Method and device for calculating ground load during jacking of single-side main landing gear of airplane

Abstract

The invention provides a method and a device for calculating a ground load when a single-side main landing gear of an aircraft is jacked up, and belongs to the technical field of ground load calculation of aircraft landing gear, the method comprises the following steps: constructing a hypothesis condition, establishing a ground load calculation theory when the single-side main landing gear is jacked up based on the hypothesis condition, and calculating the ground load when the single-side main landing gear is jacked up; a rotation angle expression and an expression of ground vertical bearing reaction borne by the left side main landing gear and the right side main landing gear after jacking are obtained; determining parameters required for calculation of the jacking state of the single-side main landing gear of the aircraft, and obtaining numerical values of the required parameters; and calculating the ground load when the single-side main landing gear is jacked up according to the rotation angle expression, the expression of the ground vertical bearing reaction borne by the left side main landing gear and the right side main landing gear after the single-side main landing gear is jacked up and the numerical values of the required parameters.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft landing gear ground load calculation, and particularly relates to a method and device for calculating ground load when a single-side main landing gear of an aircraft is jacked up. BACKGROUND

[0002] When the main landing gear of an aircraft is maintained on the ground, for example, the tire of the wheel is replaced, the main landing gear on the side needs to be jacked up by a jack or other equipment. As the jacking height increases, the fuselage will be deflected to a certain extent, and the center of gravity of the aircraft will shift to the other side of the main landing gear. Correspondingly, this situation will cause the loads of the left and right main landing gears to change. The load, as one of the aircraft ground maintenance loads, needs to be considered in the design stage and needs to be calculated to obtain a relatively accurate load for the structural design of the main landing gear. SUMMARY

[0003] The purpose of the present application is to provide a method and device for calculating ground load when a single-side main landing gear of an aircraft is jacked up, so as to solve or alleviate at least one problem in the background art.

[0004] In one aspect, the technical solution of the present application is: a method for calculating ground load when a single-side main landing gear of an aircraft is jacked up, comprising:

[0005] constructing a hypothetical condition, establishing a single-side main landing gear jacking-up ground load calculation theory based on the hypothetical condition, obtaining a rotation angle expression and a ground vertical support reaction force expression of the left and right main landing gears after jacking up;

[0006] determining parameters required for calculating the single-side main landing gear jacking-up state, and obtaining numerical values of the required parameters;

[0007] calculating the ground load when the single-side main landing gear is jacked up according to the rotation angle expression, the ground vertical support reaction force expression of the left and right main landing gears after jacking up, and the numerical values of the required parameters.

[0008] Preferably, the hypothetical condition is that the elastic deformation of the aircraft body and the pitching motion of the aircraft body when the single-side main landing gear is jacked up are not considered, and a triangle composed of the center of gravity of the aircraft body, the left main landing gear contact point, and the right main landing gear contact point is regarded as a geometrically invariant figure.

[0009] Preferably, the process of establishing a single-side main landing gear jacking-up ground load calculation theory based on the hypothetical condition to obtain a rotation angle expression and a ground vertical support reaction force expression of the two main landing gears comprises:

[0010] placing a triangle OAB composed of the center of gravity A of the aircraft body, the left main landing gear contact point O, and the right main landing gear contact point B in the OYZ coordinate system, in which the origin is O, the Y direction points to the right wing of the aircraft, and the Z direction is vertically upward;

[0011] Suppose the unilateral main landing gear jacking point is located at the right main landing gear grounding point B, when the jacking distance is Δ, the rotation angle of the triangle OAB around point O is θ, and the calculation formula of the rotation angle θ is:

[0012] In the formula: is the length of the line segment OB, that is, the main wheel track;

[0013] Suppose the initial coordinates of the body center of gravity A point are (y 0A , z 0A ), and the initial coordinate values of the body center of gravity A point are respectively: In the formula: h is the distance between point A and the line segment OB, that is, the initial height of the aircraft center of gravity from the ground;

[0014] Suppose the coordinates of the body center of gravity A point after jacking are (y 1A , z 1A ), according to the rotation axis theorem, the coordinate values of the body center of gravity A point after jacking are calculated from the initial coordinates (y 0A , z 0A ) of the body center of gravity A point and the rotation angle θ: ;

