Multi-scenario gravity center adjustment method and system for aircraft test flight

Abstract

The present application relates to a method and system for adjusting the center of gravity of an aircraft in multiple scenarios. The method comprises: receiving target center of gravity data required for flight testing, and the roll angle and pitch angle of the aircraft; determining whether the roll angle is greater than a roll angle threshold; when the roll angle is greater than the roll angle threshold, closing the water tank inter-tube valve and suspending the center of gravity adjustment; when the roll angle is less than or equal to the roll angle threshold, opening the water tank inter-tube valve, and determining whether the pitch angle is less than a first pitch angle threshold; when the pitch angle is less than the first pitch angle threshold, adjusting the center of gravity using a water tank external circulation mode; when the pitch angle is greater than or equal to the first pitch angle threshold and less than a second pitch angle threshold, wherein the second pitch angle threshold is greater than the first pitch angle threshold, adjusting the center of gravity using a water tank internal circulation mode; and when the pitch angle is greater than or equal to the second pitch angle threshold, suspending the center of gravity adjustment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft test flight, in particular to a test flight multi-scene center of gravity adjustment method and system. BACKGROUND

[0002] The center of gravity position of an aircraft, especially a large civil aircraft, plays a very key role in the flight performance, stability, maneuverability and safety of the aircraft. Ensuring the safety and performance of the aircraft under various extreme complex working conditions is one of the core tasks of the test flight of a large civil aircraft. Therefore, a center of gravity adjustment system is installed to adjust the real-time center of gravity of the aircraft to verify the related performance of the aircraft. The center of gravity adjustment system calculates the real-time weight and center of gravity of the aircraft according to the ground weight information, fuel consumption information, landing gear state, center of gravity adjustment system weight state, etc., and can adjust or maintain the center of gravity of the aircraft by controlling the transmission of the water in the front and rear passenger cabins according to the test flight requirements.

[0003] The traditional center of gravity adjustment system mainly relies on the adjustment between the front water tank group and the rear water tank group of the center of gravity adjustment system installed in the passenger cabin to realize limited center of gravity adjustment. This method is relatively simple in principle, but when facing the complex changes of flight attitude in test flight, this adjustment method is difficult to realize the rapid and accurate differential adjustment of the center of gravity of the aircraft.

[0004] With the development of test flight technology towards refinement and comprehensiveness, the accuracy and flexibility of the center of gravity adjustment are increasingly required. The traditional center of gravity adjustment method cannot meet the demand of dynamic adjustment of the center of gravity under various complex flight attitude combinations, and cannot simulate more diversified and extreme center of gravity distribution scenes, thereby restricting the full-fledged and deep exploration and verification of the performance of the aircraft in test flight. SUMMARY

[0005] An object of the present application is to provide a test flight multi-scene center of gravity adjustment method and system which can overcome the shortcomings of the prior art, adapt to various complex flight attitude scenes, and realize rapid and accurate differential adjustment of the center of gravity of the aircraft.

[0006] The above object of the present application is achieved by a test flight multi-scene center of gravity adjustment method, which comprises the following steps:

[0007] Receiving target center of gravity data required for test flight and attitude data of the aircraft, wherein the attitude data of the aircraft comprises a roll angle and a pitch angle of the aircraft;

[0008] Judging whether the roll angle of the aircraft is greater than a roll angle threshold value;

[0009] When the roll angle of the aircraft is greater than the roll angle threshold value, it is determined that the aircraft is in a large roll angle flight scene, the inter-tank cross pipe valve is closed, and the center of gravity adjustment is suspended;

[0010] When the roll angle of the aircraft is less than or equal to the roll angle threshold, it is determined that the aircraft is in a small roll angle flight scenario, the inter-tank cross pipe valve is opened, and it is determined whether the pitch angle of the aircraft is less than the first pitch angle threshold;

[0011] When the pitch angle of the aircraft is less than the first pitch angle threshold, it is determined that the aircraft is in a small pitch angle flight scenario, the center of gravity is adjusted in a tank outer circulation mode, and the center of gravity is supplemented and adjusted in a tank inner circulation mode if necessary;

[0012] When the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold and less than the second pitch angle threshold, wherein the second pitch angle threshold is greater than the first pitch angle threshold, it is determined that the aircraft is in a medium pitch angle flight scenario, the center of gravity is adjusted in a tank inner circulation mode, and the center of gravity is supplemented and adjusted in a tank outer circulation mode if necessary;

[0013] When the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold, it is determined that the aircraft is in a large pitch angle flight scenario, and the center of gravity adjustment is suspended.

