device 42 resets the minimum maneuvering speed Vman on the second side of the aircraft to zero and outputs it. Wherein, the first display device 51 and the second display device 52 respectively display the minimum maneuvering speed Vman output by the comparison device on their respective sides and the information that the minimum maneuvering speed Vman on both sides of the aircraft is zero.

[0113] S324) Respectively determine whether the minimum maneuvering speed Vman output by the first computing device 31 and the second computing device 32 is not greater than (i.e., less than or equal to) the second threshold. If so, execute step S325); otherwise, execute step S323).

[0114] S325) When the difference between the minimum maneuvering speed Vman on the first side of the aircraft output by the first computing device 31 and the minimum maneuvering speed Vman on the second side of the aircraft output by the second computing device 32 is less than or equal to the second voting threshold TBD2, the first comparison device 41 outputs the average value between the minimum maneuvering speed Vman on the first side of the aircraft and the minimum maneuvering speed Vman on the second side of the aircraft, and / or the second comparison device 42 outputs the average value between the minimum maneuvering speed Vman on the first side of the aircraft and the minimum maneuvering speed Vman on the second side of the aircraft. During the normal operation of the aircraft, the first display device 51 and the second display device 52 respectively display the minimum maneuvering speed Vman output by the comparison device on their respective sides and the average value between the minimum maneuvering speed Vman on both sides of the aircraft. That is, the first display device 51 displays the minimum maneuvering speed Vman output by the first comparison device 41 and the average value between the minimum maneuvering speed Vman on both sides of the aircraft, and the second display device 52 displays the minimum maneuvering speed Vman output by the second comparison device 42 and the average value between the minimum maneuvering speed Vman on both sides of the aircraft. When a fault occurs during the normal operation of the aircraft, the pilot can determine which side of the aircraft has a fault based on the data respectively displayed by the two display devices, that is, the minimum maneuvering speed Vman and the average value between the minimum maneuvering speed Vman on both sides of the aircraft, so as to quickly solve the inconsistency problem caused by the detection error or installation error of the angle-of-attack detection device or the airspeed detection device.

[0115] The flight control method provided in this embodiment adopts a safe and reliable architecture design with two sets of independent low-speed band indicating devices, which avoids the simultaneous error of the display devices on both sides caused by a single failure of the computing device or the comparison device. The angle of attack is the most direct parameter reflecting the state of the aircraft approaching or reaching the stall state. The computing device of the flight control system can obtain the characteristic zero-lift angle of attack αzl, stall warning angle of attack αsw, and stall angle of attack αs of the aircraft under different configurations through the stored database, and calculate the minimum maneuvering speed Vman and stall warning speed Vsw adapted to various configurations of the actual aircraft based on these characteristic angles of attack, so as to provide a low-speed band indication for the safety of the aircraft. The stall warning speed Vsw and minimum maneuvering speed Vman calculated based on Formulas 1-4 increase continuously as the angle of attack of the aircraft continues to increase, thus providing a low-speed indication to the pilot that the speed margin of the aircraft from stalling is decreasing. By adjusting K1, K2, and N1 in Formulas 1-4, the stall warning speed Vsw and minimum maneuvering speed Vman with different speed margins can be provided according to the characteristics of the aircraft itself. The stall warning speed Vsw and minimum maneuvering speed Vman obtained through the comparison device and its comparison voting method can solve the inconsistency problem caused by the detection error or installation error of the angle of attack detection device or airspeed detection device, and the design of the voting thresholds TBD1 and TBD2 can solve the problem that the comparison device outputs unsafe and incorrect stall warning speed Vsw and minimum maneuvering speed Vman due to the error of the detection device itself, which not only solves the problem of inconsistent low-speed band display of the display devices on both sides of the aircraft, but also ensures the problem of unsafe indication caused by a single error.