[0015] Similarly, the coordinate values (y 1B , z 1B ) of the right main landing gear grounding point B after jacking are:

[0016] ;

[0017] After obtaining the Y-axis coordinate y 1A of the body center of gravity A point after jacking, the horizontal offset of the aircraft center of gravity is calculated: ;

[0018] According to the moment balance, the horizontal distance between the body center of gravity A point and the right main landing gear grounding point B after jacking is ;

[0019] After arrangement, it is obtained that ;

[0020] According to the moment balance, the horizontal distance between point O and the right main landing gear grounding point B after jacking is: ;

[0021] Ignoring the horizontal ground friction, according to the moment balance relationship around the right main landing gear grounding point B, the vertical ground support reaction force on the left main landing gear after jacking is: ​​​, wherein: G is the total weight of the airplane borne by the two main landing gears;

[0022] According to the vertical force balance, the ground vertical support reaction force borne by the right main landing gear is:

[0023] .

[0024] Preferably, the parameters required for calculating the single-side main landing gear jacking state of the airplane include: the main wheel track , the height of the center of gravity from the ground h, the jacking height Δ, and the total weight of the airplane borne by the two main landing gears G;

[0025] The main wheel track is obtained from the list of airplane overall design parameters;

[0026] The height of the center of gravity from the ground h is obtained through theoretical calculation or through the measured center of gravity position according to the airplane loading state;

[0027] The jacking height Δ is obtained through theoretical calculation or through the distance between the jacking point and the ground;

[0028] The total weight of the airplane borne by the two main landing gears G is obtained through theoretical calculation or through the airplane weight and the center of gravity measurement program.

[0029] Preferably, the process of calculating the ground load when the single-side main landing gear is jacked according to the rotation angle expression and the ground vertical support reaction force expressions borne by the two main landing gears and the numerical values of the required parameters includes:

[0030] The rotation angle θ is calculated according to the main wheel track , the jacking height Δ, and the rotation angle expression;

[0031] Then, the ground vertical support reaction force borne by the left main landing gear after jacking and the ground vertical support reaction force borne by the right main landing gear after jacking are respectively calculated according to the rotation angle θ, the main wheel track , the height of the center of gravity from the ground h, the total weight of the airplane borne by the two main landing gears G, and the ground vertical support reaction force expressions borne by the left and right main landing gears after jacking.

[0032] On the other hand, the technical solution provided by the present application is: a device for calculating the ground load when the single-side main landing gear of an airplane is jacked, comprising:

[0033] An expression construction module is configured to construct a hypothetical condition, establish a single-side main landing gear jacking ground load calculation theory based on the hypothetical condition, obtain a rotation angle expression, and obtain a ground vertical support reaction force expression borne by the left and right main landing gears after jacking;

[0034] a parameter acquisition module, configured to determine parameters required for calculating a single-side main landing gear jacking state of the aircraft and acquire values of the required parameters;

[0035] a ground load calculation module, configured to calculate a ground load when the single-side main landing gear is jacked up according to the rotation angle expression and expressions of vertical ground support reaction forces on the left and right main landing gears after jacking up and the values of the required parameters.

[0036] Preferably, the assumption condition is that a triangle formed by the center of gravity of the aircraft, the left main landing gear contact point and the right main landing gear contact point is regarded as a geometrically invariant figure without considering elastic deformation of the aircraft body and pitching motion of the aircraft body at the moment when the single-side main landing gear is jacked up.

[0037] Preferably, the process of establishing a ground load calculation theory when the single-side main landing gear is jacked up based on the assumption condition and obtaining the rotation angle expression and expressions of vertical ground support reaction forces on the left and right main landing gears includes:

[0038] placing the triangle OAB formed by the center of gravity A of the aircraft body, the left main landing gear contact point O and the right main landing gear contact point B in the OYZ coordinate system, in which the origin is O, the Y direction points to the right wing of the aircraft and the Z direction is vertically upward;

[0039] assuming that the single-side main landing gear jacking point is located at the right main landing gear contact point B, and the rotation angle of the triangle OAB around point O is θ when the jacking distance is Δ, the calculation formula of the rotation angle θ is:

