Method and system for estimating landing load of multi-strut undercarriage

Abstract

The invention belongs to the technical field of aircraft design, and relates to a multi-strut undercarriage landing load estimation method and system.The method comprises the steps that firstly, initial filling parameters of a buffer are determined, and a relation curve graph of axle vertical loads and gravity center displacement of main undercarriages is determined according to the landing height difference of the main undercarriages; calculating the work absorbed by each main landing gear and the total work of the single-side main landing gear according to the load of each main landing gear; judging whether the total work quantity of the single-side main undercarriage is greater than the designed landing work quantity of the undercarriage or not, and if so, completing the estimation of the landing load of the undercarriage; according to the method, the landing load of the multi-strut undercarriage is estimated through the static compression curve of the multi-strut undercarriage, the estimation method also considers the influence of the distance between multiple struts and the sinking angle of the tail of the aircraft, and the arrangement rationality of the multi-strut undercarriage can be quickly evaluated in the scheme design stage; basic arrangement parameters and buffer filling parameters of the multi-strut undercarriage are formed.

Description

Technical Field

[0001] The present application belongs to the field of aircraft design technology, and in particular relates to a landing load estimation method and system for a multi-strut landing gear. Background Art

[0002] During the landing gear design process, it is necessary to analyze the buffer performance based on the amount of work absorbed by the landing gear to determine the required buffer stroke and the corresponding landing load (or landing overload). Compared with the traditional single-strut landing gear, the multi-strut landing gear has a statically indeterminate layout, and the power distribution of each strut is not clearly specified. Therefore, the required buffer stroke and the corresponding landing load cannot be determined based on the existing formula.

[0003] In conventional landing gear designs, the landing gear's cushioning system converts the aircraft's landing kinetic energy into deformation energy for the cushions and tires during landing. The landing gear's landing work primarily consists of two components: the aircraft's kinetic energy from landing until the tires touch down, and the aircraft's potential energy from the time the tires touch down until the tires and cushions stop compressing. Therefore, the following formula can be used:

[0004]

[0005] Where: N is the vertical overload factor of the landing gear;

[0006] P dl is the equivalent load acting on the tire, N;

[0007] S lz is the axle displacement, m;

[0008] δ lt is the tire compression, m;

[0009] η lz is the efficiency coefficient of the axle displacement absorbed work;

[0010] η lt is the efficiency coefficient of the tire;

[0011] m dl is the equivalent mass acting on the landing gear, kg;

[0012] W is the weight of the aircraft;

[0013] L is the lift of the aircraft;

[0014] V y is the aircraft's sinking speed.

[0015] If L=W, the above formula becomes:

[0016]

[0017] However, for the statically indeterminate layout of multi-wheel and multi-strut landing gear, since the energy absorbed by each strut cannot be determined (it cannot be simply evenly distributed), the cushioning performance of each strut cannot be directly analyzed using the above formula.

[0018] Therefore, how to quickly estimate the landing load of a statically indeterminate layout of a multi-strut landing gear is a problem that needs to be solved. Summary of the Invention

[0019] The purpose of this application is to provide a multi-strut landing gear landing load estimation method and system to solve the problem in the prior art that it is difficult to quickly estimate the landing load of a statically indeterminate layout of a multi-strut landing gear.

[0020] The technical solution of this application is: a method for estimating landing loads of a multi-strut landing gear, comprising:

[0021] Use existing reference aircraft to preliminarily determine landing gear travel; preliminarily determine initial buffer filling parameters based on shutdown compression requirements; then, based on the landing height differences of each main landing gear, determine the relationship curve between vertical load on each main landing gear axle and center of gravity displacement;

[0022] Assuming the center of gravity displacement required to absorb the aircraft landing work, the vertical load on each main landing gear is determined based on the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, and the vertical load on each main landing gear is quickly obtained. The center of gravity displacement of each main landing gear is then determined based on the aircraft center of gravity displacement and the landing height difference of each main landing gear. Finally, the work absorbed by each main landing gear and the total work of each main landing gear on a single side are calculated based on the vertical load on each main landing gear and the center of gravity displacement of each main gear.

[0023] Obtain the designed landing work of the landing gear and determine whether the total work of the single-side main landing gear is greater than the designed landing work of the landing gear. If so, it means that the landing gear can absorb the designed landing work, and the landing gear landing load estimation is completed.