[0116] The above has introduced in detail a flight control system and method for an aircraft provided in an embodiment of the present application. Specific examples are used in this article to elaborate on the principle and implementation manner of the present application. The description of the above embodiments is only used to help understand the technical solution and its core idea of the present application; those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. An aircraft flight control system, characterized in that, Comprising: An angle of attack detection device for obtaining the angle of attack α of the aircraft; And A computing device that internally stores a stall warning angle of attack α sw , a zero-lift angle of attack α zl , a stall angle of attack α si , a stall warning angle of attack safety margin coefficient N1, a stall warning speed safety margin coefficient K1, and a minimum maneuvering speed safety margin coefficient K2. The computing device is configured to compare the aircraft angle of attack α with the stall warning angle of attack α sw and determine the stall warning speed V sw of the aircraft and the minimum maneuvering speed V sw based on the difference between the aircraft angle of attack α and the stall warning angle of attack α man ; An airspeed detection device for obtaining the flight airspeed V cas ; When the angle of attack α of the aircraft is less than or equal to the stall warning angle of attack α sw the stall warning speed V is calculated using the following formula sw and the minimum maneuvering speed V man , Or, When the angle of attack α of the aircraft is greater than the stall warning angle of attack α sw , compare the angle of attack α of the aircraft with the stall angle of attack α si , and based on the difference between the angle of attack α of the aircraft and the stall angle of attack α si , determine the stall warning speed V sw of the aircraft and the minimum maneuvering speed V man .

2. The flight control system according to claim 1, characterized in that When the angle of attack α of the aircraft is less than or equal to the stall angle of attack α si the stall warning speed V is calculated using the following formula sw and the minimum maneuvering speed V man , 3. The flight control system according to claim 2, characterized in that When the angle of attack α of the aircraft is greater than the stall angle of attack α si , set the angle of attack α of the aircraft equal to the stall angle of attack α si , and calculate the stall warning speed V using the following formula sw and the minimum maneuvering speed V man , 4. The flight control system according to any one of claims 1-3, characterized in that, Further comprising: A comparison device for receiving the stall warning speed V sw and the minimum maneuvering speed V man , the comparison device compares the stall warning speed V sw with a first threshold value, and based on the difference between the stall warning speed V sw and the first threshold value, to determine the output value of the stall warning speed V sw ; The comparison device compares the minimum maneuvering speed V man with a second threshold value, and determines the output value of the minimum maneuvering speed V man according to the difference between the minimum maneuvering speed V man and the second threshold value.

5. The flight control system according to claim 4, characterized in that There are two said angle of attack detection devices, namely a first angle of attack detection device and a second angle of attack detection device. The first angle of attack detection device is arranged on the first side of the aircraft, and the second angle of attack detection device is arranged on the second side of the aircraft. Each angle of attack detection device is used to obtain the angle of attack α of the aircraft corresponding to the side where the angle of attack detection device is located; There are two airspeed detection devices, namely a first airspeed detection device and a second airspeed detection device. The first airspeed detection device is arranged on the first side of the aircraft, and the second airspeed detection device is arranged on the second side of the aircraft. Each airspeed detection device is used to obtain the flight airspeed V corresponding to the side where the airspeed detection device is located. cas ; There are two computing devices, namely a first computing device and a second computing device. The first computing device is used to calculate the stall warning speed V on the first side of the aircraft sw and the minimum maneuvering speed V man , and the second computing device is used to calculate the stall warning speed V on the second side of the aircraft sw and the minimum maneuvering speed V man ; There are two comparison devices, namely the first comparison device and the second comparison device. The first comparison device is used to compare the difference between the stall warning speed V on the first side of the aircraft sw and the first threshold, and the difference between the minimum maneuvering speed V man and the second threshold. The second comparison device is used to compare the difference between the stall warning speed V on the second side of the aircraft sw and the first threshold, and the difference between the minimum maneuvering speed V man and the second threshold.