[0040] in which: is the length of the line segment OB, i.e. the main wheel track;

[0041] assuming that the initial coordinates of the center of gravity A of the aircraft body are (y 0A , z 0A ), the initial coordinate values of the center of gravity A of the aircraft body are: , in which: h is the distance between point A and the line segment OB, i.e. the initial height of the center of gravity of the aircraft from the ground;

[0042] assuming that the coordinates of the center of gravity A of the aircraft body after jacking up are (y 1A , z 1A ), the coordinate values of the center of gravity A of the aircraft body after jacking up are calculated from the initial coordinates (y 0A , z 0A ) of the center of gravity A of the aircraft body and the rotation angle θ according to the rotation axis theorem: , ;

[0043] Similarly, the coordinate values (y 1B , z 1B):

[0044] , ;

[0045] After the Y coordinate y of the center of gravity A of the aircraft is obtained after jacking up 1A , the horizontal offset of the center of gravity of the aircraft is calculated: ;

[0046] According to the moment balance, the horizontal distance between the center of gravity A of the aircraft after jacking up and the right landing gear contact point B is ;

[0047] After sorting, we get ;

[0048] According to the moment balance, the horizontal distance between the point O after jacking up and the right landing gear contact point B is: ;

[0049] Ignoring the horizontal ground friction, according to the moment balance around the right landing gear contact point B, the vertical ground reaction force on the left landing gear after jacking up is: , wherein: G is the total weight of the aircraft supported by the two landing gears;

[0050] According to the vertical force balance, the vertical ground reaction force on the right landing gear is:

[0051] .

[0052] Preferably, the parameters required for calculating the single-side landing gear jacking-up state of the aircraft include: the main wheel distance , the height of the center of gravity from the ground h, the jacking-up height Δ, and the total weight of the aircraft G supported by the two landing gears;

[0053] The main wheel distance is obtained from the aircraft overall design parameter list;

[0054] The height of the center of gravity from the ground h is obtained by theoretical calculation or by measuring the center of gravity position according to the aircraft loading state;

[0055] The jacking-up height Δ is obtained by theoretical calculation or by measuring the distance between the jacking-up point and the ground;

[0056] The total weight of the aircraft G supported by the two landing gears is obtained by theoretical calculation or by the aircraft weight and center of gravity measurement program.

[0057] Preferably, the process of calculating the ground load when the single-side landing gear is jacked up according to the rotation angle expression and the vertical ground reaction force expression of the two landing gears and the numerical values of the required parameters includes:

[0058] According to the main wheel track And the rotation angle expression calculation of the lifting height Δ and the rotation angle;

[0059] Then, according to the rotation angle θ and the main wheel track , the center of gravity height h, the total weight of the aircraft G supported by the two side main landing gears, and the ground vertical support reaction expression of the left and right side main landing gears after lifting, the ground vertical support reaction of the left side main landing gear after lifting and the ground vertical support reaction of the right side main landing gear after lifting are calculated respectively.

[0060] In a third aspect, the application provides an electronic device, comprising:

[0061] One or more processors;

[0062] Memory;

[0063] One or more application programs stored in the memory and configured to be executed by the one or more processors, the one or more application programs being configured for implementing the calculation of the ground load of the single side main landing gear of the aircraft when lifting as claimed in any one of the above.

[0064] In a last aspect, the application provides a computer readable storage medium, which stores at least one instruction, at least one program, a code set or an instruction set, which is loaded and executed by a processor to implement the calculation of the ground load of the single side main landing gear of the aircraft when lifting as claimed in any one of the above.

[0065] The application can reasonably and effectively determine the ground vertical support reaction of the left and right side main landing gears when the single side main landing gear is lifted, which helps to improve the accuracy and efficiency of the ground load calculation under this working condition. BRIEF DESCRIPTION OF DRAWINGS

[0066] In order to more clearly illustrate the technical solutions provided by the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

[0067] Figure 1 The flow chart of the calculation method of the ground load of the single side main landing gear of the aircraft in the application.

[0068] Figure 2 The aircraft heading view in the application.

[0069] Figure 3 The coordinate system OYZ in which the triangle OAB is located and the rotation diagram of the triangle OAB in the application.