[0014] According to the above technical solution, the aircraft test flight multi-scenario center of gravity adjustment method can achieve the following beneficial technical effects: It can adapt to various complex flight attitude scenarios and can achieve rapid and accurate differentiated adjustment of the center of gravity of the aircraft.

[0015] Preferably, the aircraft comprises a front tank group and a rear tank group, the front tank group comprises a front row of tanks and a rear row of tanks, the rear tank group also comprises a front row of tanks and a rear row of tanks, and the inter-tank cross pipe valve is a valve arranged on a cross pipe between two tanks in each row.

[0016] Preferably, the tank outer circulation mode refers to participation in circulation between the front row of tanks of the front tank group and the rear row of tanks of the rear tank group, and the tank inner circulation mode refers to participation in circulation between the rear row of tanks of the front tank group and the front row of tanks of the rear tank group.

[0017] Preferably, the front tank group and the rear tank group are connected by two side main pipelines, and a valve is arranged between the inlet of each main pipeline and the tank.

[0018] Preferably, when the aircraft is in a large roll angle flight scenario or a large pitch angle flight scenario, water level information is received, and if the water level in a certain tank on one side is too high, the water in the tank with the too high water level is transferred to a tank with a lower water level.

[0019] The above object of the application is also achieved by a multi-scenario center of gravity adjustment system for aircraft test flight, which comprises:

[0020] A total control unit configured to receive target center of gravity data required for test flight and attitude data of the aircraft, the attitude data of the aircraft including roll angle and pitch angle of the aircraft;

[0021] The total control unit is further configured to:

[0022] determine whether the roll angle of the aircraft is greater than a roll angle threshold value;

[0023] when the roll angle of the aircraft is greater than the roll angle threshold value, determine that the aircraft is in a large roll angle flight scenario, close the water tank inter-lateral pipe valve, and suspend the center of gravity adjustment;

[0024] when the roll angle of the aircraft is less than or equal to the roll angle threshold value, determine that the aircraft is in a small roll angle flight scenario, open the water tank inter-lateral pipe valve, and determine whether the pitch angle of the aircraft is less than a first pitch angle threshold value;

[0025] when the pitch angle of the aircraft is less than the first pitch angle threshold value, determine that the aircraft is in a small pitch angle flight scenario, adjust the center of gravity in a water tank outer circulation mode, and supplement the center of gravity adjustment in a water tank inner circulation mode when necessary;

[0026] when the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold value and less than a second pitch angle threshold value, wherein the second pitch angle threshold value is greater than the first pitch angle threshold value, determine that the aircraft is in a medium pitch angle flight scenario, adjust the center of gravity in a water tank inner circulation mode, and supplement the center of gravity adjustment in a water tank outer circulation mode when necessary;

[0027] when the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold value, determine that the aircraft is in a large pitch angle flight scenario, and suspend the center of gravity adjustment.

[0028] According to the above technical solution, the aircraft test flight multi-scenario center of gravity adjustment system can adapt to various complex flight attitude scenarios and can achieve rapid and accurate differential adjustment of the center of gravity of the aircraft.

[0029] Preferably, the aircraft test flight multi-scenario center of gravity adjustment system comprises a front water tank group and a rear water tank group, the front water tank group comprises a front row of water tanks and a rear row of water tanks, the rear water tank group also comprises a front row of water tanks and a rear row of water tanks, and the water tank inter-lateral pipe valve is a valve arranged on a lateral pipe between two water tanks in each row.

[0030] Preferably, the water tank outer circulation mode refers to circulation between the front row of water tanks of the front water tank group and the rear row of water tanks of the rear water tank group, and the water tank inner circulation mode refers to circulation between the rear row of water tanks of the front water tank group and the front row of water tanks of the rear water tank group.

[0031] Preferably, the front water tank group and the rear water tank group are connected by two side main pipelines, and a valve is arranged between the inlet of each main pipeline and the water tank.

