Airplane test flight multi-scene gravity center adjusting method and system

Abstract

The invention relates to an aircraft test flight multi-scene gravity center adjusting method and system. The method comprises the following steps: receiving target gravity center data required by test flight and a rolling angle and a pitching angle of an aircraft; judging whether the rolling angle is greater than a rolling angle threshold value or not; when the rolling angle is larger than the rolling angle threshold value, the transverse pipe valve between the water tanks is closed, and gravity center adjustment is suspended; when the rolling angle is smaller than or equal to the rolling angle threshold value, a transverse pipe valve between the water tanks is opened, and whether the pitching angle is smaller than a first pitching angle threshold value or not is judged; when the pitching angle is smaller than a first pitching angle threshold value, the gravity center is adjusted in a water tank external circulation mode; when the pitching angle is larger than or equal to a first pitching angle threshold value and smaller than a second pitching angle threshold value, the second pitching angle threshold value is larger than the first pitching angle threshold value, and gravity center adjustment is conducted in a water tank internal circulation mode; when the pitching angle is larger than or equal to the second pitching angle threshold value, the gravity center adjustment is suspended.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft flight test, and in particular to a method and system for adjusting the center of gravity in multiple scenarios of aircraft flight test. Background Art

[0002] The center of gravity position of an aircraft plays an extremely critical role in the flight performance, stability, controllability and safety of an aircraft (especially a large civil aircraft). Ensuring the safety and performance of the aircraft under various extremely complex working conditions is one of the core tasks of large civil aircraft test flights. Therefore, a center of gravity adjustment system is installed to adjust the real-time center of gravity of the aircraft to verify the relevant performance of the aircraft. The center of gravity adjustment system calculates the real-time weight and center of gravity of the aircraft based on ground weight information, fuel consumption information, landing gear status, weight status of the center of gravity adjustment system, etc., and can adjust or maintain the center of gravity of the aircraft by controlling the transmission of weight water in the front and rear 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 cabin to achieve limited center of gravity adjustment. This method is relatively simple in principle. However, when faced with complex changes in flight attitude during test flights, this adjustment method is difficult to achieve rapid and accurate differentiated adjustment of the aircraft's center of gravity.

[0004] As flight test technology develops towards refinement and comprehensiveness, the requirements for the accuracy and flexibility of center of gravity adjustment are becoming increasingly higher. Traditional center of gravity adjustment methods can hardly meet the needs of dynamic adjustment of the center of gravity under a variety of complex flight posture combinations, and cannot simulate more diverse and extreme center of gravity distribution scenarios, thus restricting the comprehensive and in-depth exploration and verification of aircraft performance in flight test work. Summary of the invention

[0005] An object of the present invention is to provide a method and system for adjusting the center of gravity of an aircraft test flight in multiple scenarios, which can overcome the shortcomings of the prior art, adapt to a variety of complex flight attitude scenarios, and achieve rapid and accurate differentiated adjustment of the center of gravity of the aircraft.

[0006] The above objectives of the present invention are achieved by a method for adjusting the center of gravity of an aircraft test flight in multiple scenarios, the method comprising:

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

[0008] Determine whether the aircraft's roll angle is greater than the roll angle threshold;

[0009] When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, the cross pipe valve between the water tanks 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, the aircraft is determined to be in a small roll angle flight scenario, the cross pipe valve between the water tanks 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, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and the water tank internal circulation method is used to supplement the center of gravity adjustment when necessary;

[0012] When the pitch angle of the aircraft is greater than or equal to a 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, it is determined that the aircraft is in a medium pitch angle flight scenario, and the center of gravity is adjusted by using a water tank internal circulation method, and if necessary, a water tank external circulation method is used to supplement the center of gravity adjustment;

[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 scheme, the aircraft test flight multi-scenario center of gravity adjustment method of the present invention can achieve the following beneficial technical effects: it can adapt to a variety of complex flight attitude scenarios and can achieve fast and accurate differentiated adjustment of the aircraft's center of gravity.

[0015] Preferably, the aircraft includes a front water tank group and a rear water tank group, the front water tank group includes a front drainage tank and a rear drainage tank, the rear water tank group also includes a front drainage tank and a rear drainage tank, and the inter-tank cross pipe valve refers to a valve arranged on the cross pipe between two water tanks in each row.