[0024] Preferably, a relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement is determined based on the initial filling parameters of the buffer and the landing height difference of each main landing gear; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship curve diagram, the vertical load on each main landing gear is found according to the relationship diagram.

[0025] Preferably, the calculation formula for the work absorbed by each main landing gear is:

[0026] W1=η1·P1·Y c ;

[0027] W2=η2·P2·(Y c -L·sinθ);

[0028] W3=η3·P3·(Yc -2L·sinθ);

[0029] Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the main wheelbase; θ is the landing attitude angle;

[0030] The total power absorbed by the main starter on one side W 总 The calculation formula is:

[0031] W 总 =W1+W2+W3.

[0032] Preferably, the calculation formula for the total power of the single-side main landing gear is:

[0033]

[0034] Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; N is the aircraft's lift; S lz is the axle displacement; δ lt is the amount of tire compression.

[0035] Preferably, after determining the relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement, a relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement is drawn; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship diagram, the load on each main landing gear is found according to the relationship diagram.

[0036] Preferably, if the total power of a single main landing gear is less than the designed landing power of the landing gear, the center of gravity displacement value is repeatedly adjusted and the total power of the single main landing gear is iteratively calculated until the total power of the single main landing gear is greater than the designed landing power of the landing gear.

[0037] As a specific embodiment, a multi-strut landing gear landing load estimation system includes:

[0038] The landing gear buffer parameter preliminary determination module uses existing reference models to preliminarily determine the landing gear travel; preliminarily determines the initial buffer filling parameters based on the shutdown compression requirements or other technical requirements; and then determines the relationship curve between the vertical load and center of gravity displacement of each main landing gear axle based on the landing height difference of each main landing gear;

[0039] Design a landing work calculation module. Assuming the center of gravity displacement required to absorb the aircraft's landing work, determine the vertical load on each main landing gear based on a curve plotting the relationship between the vertical load on each main landing gear axle and the center of gravity displacement, and quickly obtain the vertical load on each main landing gear. Then, determine the center of gravity displacement of each main landing gear based on the aircraft's center of gravity displacement and the landing height difference of each main landing gear. Finally, calculate the work absorbed by each main landing gear and the total work of each main landing gear on a single side based on the vertical load and the center of gravity displacement of each main landing gear.

[0040] The landing load judgment module is designed to obtain the designed landing load of the landing gear and determine whether the total load of the single-side main landing gear is greater than the designed landing load of the landing gear. If so, it means that the landing gear can absorb the designed landing load, and the landing load of the landing gear is estimated.

[0041] Preferably, the calculation formula for the work absorbed by each main landing gear is:

[0042] W1=η1·P1·Y c ;

[0043] W2=η2·P2·(Y c -L·sinθ);

[0044] W3=η3·P3·(Y c -2L·sinθ);

[0045] Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the aircraft's lift; θ is the landing attitude angle;

[0046] The total power absorbed by the main starter on one side W 总 The calculation formula is:

[0047] W 总 =W1+W2+W3.

[0048] Preferably, the calculation formula for the total power of the single-side main landing gear is:

[0049]

[0050] Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; L is the aircraft's lift; S lz is the axle displacement; δ ltis the amount of tire compression.

[0051] Preferably, after determining the relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement, a relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement is drawn; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship diagram, the load on each main landing gear is found according to the relationship diagram.

[0052] Preferably, if the total power of a single main landing gear is less than the designed landing power of the landing gear, the center of gravity displacement value is repeatedly adjusted and the total power of the single main landing gear is iteratively calculated until the total power of the single main landing gear is greater than the designed landing power of the landing gear.

[0053] The present invention provides a multi-strut landing load estimation method and system. The method first determines initial buffer filling parameters and, based on the landing height differences of each main landing gear, determines a curve showing the relationship between the vertical load on each main landing gear axle and the center of gravity displacement. The method then calculates the power absorbed by each main landing gear and the total power of the single main landing gear based on the loads on each main landing gear. A determination is made as to whether the total power of the single main landing gear exceeds the designed landing power of the landing gear. If so, the landing load estimation is completed. The landing load of the multi-strut landing gear is estimated using the static compression curve of the multi-strut landing gear. This estimation method also considers the effects of the spacing between the struts and the tail drop angle of the aircraft. This method allows for a rapid assessment of the rationality of the multi-strut landing gear layout during the design phase, thereby generating basic layout parameters and buffer filling parameters for the multi-strut landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0055] Figure 1 This is a schematic diagram of the overall process of this application;