[0032] Preferably, the aircraft test flight multi-scenario gravity center adjusting system further comprises a liquid level sensor arranged in each water tank, and the master control unit is further configured to:

[0033] When the aircraft is in a large roll angle flight scenario or a large pitch angle flight scenario, the water tank liquid level information provided by the liquid level sensor is received, and if the liquid level in a water tank on one side is too high, the water in the water tank with the too high liquid level is transferred to a water tank with a lower liquid level. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 A principle block diagram of the aircraft test flight multi-scenario gravity center adjusting system of the present application;

[0035] Figure 2 A flow chart of the aircraft test flight multi-scenario gravity center adjusting method of the present application;

[0036] Figure 3 A mechanical structure block diagram of the aircraft test flight multi-scenario gravity center adjusting system of the present application;

[0037] Figure 4 An operation diagram of the aircraft test flight multi-scenario gravity center adjusting system in a large roll angle flight scenario of the present application;

[0038] Figure 5 An intelligent adjusting example diagram of the aircraft test flight multi-scenario gravity center adjusting system in a large angle flight scenario of the present application.

[0039] LIST OF REFERENCE NUMBERS

[0040] 1. solenoid valve;

[0041] 2. water tank;

[0042] 3. liquid level sensor;

[0043] 4. electric ball valve;

[0044] 5. water pump;

[0045] 6. flow sensor. DETAILED DESCRIPTION

[0046] In the following detailed description of implementations of the application, numerous specific details are set forth in order to provide a thorough understanding of the application. However, well-known methods, procedures, components, and circuits have not been described in detail as such exemplary implementations are believed to be best understood according to the claims. Although the following presented in the following detailed description with reference to the accompanying drawings depictions include various specific embodiments to the application it is understood that the scope of the application is not limited to these depictions, but rather encompasses all changes, alterations and modifications that come within the spirit and scope of the application. Accordingly, the application is not to be limited as illustrated in the figures, but is to be accorded the full scope consistent with the claims, to the full extent allowed by applicable laws and regulations. All statements regarding the application herein are meant as illustrative only and were presented only to more clearly, completely and accurately describe the application. Accordingly, the scope of the application should be determined only by the claims.

[0047] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the application herein and the claims that follow is not intended to be limiting of the application so long as the context permits. Although any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present application, exemplary methods and materials are now described. Unless defined otherwise, all technical and scientific terms and any acronyms used herein have the same meanings as commonly understood by one of ordinary skill in the art in the field of the application. Any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present application. The descriptions herein of the exemplary embodiments of the application are intended to be illustrative, but not limiting, of the scope of the application as set forth herewith. Other and further embodiments of the application can be devised without departing from the basic scope of the application. Although the depictions presented herein include a limited number of embodiments to the application it is understood that the scope of the application is not limited to these depictions, but rather encompasses all changes, alterations and modifications that come within the spirit and scope of the application. Accordingly, the application is not to be limited as illustrated in the figures, but is to be accorded the full scope consistent with the claims, to the full extent allowed by applicable laws and regulations. All statements regarding the application herein are meant as illustrative only and were presented only to more clearly, completely and accurately describe the application. Accordingly, the scope of the application should be determined only by the claims.

[0048] Figure 1 A principle block diagram of the aircraft test flight multi-scene gravity center adjusting system of the application; Figure 2 A flow chart of the aircraft test flight multi-scene gravity center adjusting method of the application; Figure 3 A mechanical structure block diagram of the aircraft test flight multi-scene gravity center adjusting system of the application; Figure 4 A running chart of the large roll angle flight scene of the aircraft test flight multi-scene gravity center adjusting system of the application; Figure 5 An intelligent adjusting example chart of the large angle flight scene of the aircraft test flight multi-scene gravity center adjusting system of the application.

[0049] The technical scheme adopted by the present application is: after entering the test flight stage, the gravity distribution system identifies the aircraft attitude data, judges the flight attitude (roll, pitch) of the aircraft through the control system, combines the liquid level, pipeline flow and other information of the system's own water tank, controls the water pump, valve and other elements in the control system, and realizes the adjustment of the aircraft gravity to the target gravity of the test flight in different scenes, while ensuring the safety of the aircraft.

[0050] Figure 1 The principle block diagram of the aircraft test flight multi-scene gravity adjustment system of the present application is shown in Figure 1 The total control unit receives the target gravity required for the test flight through the on-board passenger cabin input device, and identifies the attitude of the aircraft through the aircraft bus and the information provided by the system's own sensors such as liquid level and flow, controls the opening and closing of the water pump and valve in the control system, thereby achieving the purpose of gravity adjustment.