[0016] Preferably, the water tank external circulation mode refers to the circulation between the front drainage tank of the front water tank group and the rear drainage tank of the rear water tank group, and the water tank internal circulation mode refers to the circulation between the rear drainage tank of the front water tank group and the front drainage tank of the rear water tank group.

[0017] Preferably, the front water tank group and the rear water tank group are connected by main pipes on both sides, and a valve is provided between the inlet of each main pipe and the water tank.

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

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

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

[0021] The master control unit is also configured as:

[0022] Determine whether the aircraft's roll angle is greater than the roll angle threshold;

[0023] When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, the cross pipe valve between the water tanks is closed, and the center of gravity adjustment is suspended;

[0024] When the roll angle of the aircraft is less than or equal to the roll angle threshold, the aircraft is determined to be in a small roll angle flight scenario, the cross pipe valve between the water tanks is opened, and it is determined whether the pitch angle of the aircraft is less than the first pitch angle threshold;

[0025] When the pitch angle of the aircraft is less than the first pitch angle threshold, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and the water tank internal circulation method is used to supplement the center of gravity adjustment when necessary;

[0026] When the pitch angle of the aircraft is greater than or equal to a 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, it is determined that the aircraft is in a medium pitch angle flight scenario, and the center of gravity is adjusted by using a water tank internal circulation method, and if necessary, a water tank external circulation method is used to supplement the center of gravity adjustment;

[0027] 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.

[0028] According to the above technical scheme, the aircraft test flight multi-scenario center of gravity adjustment system of the present invention can achieve the following beneficial technical effects: it can adapt to a variety of complex flight attitude scenarios and can achieve fast and accurate differentiated adjustment of the aircraft's center of gravity.

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

[0030] Preferably, the water tank external circulation mode refers to the circulation between the front drainage tank of the front water tank group and the rear drainage tank of the rear water tank group, and the water tank internal circulation mode refers to the circulation between the rear drainage tank of the front water tank group and the front drainage tank of the rear water tank group.

[0031] Preferably, the front water tank group and the rear water tank group are connected by main pipes on both sides, and a valve is provided between the inlet of each main pipe and the water tank.

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

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

[0034] Figure 1 This is a principle block diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention;

[0035] Figure 2 This is a flow chart of the method for adjusting the center of gravity in multiple scenarios of an aircraft test flight according to the present invention;

[0036] Figure 3 This is a mechanical structure diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention;

[0037] Figure 4 It is an operation diagram of a large roll angle flight scenario of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention;

[0038] Figure 5 This is a diagram showing an example of intelligent adjustment for large-angle flight scenarios of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention.

[0039] Reference numerals list

[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] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to be concise and clear, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means, and should not be understood as insufficient content of this disclosure.

[0047] Unless otherwise defined, the technical or scientific terms used in the claims and the specification shall have the usual meaning understood by persons with ordinary skills in the technical field to which the invention belongs. The words "first", "second" and similar words used in the patent application specification and the claims of the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "One" or "one" and other similar words do not indicate a quantitative limitation, but indicate the existence of at least one. "Include" or "comprises" and other similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalent elements, and do not exclude other elements or objects. "Connected" or "connected" and other similar words are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0048] Figure 1 This is a principle block diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention; Figure 2 This is a flow chart of the method for adjusting the center of gravity in multiple scenarios of an aircraft test flight according to the present invention; Figure 3 This is a mechanical structure diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention; Figure 4 It is an operation diagram of a large roll angle flight scenario of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention; Figure 5 This is a diagram showing an example of intelligent adjustment for large-angle flight scenarios of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention.

[0049] The technical solution adopted by the present invention is: after entering the test flight stage, the center of gravity adjustment system identifies the aircraft's heading data, determines the aircraft's flight attitude (roll, pitch) through the control system, combines the system's own water tank liquid level, pipeline flow and other information, controls the water pump, valves and other components in the system, and adjusts the aircraft's center of gravity to the target center of gravity of the test flight test in different scenarios, while ensuring the safety of the aircraft.