[0070] Figure 4 Figure 1 is a schematic diagram of torque balance in the present application.

[0071] Figure 5 Figure 2 is a comparison diagram of the calculated results and the measured results of the right main landing gear support reaction force in an embodiment of the present application.

[0072] Figure 6 Figure 3 is a schematic diagram of a device for calculating the ground load of a single main landing gear of an airplane in the present application. DETAILED DESCRIPTION

[0073] In order to make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

[0074] In order to analyze the change of the ground load of the two main landing gears caused by the lifting of the single main landing gear when the main landing gear is maintained on the ground, the present application provides a method and a device for calculating the ground load of the single main landing gear of an airplane, so as to improve the accuracy and efficiency of the ground load calculation under this working condition.

[0075] As shown in Figure 1 , the present application first provides a method for calculating the ground load of the single main landing gear of an airplane, which comprises the following steps.

[0076] Step S1: constructing a hypothetical condition, and establishing a ground load calculation theory for the single main landing gear lifting based on the hypothetical condition, to obtain a rotation angle expression and a ground vertical support reaction force expression of the two main landing gears.

[0077] Figure 2 As shown in Figure 2, if the elastic deformation of the airplane body and the pitching movement of the airplane body are not considered when the single main landing gear is lifted, the triangle composed of the center of gravity of the airplane body, the left main landing gear contact point and the right main landing gear contact point can be regarded as a geometrically invariant figure.

[0078] As shown in Figure 3 , the triangle OAB composed of the center of gravity A of the airplane body, the left main landing gear contact point O and the right main landing gear contact point B is placed in the OYZ coordinate system. In the OYZ coordinate system, the origin is O, the Y direction points to the right wing of the airplane, and the Z direction is vertically upward. It is assumed that the single main landing gear lifting point is located at the right main landing gear contact point B, and when the lifting distance is Δ, the triangle OAB rotates an angle θ around point O. According to the geometric relationship, the calculation formula of the rotation angle θ is as follows: ; (1)

[0079] In the formula, OB is the length of the line segment OB, that is, the main wheel track (the distance between the left and right main landing gear contact points).

[0080] ​Let the initial coordinates of the aircraft's center of gravity A be (y 0A , z 0A ),Depend on Figure 2 The initial coordinates of the aircraft's center of gravity A are as follows:

[0081] (2)

[0082] (3)

[0083] In the formula: h is the distance between point A and line segment OB, which is the initial height of the aircraft's center of gravity above the ground.

[0084] Let the coordinates of the center of gravity A of the machine after it is lifted (rotated) be (y 1A , z 1A According to the rotation axis theorem, this coordinate value can be obtained from the initial coordinates (y, y) of point A. 0A , z 0A The results are obtained from the calculation of the rotation angle θ.

[0085] (4)

[0086] (5)

[0087] Similarly, the coordinates (y) of the right main landing gear contact point B after lifting (rotation) can be obtained. 1B , z 1B ):

[0088] (6)

[0089] (7)

[0090] After obtaining the Y-axis coordinate y of the center of gravity A of the lifted machine... 1A Then, the horizontal offset of the aircraft's center of gravity can be calculated, i.e.:

[0091] (8)

[0092] Further solve for the vertical force on the left main landing gear. From... Figure 4 As shown in the torque balance diagram, the horizontal distance between point A, the center of gravity of the aircraft, and point B, the touchdown point of the right main landing gear, after being lifted is:

[0093] (9)

[0094] Substituting equations (2) and (3) into equation (9), we get:

[0095] (10)

[0096] Depend on Figure 4According to the moment balance shown, the horizontal distance between the jacking point O and the right main landing gear contact point B is: ; (11)

[0097] Ignoring the horizontal ground friction, according to the moment balance around the right main landing gear contact point B, the vertical ground reaction force on the left main landing gear after jacking is:

[0098] ; (12)

[0099] In the formula: G is the total weight of the aircraft borne by the two main landing gears.

[0100] According to the vertical force balance, the vertical ground reaction force on the right main landing gear is:

[0101] (13)

[0102] Step S2: Determine the parameters required for calculating the single-side main landing gear jacking state of the aircraft, and obtain the numerical values of the required parameters.