[0051] Figure 3 The mechanical structure block diagram of the aircraft test flight multi-scene gravity adjustment system of the present application is shown in The aircraft test flight multi-scene gravity adjustment system mainly includes front water tank groups (such as front passenger cabin water tank groups), rear water tank groups (such as rear passenger cabin water tank groups), water pumps, valves and the like. The front water tank group includes front and rear rows of water tanks, and the rear water tank group also includes front and rear rows of water tanks. For example, each water tank group is composed of four rows of eight water tanks, the front two rows of water tanks are the front row of water tanks, and the rear two rows of water tanks are the rear row of water tanks. A liquid level sensor 3 is arranged inside each water tank. The front water tank group and the rear water tank group are connected by two side main pipelines, and an electromagnetic valve 1 (which can be referred to as an entering part valve, and the electromagnetic valve is only a preferred form, and other forms of valves can also be used) is arranged between the entering part of each main pipeline and the water tank to control the water entering the water tank. Each two water tanks 2 in each row are connected by a cross pipe, and an electromagnetic valve 1 (which can be referred to as a water tank cross pipe valve, and the electromagnetic valve is only a preferred form, and other forms of valves can also be used) is arranged on the cross pipe to control the water flow between each row of water tanks 2. An electric ball valve 4 (which is only a preferred form, and other forms of valves can also be used), a water pump 5, a flow sensor 6 and the like are arranged on the two side main pipelines. It should be noted that the transverse direction used herein refers to the direction perpendicular to the longitudinal direction (heading) of the aircraft, and the cross pipe refers to the pipeline arranged in the transverse direction.

[0052] As shown in Figures 1 to 4 The aircraft test flight multi-scene gravity adjustment method according to the present application includes:

[0053] receiving target gravity data required for the test flight and attitude data of the aircraft, the attitude data of the aircraft including the roll angle and the pitch angle of the aircraft;

[0054] judging whether the roll angle of the aircraft is greater than a roll angle threshold (for example, a roll angle threshold x);

[0055] When the roll angle of the aircraft is greater than the roll angle threshold, it is determined that the aircraft is in a large roll angle flight scenario, the inter-tank cross-pipe valve is closed to avoid water flow from one side of the tank to the other side, causing the other side of the tank to overflow, and the center of gravity adjustment is suspended;

[0056] When the roll angle of the aircraft is less than or equal to the roll angle threshold, it is determined that the aircraft is in a small roll angle flight scenario, the inter-tank cross-pipe valve is opened, and it is determined whether the pitch angle of the aircraft is less than a first pitch angle threshold (e.g., first pitch angle threshold y);

[0057] When the pitch angle of the aircraft is less than the first pitch angle threshold, it is determined that the aircraft is in a small pitch angle flight scenario, the center of gravity adjustment is performed using the outer tank circulation mode, and if necessary (i.e., the outer circulation is still insufficient to reach the test target center of gravity), the center of gravity adjustment is supplemented using the inner tank circulation mode;

[0058] When the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold and less than a second pitch angle threshold (e.g., second pitch angle threshold z), where the second pitch angle threshold is greater than the first pitch angle threshold, it is determined that the aircraft is in a medium pitch angle flight scenario, the center of gravity adjustment is performed using the inner tank circulation mode, and if necessary (i.e., the inner circulation is still insufficient to reach the test target center of gravity), the center of gravity adjustment is supplemented using the outer tank circulation mode;

[0059] When the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold, it is determined that the aircraft is in a large pitch angle flight scenario, and the center of gravity adjustment is suspended.

[0060] Preferably, the roll angle threshold x is 28-32 degrees. More preferably, the roll angle threshold x is 30 degrees.

[0061] Preferably, the first pitch angle threshold y is 8-12 degrees. More preferably, the first pitch angle threshold y is 10 degrees.

[0062] Preferably, the second pitch angle threshold z is 28-32 degrees. More preferably, the second pitch angle threshold z is 30 degrees.