6. The flight control system according to claim 5, characterized in that When the stall warning speed V of the first side of the aircraft output by the first computing device sw is greater than the first threshold, the stall warning speed V of the second side of the aircraft output by the second computing device sw is greater than the first threshold, and the stall warning speed V of the first side of the aircraft output by the first computing device sw and the stall warning speed V of the second side of the aircraft output by the second computing device sw when the difference between them is less than or equal to the first voting threshold TBD1, the first comparison device and / or the second comparison device output the average value between the stall warning speed V of the first side of the aircraft sw and the stall warning speed V of the second side of the aircraft sw ​ 7. The flight control system according to claim 6, characterized in that When the stall warning speed V on the first side of the aircraft output by the first computing device sw is less than or equal to the first threshold, and / or the stall warning speed V on the second side of the aircraft output by the second computing device sw is less than or equal to the first threshold, the first comparison device outputs the stall warning speed V on the first side of the aircraft sw as zero, and / or the second comparison device outputs the stall warning speed V on the second side of the aircraft sw as zero.

8. The flight control system according to claim 6, characterized in that When the minimum maneuvering speed V on the first side of the aircraft output by the first computing device man is greater than the second threshold, the second computing device outputs the minimum maneuvering speed V on the second side of the aircraft man is greater than the second threshold, and the minimum maneuvering speed V on the first side of the aircraft output by the first computing device man and the minimum maneuvering speed V on the second side of the aircraft output by the second computing device man when the difference between them is less than or equal to the second voting threshold TBD2, the first comparison device and / or the second comparison device output the average value between the minimum maneuvering speed V on the first side of the aircraft man and the minimum maneuvering speed V on the second side of the aircraft man therebetween.

9. The flight control system according to claim 6, characterized in that When the minimum maneuvering speed V of the first side of the aircraft output by the first computing device man is less than or equal to the second threshold, and / or the minimum maneuvering speed V of the second side of the aircraft output by the second computing device man is less than or equal to the second threshold, the first comparison device outputs the minimum maneuvering speed V of the first side of the aircraft man as zero, and / or the second comparison device outputs the minimum maneuvering speed V of the second side of the aircraft man as zero.

10. A flight control method for an aircraft, characterized in that, Including the following steps: Obtain the angle of attack α of the aircraft; Stored stall warning angle of attack α sw , zero-lift angle of attack α zl , stall angle of attack α si , stall warning angle of attack safety margin coefficient N1, stall warning speed safety margin coefficient K1, and minimum maneuvering speed safety margin coefficient K2. Compare the aircraft angle of attack α with the stall warning angle of attack α sw , and based on the difference between the aircraft angle of attack α and the stall warning angle of attack α sw , determine the stall warning speed V sw and the minimum maneuvering speed V man ; When the angle of attack α of the aircraft is less than or equal to the stall warning angle of attack α sw the stall warning speed V is calculated using the following formula sw and the minimum maneuvering speed V man , Or When the angle of attack α of the aircraft is greater than the stall warning angle of attack α sw , compare the angle of attack α of the aircraft with the stall angle of attack α si , and based on the difference between the angle of attack α of the aircraft and the stall angle of attack α si , to determine the stall warning speed V sw and the minimum maneuvering speed V man .

11. The flight control method according to claim 10, characterized in that When the angle of attack α of the aircraft is less than or equal to the stall angle of attack α si the stall warning speed V is calculated using the following formula sw and the minimum maneuvering speed V man , 12. The flight control method according to claim 11, characterized in that When the angle of attack α of the aircraft is greater than the stall angle of attack α si , set the angle of attack α of the aircraft equal to the stall angle of attack α si , and calculate the stall warning speed V sw and the minimum maneuvering speed V man , 13. The flight control method according to claim 11 or 12, characterized in that, After the step of storing the stall warning angle of attack α sw it further includes: Receive the stall warning speed V sw and the minimum maneuvering speed V man , compare the stall warning speed V sw with a first threshold, and based on the difference between the stall warning speed V sw and the first threshold, determine the output value of the stall warning speed V sw ; compare the minimum maneuvering speed V man with a second threshold, and based on the difference between the minimum maneuvering speed V man and the second threshold, determine the output value of the minimum maneuvering speed V man .

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