[0103] According to formula (1), formula (12) and formula (13), in order to calculate the ground load when the single-side main landing gear is jacked, the numerical values of the four state parameters shown in Table 1 are required. Among them, the main wheel distance can be obtained from the aircraft overall design parameter list; the height of the center of gravity from the ground h can be obtained by theoretical calculation or by measuring the center of gravity position according to the aircraft loading state; the jacking height Δ can be obtained by theoretical calculation or by measuring the distance between the jacking point and the ground; and the total weight of the aircraft borne by the two main landing gears G can be obtained by theoretical calculation or by the aircraft weight and the center of gravity measurement program.

[0104] Table 1 Parameters required for calculating the single-side main landing gear jacking state of the aircraft

[0105] Serial number Parameter name Parameter symbol Dimension 1 Main wheel track m 2 Height of the center of gravity from the ground h m 3 Lifting height Δ m 4 Total weight of the aircraft supported by the main landing gear on both sides G N

[0106] Step S3: Calculate the ground load when the single-side main landing gear is jacked according to the rotation angle expression obtained in step 1 and the vertical ground reaction force expression of the two main landing gears and the numerical values of the required parameters obtained in step 2.

[0107] According to the state parameters shown in Table 1, first, the rotation angle θ is calculated according to formula (1), and then the rotation angle θ, the main wheel distance , the height of the center of gravity from the ground h, and the total weight of the aircraft borne by the two main landing gears G are substituted into formula (12) and formula (13) respectively to calculate the vertical ground reaction force F L on the left main landing gear and the vertical ground reaction force F R on the right main landing gear.

[0108] The method described in this application can reasonably and effectively determine the vertical ground support reaction forces on the left and right main landing gears when one side of the main landing gear is lifted, which helps to improve the accuracy and efficiency of ground load calculation under this working condition.

[0109] The present application will be further described below with reference to specific embodiments provided in the present application. The derivation process of the formula in step S1 of the method of the present application will not be repeated.

[0110] Table 2 shows the values ​​of the parameters required for calculating the ground load of the aircraft in the single-side main landing gear jacking-up state in this embodiment of the application. Among them, the main wheel track is obtained from the aircraft's overall design parameter list; the center of gravity height above the ground is obtained through theoretical calculation based on the aircraft's loading state; the jacking-up height is obtained through the measured distance between the jacking-up point and the ground; and the total weight of the aircraft borne by both main landing gears is obtained through the aircraft's weight and center of gravity measurement program.

[0111] Table 2. Values ​​of relevant parameters for the single-sided main landing gear in the jack-up state.

[0112] Serial number Parameter name Parameter symbol Dimension Value 1 Main wheel track m 5.2 2 Height of the center of gravity from the ground h m 3.8 3 Lifting height Δ m 0.2 4 Total weight of the aircraft supported by the main landing gear on both sides G N 1176122

[0113] According to the main wheel track in Table 2 The value of the lifting height Δ and the calculation of the rotation angle θ using equation (1):

[0114] .

[0115] Then, based on the center of gravity height h from the ground and the main wheel track in Table 2... The values ​​of the total aircraft weight G borne by the two main landing gears, the rotation angle θ calculated in the above steps, and the ground vertical support reaction force F on the left main landing gear calculated by equation (12) are used. L :

[0116] .

[0117] Finally, based on the center of gravity height h from the ground and the main wheel track in Table 2... The values ​​of the total aircraft weight G borne by the two main landing gears, the rotation angle θ calculated in the above steps, and the ground vertical support reaction force F on the right main landing gear calculated by equation (13) are used. R :

[0118] .

[0119] In this embodiment of the application, different lifting heights Δ are set, and the corresponding vertical ground support reaction force F on the right main landing gear is calculated. R Analyze the vertical ground reaction force F acting on the right main landing gear. R The variation law of the lifting height Δ.

[0120] For example, in this embodiment of the application, the lifting height Δ is set to 0m, 0.1m, 0.3m, 0.4m and 0.5m respectively. Steps S2 and S3 are repeated to calculate the corresponding vertical ground reaction force F on the right main landing gear. R The calculation results are shown in Table 3. It can be seen that as the lifting height increases, the vertical ground reaction force on the right main landing gear decreases linearly.