[0063] As Figure 3As shown, the water tank outer circulation mode refers to the circulation between the front drain tank of the front water tank group (i.e., the outer water tank of the front water tank group) and the rear drain tank of the rear water tank group (i.e., the outer water tank of the rear water tank group), and the water tank inner circulation mode refers to the circulation between the rear drain tank of the front water tank group (i.e., the inner water tank of the front water tank group) and the front drain tank of the rear water tank group (i.e., the inner water tank of the rear water tank group). That is, in the case where each water tank group is composed of four rows of eight water tanks, the water tank outer circulation mode refers to the circulation between the front two rows of water tanks of the front water tank group and the rear two rows of water tanks of the rear water tank group, and the water tank inner circulation mode refers to the circulation between the rear two rows of water tanks of the front water tank group and the front two rows of water tanks of the rear water tank group.

[0064] As shown, Figure 5 When the aircraft is in a large roll angle flight scenario (i.e., the roll angle is greater than a roll angle threshold x) or a large pitch angle flight scenario (i.e., the pitch angle is greater than a second pitch angle threshold z), the water tank liquid level information is received, and if the liquid level in a certain water tank on one side is too high, the water in the water tank with the too high liquid level is transferred to a water tank with a lower liquid level by starting the water pump 5, the electric ball valve 4, and the electromagnetic valve of the related water tank.

[0065] As shown, Figures 1 to 4 The aircraft test flight multi-scenario gravity center adjustment system according to the present application comprises:

[0066] a total control unit configured to receive target gravity center data required for the test flight and attitude data of the aircraft, the attitude data of the aircraft including a roll angle and a pitch angle of the aircraft;

[0067] The total control unit is further configured to:

[0068] determine whether the roll angle of the aircraft is greater than a roll angle threshold;

[0069] When the roll angle of the aircraft is greater than the roll angle threshold, it is determined that the aircraft is in a large roll angle flight scenario, the inter-tank cross pipe valve is closed, and the gravity center adjustment is suspended;

[0070] When the roll angle of the aircraft is less than or equal to the roll angle threshold, it is determined that the aircraft is in a small roll angle flight scenario, the inter-tank cross pipe valve is opened, and it is determined whether the pitch angle of the aircraft is less than a first pitch angle threshold;

[0071] When the pitch angle of the aircraft is less than the first pitch angle threshold, it is determined that the aircraft is in a small pitch angle flight scenario, the water tank outer circulation mode is adopted for the gravity center adjustment, and the water tank inner circulation mode is adopted for supplementary gravity center adjustment when necessary;

[0072] When the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold and less than the second pitch angle threshold, wherein the second pitch angle threshold is greater than the first pitch angle threshold, it is determined that the aircraft is in a medium pitch angle flight scenario, the water tank internal circulation mode is adopted for center of gravity adjustment, and the water tank external circulation mode is adopted for supplementary center of gravity adjustment when necessary;

[0073] When the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold, it is determined that the aircraft is in a large pitch angle flight scenario, and the center of gravity adjustment is suspended.

[0074] The beneficial effects of the present application compared with the prior art are:

[0075] 1) Improve flight safety. The present application accurately identifies the attitude of the aircraft and takes timely measures to avoid flight safety problems caused by imbalance of the center of gravity of the aircraft, especially when the aircraft is in a large roll angle or a large pitch angle, the system automatically closes the related adjustment function, effectively preventing the center of gravity adjustment from being caused by the large attitude angle of the aircraft.

[0076] 2) Adapt to adjustment in multiple scenarios and enhance the flexibility of adjustment. The present application can intelligently select internal circulation, external circulation or a combination of the two to adjust the center of gravity according to different flight attitudes, improving the flexibility of adjustment.

[0077] 3) Improve adjustment efficiency and accuracy. The present application preferentially adopts external circulation and internal circulation for small angle and medium angle pitch flight, respectively, and adopts supplementary circulation mode to improve the efficiency of center of gravity adjustment when the main circulation is insufficient. Especially in the flight state with small pitch angle, the water pump has high lift, and the use of external circulation adjustment produces a larger moment arm, which can more quickly and effectively adjust the center of gravity position of the aircraft, improving the adjustment efficiency and ensuring the accuracy of the center of gravity adjustment.

[0078] 4) Extreme attitude protection. In a large angle flight attitude, the center of gravity adjustment is suspended to prevent risks caused by excessive adjustment and to ensure the safety and stability of the aircraft in an extreme attitude.

[0079] 5) Intelligent balance and enhanced reliability. When the roll or pitch angle is too large and the water tank liquid level is unbalanced, water is transferred according to the liquid level information to balance the center of gravity, improving the reliability and adaptability of the center of gravity adjustment, ensuring that the center of gravity of the aircraft is always within a reasonable range in complex scenarios, and ensuring flight safety and data accuracy.