[0050] Figure 1 This is a principle block diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention. Figure 1 As shown, the master control unit receives the target center of gravity required for the test flight from the cabin input device on the aircraft, and at the same time extracts information through the aircraft bus to identify the aircraft's posture and the liquid level, flow and other information provided by the system's own sensors, and controls the system's water pumps and valves to open and close, thereby achieving the purpose of center of gravity adjustment.

[0051] Figure 3 The mechanical structure block diagram of the aircraft test flight multi-scenario center of gravity adjustment system of the present invention. The aircraft test flight multi-scenario center of gravity adjustment system mainly includes a front water tank group (such as a front cabin water tank group), a rear water tank group (such as a rear cabin water tank group), a water pump, a valve, etc. The front water tank group includes a front drainage tank and a rear drainage tank, and the rear water tank group also includes a front drainage tank and a rear drainage tank. For example, each water tank group consists of four rows of eight water tanks, the front two row water tanks are the front drainage tanks, and the rear two row water tanks are the rear drainage tanks. A liquid level sensor 3 is provided inside each water tank. The front water tank group and the rear water tank group are connected by main pipes on both sides, and a solenoid valve 1 (which can be called an inlet valve, the solenoid valve is only a preferred form, and other forms of valves can also be used) is provided between the inlet of each main pipe and the water tank to control the main pipe water to enter the water tank. Each row of two water tanks 2 is connected by a cross pipe, and a solenoid valve 1 (which can be called a cross pipe valve between water tanks, the solenoid valve is only a preferred form, and other forms of valves can also be used) is provided on the cross pipe to control the flow of water between each row of water tanks 2. The main pipes on both sides are provided with electric ball valves 4 (electric ball valves are only a preferred form, other forms of valves can also be used), water pumps 5, flow sensors 6, etc. It should be noted that the transverse direction used in this article refers to the direction perpendicular to the longitudinal direction (heading) of the aircraft, and the transverse pipe refers to the pipeline arranged transversely.

[0052] like Figures 1 to 4 As shown, the method for adjusting the center of gravity of an aircraft test flight in multiple scenarios according to the present invention includes:

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

[0054] Determine whether the roll angle of the aircraft is greater than a roll angle threshold (eg, roll angle threshold x);

[0055] When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, and the cross pipe valve between the water tanks is closed to prevent the water in one water tank from flowing to the other side, causing the other side's water 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, the aircraft is determined to be in a small roll angle flight scenario, the cross pipe valve between the water tanks is opened, and it is determined whether the pitch angle of the aircraft is less than a first pitch angle threshold (for example, the first pitch angle threshold y);

[0057] When the pitch angle of the aircraft is less than the first pitch angle threshold, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and when necessary (that is, when the external circulation is still insufficient to reach the test target center of gravity), the water tank internal circulation method is used to supplement the center of gravity adjustment;

[0058] 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 (e.g., the second pitch angle threshold z), 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 center of gravity is adjusted by using the water tank internal circulation method, and when necessary (i.e., when the internal circulation is still insufficient to reach the test target center of gravity), the water tank external circulation method is used to supplement the center of gravity adjustment;

[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 to 32 degrees, and more preferably, the roll angle threshold x is 30 degrees.

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

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

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

[0064] like Figure 5 As shown, when the aircraft is in a large roll angle flight scenario (i.e., the roll angle is greater than the roll angle threshold x) or a large pitch angle flight scenario (i.e., the pitch angle is greater than the second pitch angle threshold z), the water tank level information is received. If the liquid level in a water tank on one side is too high, the water in the water tank with too high liquid level is transferred forward or backward to the water tank with lower liquid level by opening the water pump 5, the electric ball valve 4 and the solenoid valve of the relevant water tank.

[0065] like Figures 1 to 4 As shown, the aircraft test flight multi-scenario center of gravity adjustment system according to the present invention includes:

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

[0067] The master control unit is also configured as:

[0068] Determine whether the aircraft's roll angle is greater than the roll angle threshold;

[0069] When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, the cross pipe valve between the water tanks is closed, and the center of gravity adjustment is suspended;

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

[0071] When the pitch angle of the aircraft is less than the first pitch angle threshold, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and the water tank internal circulation method is used to supplement the center of gravity 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, and the center of gravity is adjusted by using the water tank internal circulation method, and the water tank external circulation method is used to supplement the 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 invention compared with the prior art are:

[0075] 1) Improve flight safety. The present invention accurately identifies the aircraft's attitude and takes timely measures to avoid flight safety problems caused by an imbalance in the aircraft's center of gravity. In particular, when the aircraft is at a large roll angle or pitch angle, the system automatically turns off the relevant adjustment function, effectively preventing errors in center of gravity adjustment caused by excessively large aircraft attitude angles.