[0056] Figure 2 This is a graph showing the relationship between the vertical load and the center of gravity displacement of each main starting wheel axle in this application. DETAILED DESCRIPTION

[0057] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0058] A method for estimating landing loads on a multi-strut landing gear, such as Figure 1 As shown, the following steps are included:

[0059] Step S100: Preliminarily determine the landing gear travel using an existing reference aircraft model; preliminarily determine the initial buffer filling parameters based on the shutdown compression requirement or other technical requirements; then, based on the landing height difference of each main landing gear, determine the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, and draw a relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, as shown in FIG. Figure 2 As shown, the ordinate is the vertical load of each main landing gear, and the abscissa is the displacement of the aircraft center of gravity; ① is the load curve of the rear main landing gear, ② is the load curve of the middle main landing gear, and ③ is the load curve of the front main landing gear.

[0060] Step S200: First, assume the center of gravity displacement required to absorb the landing work of the aircraft. Figure 2 The loads on each main landing gear are searched and quickly acquired. The center of gravity displacement of each main landing gear is then determined based on the aircraft's center of gravity displacement and the landing height difference of each main landing gear. Finally, the work absorbed by each main landing gear and the total work of the single-side main landing gear are calculated based on the vertical loads on each main landing gear and the center of gravity displacement of each main gear.

[0061] Preferably, the calculation formula for the displacement of each main landing gear axle and the tire compression is:

[0062]

[0063] Where N is the vertical overload factor of the landing gear;

[0064] P dl is the equivalent load acting on the tire, N;

[0065] S lz is the axle displacement, m;

[0066] δ lt is the tire compression, m;

[0067] η lz is the efficiency coefficient of the wheel axle displacement absorbed work, which is taken as 0.7;

[0068] η lt is the efficiency coefficient of the tire, usually taken as 0.47;

[0069] m dl is the equivalent mass acting on the landing gear, kg;

[0070] V y is the aircraft's sinking speed.

[0071] Preferably, the calculation formula for the work absorbed by each main landing gear is:

[0072] W1=η1·P1·Y c ;

[0073] W2=η2·P2·(Y c -L·sinθ);

[0074] W3=η3·P3·(Y c -2L·sinθ);

[0075] Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the main wheelbase; θ is the landing attitude angle;

[0076] The total power absorbed by the main starter on one side W 总 The calculation formula is:

[0077] W 总 =W1+W2+W3.

[0078] The calculation formula for the total power of a single-side main landing gear is:

[0079]

[0080] Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; N is the aircraft's lift; S lz is the axle displacement; δ lt is the amount of tire compression.

[0081] Step S300: Obtain the designed landing power of the landing gear. This parameter is determined before the landing gear structure is designed. Determine whether the total power of the main landing gear on one side is greater than the designed landing power of the landing gear.

[0082] If so, it means that the landing gear can absorb the designed landing work, and the landing gear landing load estimation is completed. If not, the initial estimation parameters are repeatedly adjusted and the total work of the single-side main landing gear is iteratively calculated until the total work of the single-side main landing gear is greater than the designed landing work of the landing gear.

[0083] This application establishes an engineering algorithm for the buffer performance of a multi-strut landing gear by utilizing a deformation coordination equation, and estimates the landing load of the multi-strut landing gear through the static compression curve of the multi-strut landing gear. This estimation method also considers the influence of the multi-strut spacing and the tail sink angle of the aircraft, and can quickly evaluate the rationality of the multi-strut landing gear layout during the scheme design stage, thereby forming the basic layout parameters and buffer filling parameters of the multi-strut landing gear.

[0084] As a specific embodiment, a multi-pillar landing gear landing load estimation system is also included, including:

[0085] The landing gear buffer parameter preliminary determination module uses existing reference models to preliminarily determine the landing gear travel; preliminarily determines the initial buffer filling parameters based on the shutdown compression requirements or other technical requirements; and then determines the relationship curve between the vertical load and center of gravity displacement of each main landing gear axle based on the landing height difference of each main landing gear;

[0086] Design a landing work calculation module. Assuming the center of gravity displacement required to absorb the aircraft's landing work, determine the vertical load on each main landing gear based on a curve plotting the relationship between the vertical load on each main landing gear axle and the center of gravity displacement, and quickly obtain the vertical load on each main landing gear. Then, determine the center of gravity displacement of each main landing gear based on the aircraft's center of gravity displacement and the landing height difference of each main landing gear. Finally, calculate the work absorbed by each main landing gear and the total work of each main landing gear on a single side based on the vertical load and the center of gravity displacement of each main landing gear.