[0080] The aircraft test flight multi-scenario center of gravity adjustment method and system proposed in the present application mainly complete dynamic and accurate adjustment of the center of gravity of the aircraft for different scenarios in the flight attitude of the aircraft through the center of gravity adjustment system, as follows:

[0081] 1) Aircraft roll flight state

[0082] When the roll angle of the aircraft is greater than the roll angle threshold x, the system determines that the aircraft is in a large roll angle flight scene, as shown in Figure 4 The system closes the water tank interconnection 1, i.e. the electromagnetic valves between the No. 1 water tank and the No. 5 water tank, between the No. 2 water tank and the No. 6 water tank, between the No. 3 water tank and the No. 7 water tank, between the No. 4 water tank and the No. 8 water tank, between the No. 9 water tank and the No. 13 water tank, between the No. 10 water tank and the No. 14 water tank, between the No. 11 water tank and the No. 15 water tank, and between the No. 12 water tank and the No. 16 water tank, to prevent the water in the water tank on one side of the aircraft from overflowing due to excessive water volume. When the roll angle of the aircraft is less than or equal to the roll angle threshold x, the system determines that the aircraft is in a small roll angle flight scene, and opens the water tank interconnection horizontal pipe electromagnetic valve 1. At this time, the system can make adjustment determination in the pitch attitude.

[0083] 2) Aircraft pitch flight state

[0084] As shown in Figure 3 When the aircraft is in a small pitch angle flight scene, the outer circulation is preferred, i.e. the No. 1 water tank, the No. 2 water tank, the No. 5 water tank, and the No. 6 water tank of the front water tank group and the No. 11 water tank, the No. 12 water tank, the No. 15 water tank, and the No. 16 water tank of the rear water tank group participate in circulation. When the outer circulation is still insufficient to reach the test target center of gravity, the inner circulation is used for supplementary adjustment. When the aircraft is in a medium pitch angle flight scene, the inner circulation is preferred, i.e. the No. 3 water tank, the No. 4 water tank, the No. 7 water tank, and the No. 8 water tank of the front water tank group and the No. 9 water tank, the No. 10 water tank, the No. 13 water tank, and the No. 14 water tank of the rear water tank group participate in circulation. When the inner circulation is still insufficient to reach the test target center of gravity, the outer circulation is used for supplementary adjustment.

[0085] 3) Large angle flight state intelligent balance

[0086] When the aircraft is in a large angle pitch or roll flight scene, the system will adjust the water volume in the front and rear water tanks by controlling the pump and the valve to avoid the overflow caused by excessive water volume in a water tank. As shown in Figure 5 , taking the No. 14 water tank as an example, the system detects that the liquid level of the No. 14 water tank is too high and there is a risk of overflow. The system will open the related water pump 5, electric ball valve 4, and No. 14 water tank electromagnetic valve. At the same time, it is detected that the liquid level of the No. 7 water tank is low, so the system will open the No. 7 water tank electromagnetic valve to adjust the water in the No. 14 water tank to the No. 7 water tank. Similarly, when the water volume in the front water tank is too high, the water in the water tank with too high liquid level can be adjusted to the water tank with lower liquid level in the rear part by reversing the water pump 5.

[0087] The specific embodiments of the present application have been described, but it will be understood by those skilled in the art that the above specific embodiments do not constitute a limitation on the present application, and various modifications can be made on the basis of the above disclosure without departing from the scope of the present application.