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

[0077] 3) Improve adjustment efficiency and accuracy. The present invention preferentially adopts external circulation and internal circulation for small-angle and medium-angle pitch flights, respectively, and adopts a supplementary circulation method to improve the efficiency of center of gravity adjustment when the main circulation is insufficient. Especially in the flight state with a small pitch angle, the water pump head is high, and the use of external circulation adjustment generates a larger force arm, which can adjust the center of gravity position of the aircraft more quickly and effectively, improve the adjustment efficiency, and ensure the accuracy of center of gravity adjustment.

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

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

[0080] The aircraft test flight multi-scenario center of gravity adjustment method and system proposed in the present invention mainly completes the dynamic and precise adjustment of the aircraft center of gravity according to different scenarios under the aircraft flight attitude through the center of gravity adjustment system, as follows:

[0081] 1) Aircraft rolling flight status

[0082] When the aircraft roll angle is greater than the roll angle threshold x, the system determines that the aircraft is in a large roll angle flight scenario, such as Figure 4 As shown, the system closes water tank room 1, that is, the solenoid valves between water tanks 1 and 5, between water tanks 2 and 6, between water tanks 3 and 7, between water tanks 4 and 8, between water tanks 9 and 13, between water tanks 10 and 14, between water tanks 11 and 15, and between water tanks 12 and 16, to prevent overflow from excessive water in the water tanks on one side of the aircraft. When the aircraft roll-on angle is less than or equal to the roll angle threshold x, the system determines that the aircraft is in a small roll angle flight scenario and opens the cross pipe solenoid valve 1 between the water tanks. At this time, the system can make adjustments under the pitch attitude.

[0083] 2) Aircraft pitch flight status

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

[0085] 3) Intelligent balance in large-angle flight state

[0086] When the aircraft is in a high-angle pitch or roll flight scenario, the system will adjust the water volume in the front and rear water tanks by controlling the pumps and valves to prevent overflow from occurring due to excessive water volume in one of the water tanks. Figure 5 As shown, taking water tank No. 14 as an example, if the system detects that the liquid level of water tank No. 14 is too high and there is a risk of overflow, the system will open the relevant water pump 5, electric ball valve 4, and solenoid valve of water tank No. 14. At the same time, if the liquid level of water tank No. 7 is detected to be low, the system will open the solenoid valve of water tank No. 7 to transfer the water in water tank No. 14 to water tank No. 7. Similarly, when the water volume in the front water tank is too high, the water in a water tank with too high liquid level in the front water tank can be transferred to a water tank with lower liquid level in the rear water tank by reversing the water pump 5.

[0087] The above describes the specific embodiments of the present invention, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation of the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. A method for adjusting the center of gravity of an aircraft in multiple scenarios during flight test, comprising: Receiving target center of gravity data and aircraft attitude data required for the test flight, wherein the aircraft attitude data includes the roll angle and pitch angle of the aircraft; Determine whether the aircraft's roll angle is greater than the roll angle threshold; When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, the cross pipe valve between the water tanks is closed, and the center of gravity adjustment is suspended; When the roll angle of the aircraft is less than or equal to the roll angle threshold, the aircraft is determined to be in a small roll angle flight scenario, the cross pipe valve between the water tanks is opened, and it is determined whether the pitch angle of the aircraft is less than the first pitch angle threshold; When the pitch angle of the aircraft is less than the first pitch angle threshold, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and the water tank internal circulation method is used to supplement the center of gravity adjustment when necessary; When the pitch angle of the aircraft is greater than or equal to a 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, it is determined that the aircraft is in a medium pitch angle flight scenario, and the center of gravity is adjusted by using a water tank internal circulation method, and if necessary, a water tank external circulation method is used to supplement 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.