[0087] The landing load judgment module is designed to obtain the designed landing load of the landing gear and determine whether the total load of the single-side main landing gear is greater than the designed landing load of the landing gear. If so, it means that the landing gear can absorb the designed landing load, and the landing load of the landing gear is estimated.

[0088] Preferably, the calculation formula for the work absorbed by each main landing gear is:

[0089] W1=η1·P1·Y c ;

[0090] W2=η2·P2·(Y c -L·sinθ);

[0091] W3=η3·P3·(Y c -2L·sinθ);

[0092] Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the aircraft's lift; θ is the landing attitude angle;

[0093] The total power absorbed by the main starter on one side W 总 The calculation formula is:

[0094] W 总 =W1+W2+W3.

[0095] Preferably, the calculation formula for the total power of the single-side main landing gear is:

[0096]

[0097] Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; L is the aircraft's lift; S lz is the axle displacement; δ lt is the amount of tire compression.

[0098] Preferably, the calculation formula for the tire compression is:

[0099]

[0100] Where N is the vertical overload factor of the landing gear;

[0101] P dl is the equivalent load acting on the tire, N;

[0102] S lz is the axle displacement, m;

[0103] δ lt is the tire compression, m;

[0104] η lz is the efficiency coefficient of the axle displacement absorbed work;

[0105] η lt is the efficiency coefficient of the tire;

[0106] m dl is the equivalent mass acting on the landing gear, kg;

[0107] V y is the aircraft's sinking speed.

[0108] Preferably, after determining the relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement, a relationship curve diagram between the vertical load on each main landing gear axle and the center of gravity displacement is drawn; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship diagram, the load on each main landing gear is found according to the relationship diagram.

[0109] Preferably, if the total power of a single main landing gear is less than the designed landing power of the landing gear, the center of gravity displacement value is repeatedly adjusted and the total power of the single main landing gear is iteratively calculated until the total power of the single main landing gear is greater than the designed landing power of the landing gear.

[0110] Finally, it should be noted that the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention. Other structures can refer to common designs. In the absence of conflicts, the same embodiment and different embodiments of the present invention can be combined with each other.

[0111] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A method for estimating landing loads of a multi-strut landing gear, characterized in that: include: Use existing reference aircraft to preliminarily determine landing gear travel; Preliminarily determine the initial filling parameters of the buffer according to the shutdown compression requirements; Then, based on the landing height differences of each main landing gear, a relationship curve between the vertical load on each main landing gear axle and the displacement of the center of gravity is determined; Assuming the center of gravity displacement required to absorb the aircraft landing work, the vertical load on each main landing gear is determined based on the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, and the vertical load on each main landing gear is quickly obtained. The center of gravity displacement of each main landing gear is then determined based on the aircraft center of gravity displacement and the landing height difference of each main landing gear. Finally, the work absorbed by each main landing gear and the total work of each main landing gear on a single side are calculated based on the vertical load on each main landing gear and the center of gravity displacement of each main gear. Obtain the designed landing work of the landing gear and determine whether the total work of the single-side main landing gear is greater than the designed landing work of the landing gear. If so, it means that the landing gear can absorb the designed landing work, and the landing gear landing load estimation is completed.

2. The multi-strut landing gear landing load estimation method according to claim 1, wherein: Based on the initial filling parameters of the buffer and the landing height difference of each main landing gear, the relationship curve between the vertical load of each main landing gear axle and the center of gravity displacement is determined; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship curve, the vertical load of each main landing gear is found according to the relationship diagram.