Claims

1. A method for adjusting the center of gravity of an aircraft in multiple flight scenarios, comprising: receiving target center of gravity data required for flight testing and attitude data of the aircraft, the attitude data of the aircraft including a roll angle and a pitch angle of the aircraft; determining whether the roll angle of the aircraft is greater than a roll angle threshold value; when the roll angle of the aircraft is greater than the roll angle threshold value, determining that the aircraft is in a large roll angle flight scenario, closing a cross-pipe valve between water tanks, and suspending adjustment of the center of gravity; when the roll angle of the aircraft is less than or equal to the roll angle threshold value, determining that the aircraft is in a small roll angle flight scenario, opening the cross-pipe valve between water tanks, and determining whether the pitch angle of the aircraft is less than a first pitch angle threshold value; when the pitch angle of the aircraft is less than the first pitch angle threshold value, determining that the aircraft is in a small pitch angle flight scenario, and adjusting the center of gravity in an out-tank circulation mode; when the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold value and less than a second pitch angle threshold value, wherein the second pitch angle threshold value is greater than the first pitch angle threshold value, determining that the aircraft is in a medium pitch angle flight scenario, and adjusting the center of gravity in an in-tank circulation mode; when the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold value, determining that the aircraft is in a large pitch angle flight scenario, and suspending adjustment of the center of gravity; the aircraft comprises a front water tank group and a rear water tank group, the front water tank group comprises a front row of water tanks and a rear row of water tanks, the rear water tank group also comprises a front row of water tanks and a rear row of water tanks, and the cross-pipe valve refers to a valve arranged on a cross-pipe between two water tanks in each row; the out-tank circulation mode refers to circulation between the front row of water tanks of the front water tank group and the rear row of water tanks of the rear water tank group, and the in-tank circulation mode refers to circulation between the rear row of water tanks of the front water tank group and the front row of water tanks of the rear water tank group.

2. The method of claim 1, wherein, The front water tank group and the rear water tank group are connected by two side main pipelines, and a valve is arranged between the inlet of each main pipeline and the water tank.

3. The method of claim 1, wherein, When the aircraft is in the large roll angle flight scenario or the large pitch angle flight scenario, water level information of the water tanks is received, and if the water level of a water tank on one side is too high, the water in the water tank with the high water level is transferred to a water tank with a lower water level. 4.A system for adjusting the center of gravity of an aircraft in multiple flight scenarios, comprising: a general control unit configured to receive target center of gravity data required for flight testing and attitude data of the aircraft, the attitude data of the aircraft including a roll angle and a pitch angle of the aircraft; the general control unit is further configured to: determine whether the roll angle of the aircraft is greater than a roll angle threshold value; when the roll angle of the aircraft is greater than the roll angle threshold value, determine that the aircraft is in a large roll angle flight scenario, close a cross-pipe valve between water tanks, and suspend adjustment of the center of gravity; when the roll angle of the aircraft is less than or equal to the roll angle threshold value, determine that the aircraft is in a small roll angle flight scenario, open the cross-pipe valve between water tanks, and determine whether the pitch angle of the aircraft is less than a first pitch angle threshold value; when the pitch angle of the aircraft is less than the first pitch angle threshold value, determine that the aircraft is in a small pitch angle flight scenario, and adjust the center of gravity in an out-tank circulation mode; When the pitch angle of the aircraft is greater than or equal to the first pitch angle threshold and less than the second pitch angle threshold, wherein the second pitch angle threshold is greater than the first pitch angle threshold, it is determined that the aircraft is in a medium pitch angle flight scenario, and the water tank inner circulation mode is adopted for the center of gravity adjustment; When the pitch angle of the aircraft is greater than or equal to the second pitch angle threshold, it is determined that the aircraft is in a large pitch angle flight scenario, and the center of gravity adjustment is suspended; The aircraft test flight multi-scenario center of gravity adjustment system comprises a front water tank group and a rear water tank group, the front water tank group comprises front and rear rows of water tanks, the rear water tank group also comprises front and rear rows of water tanks, and the water tank inter-row pipe valve is a valve arranged on a pipe between two water tanks in each row; The water tank outer circulation mode refers to that the front row of water tanks of the front water tank group and the rear row of water tanks of the rear water tank group participate in circulation, and the water tank inner circulation mode refers to that the rear row of water tanks of the front water tank group and the front row of water tanks of the rear water tank group participate in circulation.

5. The aircraft flight test multi-scenario CG adjustment system of claim 4, wherein, The front water tank group and the rear water tank group are connected by two side main pipes, and a valve is arranged between the entering part of each main pipe and the water tank.

6. The aircraft flight test multi-scenario CG adjustment system of claim 4, wherein, The aircraft test flight multi-scenario center of gravity adjustment system further comprises a liquid level sensor arranged in each water tank, and the total control unit is further configured to: When the aircraft is in a large roll angle flight scenario or a large pitch angle flight scenario, the water tank liquid level information provided by the liquid level sensor is received, and if the liquid level in a certain water tank on one side is too high, the water in the water tank with the too high liquid level is transferred to a water tank with a lower liquid level.

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