[0121] Table 3. Vertical ground reaction forces on the right main landing gear at different jacking heights

[0122] Lifting height / m 0 0.1 0.3 0.4 0.5 Right side main landing gear support reaction force / N 588061 571530 538393 521751 505035

[0123] This application involves installing a force sensor between the jack and the top point of the right main landing gear, which can measure the vertical ground support reaction force on the right main landing gear corresponding to different jacking heights. For example... Figure 5 The comparison between the calculated and measured results of the right main landing gear support reaction force shown in the figure shows that the two are in high agreement, with a maximum relative error of less than 2%, indicating that the method of this application is feasible and effective.

[0124] like Figure 6 As shown, based on this, this application also provides a calculation device for the ground load when one side of the aircraft's main landing gear is raised. The device 100 includes:

[0125] The expression construction module 101 is used to construct the assumptions and establish the calculation theory of ground load when the single-sided main landing gear is lifted based on the assumptions, so as to obtain the rotation angle expression and the expression of the ground vertical support reaction force on the left and right main landing gears after lifting.

[0126] The parameter acquisition module 102 is used to determine the parameters required for calculating the single-side main landing gear lift-up state of the aircraft, and to acquire the values ​​of the required parameters.

[0127] The ground load calculation module 103 is used to calculate the ground load when the main landing gear on one side is lifted based on the rotation angle expression, the expression of the ground vertical support reaction force on the left and right main landing gears after lifting, and the numerical values ​​of the required parameters.

[0128] The processing procedures of each module of the calculation device for ground load when the aircraft's single-sided main landing gear is raised can refer to the above-mentioned calculation method for ground load when the aircraft's single-sided main landing gear is raised, and will not be repeated here.

[0129] Additionally, this application provides an electronic device comprising: one or more processors; a memory; and one or more application programs stored in the memory and configured to be executed by the one or more processors, the one or more application programs being configured to implement a method for calculating ground load when a single-sided main landing gear of an aircraft is raised as described in any of the preceding claims.

[0130] Finally, this application also provides a computer-readable storage medium, characterized in that the computer-readable storage medium stores at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, the at least one program, the code set, or the instruction set is loaded and executed by a processor to implement the method for calculating the ground load when the aircraft's single-sided main landing gear is raised as described above.

[0131] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method of calculating the ground load of a single-side main landing gear of an aircraft during jacking, characterized in that, The method comprises the steps of: constructing a hypothesis condition, establishing a ground load calculation theory for a single main landing gear jacking condition based on the hypothesis condition, obtaining a rotation angle expression and a ground vertical support reaction force expression for the left and right main landing gears after jacking; determining parameters required for calculating the single main landing gear jacking condition, and obtaining numerical values of the required parameters; calculating the ground load when the single main landing gear is jacked up according to the rotation angle expression, the ground vertical support reaction force expression for the left and right main landing gears after jacking, and the numerical values of the required parameters.

2. The method of calculating the ground load of a single-side main landing gear of an aircraft during jacking, as claimed in claim 1, characterized in that, The hypothesis condition is that the elastic deformation of the aircraft body and the pitching motion of the aircraft body are not considered when the single main landing gear is jacked up, and a triangle formed by the center of gravity of the aircraft body, the left main landing gear contact point, and the right main landing gear contact point is regarded as a geometrically invariant figure.