3. The method for estimating landing loads of a multi-strut landing gear according to claim 1, wherein: The calculation formula for the work absorbed by each main landing gear is: W1=η1·P1·Y c ; W2=η2·P2·(Y c -L·sinθ); <h2 style=";text-align:left;direction:ltr">W3=η3·P3·(Y<h2 style=";text-align:left;direction:ltr"> c <h2 style=";text-align:left;direction:ltr"> -2L·sinθ); Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the aircraft's lift; θ is the landing attitude angle; The total power absorbed by the main starter on one side W 总 The calculation formula is: <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 总 <h2 style=";text-align:left;direction:ltr"> =W1+W2+W3。 4. The multi-strut landing gear landing load estimation method according to claim 1, wherein: The calculation formula for the total power of the single-side main landing gear is: Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; L is the aircraft's lift; S lz is the axle displacement; δ lt is the amount of tire compression.

5. The method for estimating landing loads of a multi-strut landing gear according to claim 1, wherein: After determining the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, draw the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship diagram, find the load on each main landing gear according to the relationship diagram.

6. The method for estimating landing loads of a multi-strut landing gear according to claim 1, wherein: If the total power of one main landing gear is less than the designed landing power of the landing gear, the center of gravity displacement value is repeatedly adjusted and the total power of one main landing gear is iteratively calculated until the total power of one main landing gear is greater than the designed landing power of the landing gear.

7. A multi-strut landing gear landing load estimation system, using the method according to any one of claims 1 to 6, characterized in that: include: Landing gear cushion parameter preliminary determination module, using existing reference models to preliminarily determine the landing gear travel; Preliminarily determine the initial filling parameters of the buffer according to the shutdown compression requirements or other technical requirements; Then, according to the landing height difference of each main landing gear, a relationship curve between the vertical load of each main landing gear axle and the displacement of the center of gravity is determined; Design a landing work calculation module. Assuming the center of gravity displacement required to absorb the aircraft's landing work, determine the vertical load on each main landing gear based on a curve plotting the relationship between the vertical load on each main landing gear axle and the center of gravity displacement, and quickly obtain the vertical load on each main landing gear. Then, determine the center of gravity displacement of each main landing gear based on the aircraft's center of gravity displacement and the landing height difference of each main landing gear. Finally, calculate the work absorbed by each main landing gear and the total work of each main landing gear on a single side based on the vertical load and the center of gravity displacement of each main landing gear. The landing load judgment module is designed to obtain the designed landing load of the landing gear and determine whether the total load of the single-side main landing gear is greater than the designed landing load of the landing gear. If so, it means that the landing gear can absorb the designed landing load, and the landing load of the landing gear is estimated.

8. The multi-strut landing gear landing load estimation system according to claim 7, wherein: The calculation formula for the work absorbed by each main landing gear is: W1=η1·P1·Y c ; W2=η2·P2·(Y c -L·sinθ); <h2 style=";text-align:left;direction:ltr">W3=η3·P3·(Y<h2 style=";text-align:left;direction:ltr"> c <h2 style=";text-align:left;direction:ltr"> -2L·sinθ); Where: W1, W2, W3 are the work absorbed by the rear main landing gear, middle main landing gear, and front main landing gear; η1, η2, η3 are the efficiency coefficients of the buffer system of the rear main landing gear, middle main landing gear, and front main landing gear; P1, P2, P3 are the vertical ground loads of the rear main landing gear, middle main landing gear, and front main landing gear; Y c is the displacement of the aircraft's center of gravity; L is the aircraft's lift; θ is the landing attitude angle; The total power absorbed by the main starter on one side W 总 The calculation formula is: <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 总 <h2 style=";text-align:left;direction:ltr"> =W1+W2+W3。 9. The multi-strut landing gear landing load estimation system according to claim 7, wherein: The calculation formula for the total power of the single-side main landing gear is: Where W sj is the total work of the main landing gear on one side; m dl is the equivalent mass of the main landing gear on one side; V y is the aircraft's sinking speed; W is the aircraft's weight; L is the aircraft's lift; S lz is the axle displacement; δ lt is the amount of tire compression.

10. The multi-strut landing gear landing load estimation system according to claim 7, wherein: After determining the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement, draw the relationship curve between the vertical load on each main landing gear axle and the center of gravity displacement; after assuming and then absorbing the center of gravity displacement required for the aircraft landing work according to the relationship diagram, find the load on each main landing gear according to the relationship diagram.

11. The multi-strut landing gear landing load estimation system according to claim 7, wherein: If the total power of one main landing gear is less than the designed landing power of the landing gear, the center of gravity displacement value is repeatedly adjusted and the total power of one main landing gear is iteratively calculated until the total power of one main landing gear is greater than the designed landing power of the landing gear.

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