2. The method for adjusting the center of gravity of an aircraft test flight in multiple scenarios according to claim 1, characterized in that: The aircraft includes a front water tank group and a rear water tank group, the front water tank group includes a front drainage tank and a rear drainage tank, the rear water tank group also includes a front drainage tank and a rear drainage tank, and the inter-tank cross pipe valve refers to a valve arranged on the cross pipe between two water tanks in each row.

3. The aircraft test flight multi-scenario center of gravity adjustment method according to claim 2, characterized in that: The water tank external circulation mode refers to the circulation between the front drainage tank of the front water tank group and the rear drainage tank of the rear water tank group, and the water tank internal circulation mode refers to the circulation between the rear drainage tank of the front water tank group and the front drainage tank of the rear water tank group.

4. The method for adjusting the center of gravity of an aircraft test flight in multiple scenarios according to claim 2, characterized in that: The front water tank group and the rear water tank group are connected by main pipes on both sides, and a valve is provided between the inlet of each main pipe and the water tank.

5. The method for adjusting the center of gravity of an aircraft test flight in multiple scenarios as claimed in claim 2, characterized in that: When the aircraft is in a large roll angle flight scenario or a large pitch angle flight scenario, the water tank level information is received. If the liquid level in a water tank on one side is too high, the water in the water tank with the high liquid level is transferred forward or backward to the water tank with the lower liquid level.

6. An aircraft test flight multi-scenario center of gravity adjustment system, comprising: A master control unit, the master control unit being configured to receive target center of gravity data required for the test flight and aircraft attitude data, the aircraft attitude data including the roll angle and pitch angle of the aircraft; The master control unit is also configured as: Determine whether the aircraft's roll angle is greater than the roll angle threshold; When the aircraft's roll angle is greater than the roll angle threshold, the aircraft is judged to be in a large roll angle flight scenario, the cross pipe valve between the water tanks is closed, and the center of gravity adjustment is suspended; When the roll angle of the aircraft is less than or equal to the roll angle threshold, the aircraft is determined to be in a small roll angle flight scenario, the cross pipe valve between the water tanks is opened, and it is determined whether the pitch angle of the aircraft is less than the first pitch angle threshold; When the pitch angle of the aircraft is less than the first pitch angle threshold, the aircraft is judged to be in a small pitch angle flight scenario, and the center of gravity is adjusted by using the water tank external circulation method, and the water tank internal circulation method is used to supplement the center of gravity adjustment when necessary; When the pitch angle of the aircraft is greater than or equal to a 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, it is determined that the aircraft is in a medium pitch angle flight scenario, and the center of gravity is adjusted by using a water tank internal circulation method, and if necessary, a water tank external circulation method is used to supplement 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.

7. The aircraft test flight multi-scenario center of gravity adjustment system as claimed in claim 6, characterized in that: The aircraft test flight multi-scenario center of gravity adjustment system includes a front water tank group and a rear water tank group. The front water tank group includes a front drainage tank and a rear drainage tank. The rear water tank group also includes a front drainage tank and a rear drainage tank. The inter-tank cross pipe valve refers to a valve arranged on the cross pipe between two water tanks in each row.

8. The aircraft test flight multi-scenario center of gravity adjustment system as claimed in claim 7, characterized in that: The water tank external circulation mode refers to the circulation between the front drainage tank of the front water tank group and the rear drainage tank of the rear water tank group, and the water tank internal circulation mode refers to the circulation between the rear drainage tank of the front water tank group and the front drainage tank of the rear water tank group.

9. The aircraft test flight multi-scenario center of gravity adjustment system as claimed in claim 7, characterized in that: The front water tank group and the rear water tank group are connected by main pipes on both sides, and a valve is provided between the inlet of each main pipe and the water tank.

10. The aircraft test flight multi-scenario center of gravity adjustment system according to claim 7, characterized in that: The aircraft test flight multi-scenario center of gravity adjustment system further includes a liquid level sensor disposed in each water tank, and the master control unit is further configured as follows: When the aircraft is in a large roll angle flight scenario or a large pitch angle flight scenario, the water tank level information provided by the liquid level sensor is received. If the liquid level in a water tank on one side is too high, the water in the water tank with the high liquid level is transferred forward or backward to the water tank with the lower liquid level.

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