3. The method for calculating ground load when a single-sided main landing gear of an aircraft is raised, as described in claim 2, is characterized in that... The process of establishing the ground load calculation theory for the single main landing gear jacking condition based on the hypothesis condition and obtaining the rotation angle expression and the ground vertical support reaction force expression for the two main landing gears comprises the steps of: placing a triangle OAB formed by the center of gravity A of the aircraft body, the left main landing gear contact point O, and the right main landing gear contact point B in an OYZ coordinate system, wherein the origin is O, the Y direction points to the right wing of the aircraft, and the Z direction is vertically upward; assuming that the single main landing gear jacking point is located at the right main landing gear contact point B, and the rotation angle of the triangle OAB around point O is θ when the jacking distance is Δ, the calculation formula of the rotation angle θ is: wherein: is the length of the segment OB, i.e. the main wheel track; Let the initial coordinates of the center of mass A of the machine be (y 0A , z 0A ), and the initial coordinate values of the center of mass A of the machine be: , , wherein h is the distance between A and the line segment OB, that is, the initial height of the center of mass of the aircraft from the ground; Let the coordinates of the center of gravity A of the raised rear body be (y 1A , z 1A ), according to the rotation axis theorem, the coordinates of the center of gravity A of the raised rear body are calculated from the initial coordinates (y 0A , z 0A ) of the center of gravity A of the body and the rotation angle θ: , ; Similarly, the coordinates (y) of the right main landing gear contact point B after lifting can be obtained. 1B , z 1B ): ， ； After the Y coordinate y of the center of gravity A of the aircraft is obtained 1A Then, the offset of the center of gravity of the aircraft in the horizontal direction is calculated: ; According to the moment balance, the horizontal distance between the center of gravity A of the lifted body and the right main landing gear contact point B is ; After finishing, we get ; According to the moment balance, the horizontal distance between the O point after jacking up and the right main landing gear contact point B is: ; Neglecting the horizontal ground friction, according to the moment balance relation around the right main landing gear contact point B, the vertical ground reaction force on the left main landing gear after the jacking is: , wherein G is the total weight of the aircraft borne by the two main landing gears. according to the vertical force balance, the ground vertical support reaction force for the right main landing gear is: 。 4. The method of calculating the ground load of a single-side main landing gear of an aircraft during jacking, as claimed in claim 3, characterized in that, The parameters required for calculating the state of the single main landing gear of the aircraft include: the main wheel distance , the height of the center of gravity from the ground h, the jacking height Δ, and the total weight of the aircraft G borne by the two main landing gears. wherein the main wheel track from the list of aircraft general design parameters; the height h of the center of gravity from the ground is obtained according to the theoretical calculation or the measured center of gravity position according to the loading state of the aircraft; the jacking height Δ is obtained by theoretical calculation or by measuring the distance between the jacking point and the ground; the total weight G of the aircraft borne by the two main landing gears is obtained by theoretical calculation or by the aircraft weight and the center of gravity measurement program.

5. A method of calculating the ground load of a single-side main landing gear of an aircraft during jacking, according to claim 4, characterized in that, The process of calculating the ground load when the single main landing gear is jacked up according to the rotation angle expression, the ground vertical support reaction force expression for the two main landing gears, and the numerical values of the required parameters comprises the steps of: According to the main wheel track and the jacking height Δ and the rotation angle expression calculation of the rotation angle θ; After that, the rotation angle θ and the main wheel track The ground vertical reaction force of the left main landing gear after jacking up and the ground vertical reaction force of the right main landing gear after jacking up are calculated respectively according to the rotation angle θ, the main wheel track L, the height of the center of gravity from the ground h, the total weight of the airplane G borne by the two main landing gears, and the expression of the ground vertical reaction force.

6. A device for calculating the ground load of a single-sided main landing gear of an aircraft during jacking, characterized in that, The method comprises the steps of: An expression construction module is configured to construct a hypothesis condition, establish a ground load calculation theory for a single main landing gear jacking condition based on the hypothesis condition, and obtain a rotation angle expression and a ground vertical support reaction force expression for the left and right main landing gears after jacking. A parameter acquisition module is configured to determine parameters required for calculating the single main landing gear jacking condition, and obtain numerical values of the required parameters. A ground load calculation module is configured to calculate the ground load when the single main landing gear is jacked up according to the rotation angle expression, the ground vertical support reaction force expression for the left and right main landing gears after jacking, and the numerical values of the required parameters.

7. A device for calculating the ground load of a single-side main landing gear of an aircraft during jacking, according to claim 6, characterized in that, The hypothesis condition is that the elastic deformation of the aircraft body and the pitching motion of the aircraft body are not considered when the single main landing gear is jacked up, and a triangle formed by the center of gravity of the aircraft body, the left main landing gear contact point, and the right main landing gear contact point is regarded as a geometrically invariant figure.

8. A device for calculating the ground load of a single-side main landing gear of an aircraft during jacking, according to claim 7, characterized in that, The process of establishing the ground load calculation theory for the single main landing gear jacking condition based on the hypothesis condition and obtaining the rotation angle expression and the ground vertical support reaction force expression for the two main landing gears comprises the steps of: A triangle OAB composed of a center of gravity A, a left main landing gear contact point O and a right main landing gear contact point B is placed in an OYZ coordinate system, in which an origin is O, Y points to a right wing of the aircraft, and Z is vertically upward; When a single main landing gear jacking point is located at the right main landing gear contact point B, a rotation angle of the triangle OAB around the point O is θ when a jacking distance is Δ, and a calculation formula of the rotation angle θ is: wherein: is the length of the segment OB, i.e. the main wheel track; Let the initial coordinates of the center of mass A of the machine body be (y 0A , z 0A ), and the initial coordinate values of the center of mass A of the machine body are: , , wherein h is the distance between point A and line segment OB, that is, the initial height of the center of mass of the aircraft from the ground; Let the coordinates of the center of gravity A of the raised rear body be (y 1A , z 1A ). According to the rotation axis theorem, the coordinates of the center of gravity A of the raised rear body are calculated from the initial coordinates (y 0A , z 0A ) of the center of gravity A of the body and the rotation angle θ: , ; Similarly, the coordinates (y) of the right main landing gear contact point B after lifting can be obtained. 1B , z 1B ): ， ； After the Y coordinate y of the center of gravity A of the aircraft is obtained 1A Then, the offset of the center of gravity of the aircraft in the horizontal direction is calculated: ; According to the moment balance, the horizontal distance between the center of gravity A of the lifted body and the right main landing gear contact point B is ; obtained after finishing ; According to the moment balance, the horizontal distance between the O point after jacking up and the right main landing gear contact point B is: ; Neglecting the horizontal ground friction, according to the moment balance relation around the right main landing gear contact point B, the vertical ground reaction force on the left main landing gear after the jacking is: , wherein: G is the total weight of the aircraft borne by the two main landing gears; According to vertical force balance, a ground vertical support reaction force received by the right main landing gear is: 。 9. A device for calculating the ground load of a single-side main landing gear of an aircraft during jacking, according to claim 8, characterized in that, The parameters required for calculating the state of the single main landing gear of the aircraft include: the main wheel distance , the height of the center of gravity from the ground h, the jacking height Δ, and the total weight of the aircraft G borne by the two main landing gears. wherein the main wheel track from the list of aircraft general design parameters; The center of gravity height from the ground h is obtained according to an aircraft loading state through theoretical calculation or through measurement of a center of gravity position; The jacking height Δ is obtained through theoretical calculation or through measurement of a distance between the jacking point and the ground; The total weight of the aircraft G received by the two main landing gears is obtained through theoretical calculation or through an aircraft weight and a center of gravity measurement program.

10. Apparatus for calculating the ground load of a single-side main landing gear of an aircraft during jacking, according to claim 9, characterized in that, A process of calculating the ground load when the single main landing gear is jacked according to the rotation angle expression, the ground vertical support reaction force expression of the two main landing gears and numerical values of required parameters includes: According to the main wheel track and the jacking height Δ and the rotation angle expression calculation of the rotation angle θ; After that, the rotation angle θ and the main wheel track The ground vertical reaction force of the left main landing gear after jacking up and the ground vertical reaction force of the right main landing gear after jacking up are calculated respectively according to the rotation angle θ, the main wheel track L, the height of the center of gravity from the ground h, the total weight of the airplane G borne by the two main landing gears, and the expression of the ground vertical reaction force.

11. An electronic device, comprising: including: one or more processors; a memory; one or more application programs stored in the memory and configured to be executed by the one or more processors, the one or more application programs being configured for implementing the calculation of the ground load when the single main landing gear of the aircraft is jacked as claimed in any one of claims 1-5.

12. A computer-readable storage medium, characterized in that, The computer readable storage medium stores at least one instruction, at least one program, a code set or an instruction set, which are loaded and executed by the processor to implement the calculation of the ground load when the single main landing gear of the aircraft is jacked as claimed in any one of claims 1-5.

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