Full-state load simulation technology for aircraft cabin door actuator

Abstract

The invention provides a full-state load simulation technology for an aircraft cabin door actuator, and relates to the technical field of rotary actuator test equipment. The device comprises a base and a rotary actuator arranged on the base, and further comprises a torque loading mechanism and an axial load loading mechanism, the torque loading mechanism comprises a rotary power output unit arranged on the base, and an output shaft of the rotary power output unit is connected with a rotary shaft of the rotary actuator and can drive the rotary shaft of the rotary actuator to rotate; the axial load loading mechanism comprises a first linear power output unit arranged on the base and a load loading unit arranged on a telescopic rod of the first linear power output unit, the load loading unit comprises a thrust seat, and the thrust seat rotatably sleeves the telescopic rod and is connected with the rotating shaft; the thrust seat can be pushed or pulled by the telescopic rod to apply force in the axial direction of the rotating shaft to the rotating shaft. According to the full-state load simulation technology for the aircraft cabin door actuator, the rotary actuator can be better tested.

Description

Technical Field

[0001] The present invention relates to the technical field of cabin door actuator test equipment, and in particular to a full-state load simulation technology for an aircraft cabin door actuator. Background Art

[0002] Rotary actuators are widely used in industrial control, especially in aerospace. They are usually designed to withstand high loads, with high reliability and stability. For example, rotary actuators can be used in aircraft doors to ensure that the doors can be opened and closed safely and reliably under various flight conditions.

[0003] In order to ensure the performance of the rotary actuator, it is necessary to test the rotary actuator after development or production to verify and evaluate its performance by simulating the load conditions in the actual working environment.

[0004] However, existing testing technologies do not fully consider the various loads that the door system is subjected to when the aircraft is in motion, cannot truly simulate the state of the aircraft door switch, and are difficult to fully test the performance of the rotary actuator. Summary of the invention

[0005] To this end, the present invention proposes a full-state load simulation technology for an aircraft door actuator, so as to more comprehensively simulate the load condition of the rotary actuator when testing the performance of the rotary actuator.

[0006] The technical solution of the present invention is as follows: A full-state load simulation technology for an aircraft door actuator comprises a base and a rotary actuator, wherein a cylinder of the rotary actuator is fixedly arranged on the base, and further comprises: The torque loading mechanism comprises a rotary power output unit arranged on the base, wherein the output shaft of the rotary power output unit is connected to the rotary shaft of the rotary actuator and can drive the rotary shaft to rotate; The axial load loading mechanism includes a first linear power output unit arranged on the base, and a load loading unit arranged on the telescopic rod of the first linear power output unit, wherein the load loading unit includes a thrust seat, which is rotatably mounted on the telescopic rod and connected to the rotating shaft, and the thrust seat can be pushed or pulled by the telescopic rod to apply an axial force to the rotating shaft along the rotating shaft.

[0007] Furthermore, it also includes a radial load loading mechanism arranged in the circumference of the rotating shaft; the radial load loading mechanism includes two second linear power output units and a bearing seat, the rotating shaft can rotate relative to the bearing seat, the two second linear power output units are arranged at intervals in the circumference of the rotating shaft, and the cylindrical ends of the two second linear power output units are respectively hinged to the base, and the rod ends of the two second linear power output units are respectively hinged to the bearing seat.

[0008] Furthermore, the bearing seat includes two support plates and two pins; the two support plates are respectively mounted on the rotating shaft, the rotating shaft can rotate relative to the two support plates, the two support plates are arranged at intervals along the axial direction of the rotating shaft, and the two pins are respectively connected between the two support plates; the rod ends of the two second linear power output units are correspondingly rotatably connected with the two pins.

[0009] Furthermore, a pressure sensor and a connecting piece are respectively provided on the rod ends of the two second linear power output units, the connecting piece is rotatably mounted on the corresponding pin shaft, and the pressure sensor is arranged between the rod end of the second linear power output unit and the connecting piece.

[0010] Furthermore, the output forces of the two second linear power output units intersect the axis of the rotating shaft at the same point.

[0011] Furthermore, it also includes an inertia simulation mechanism; the inertia simulation mechanism includes an inertia disc mounting seat and a plurality of inertia discs, the inertia disc mounting seat is fixedly connected to the rotating shaft and is located on one side of the rotating shaft, and each of the inertia discs is detachably arranged on the inertia disc mounting seat.

[0012] Furthermore, the inertia disk mounting seat includes two fan-shaped mounting plates fixedly connected to the rotating shaft, the two mounting plates are arranged at intervals along the axial direction of the rotating shaft, and a connecting plate connecting the two mounting plates is provided between the two mounting plates, and the inertia disks are detachably provided on the outer sides of the two mounting plates; the output shaft of the torque loading mechanism is connected to the mounting plate close to the torque loading mechanism through a cross shaft.

[0013] Furthermore, the inertia disk mounting seat includes two mounting plates spaced apart along the axial direction of the rotating shaft, and a converter is fixed on the rotating shaft, and a plurality of the inertia disks are stacked and fixed on the end surfaces of the two mounting plates and the converter away from the rotating shaft.

[0014] Furthermore, it also includes an inertia simulation mechanism; the inertia simulation mechanism includes an inertia disc mounting seat and a plurality of inertia discs, the inertia disc mounting seat is fixedly connected to the rotating shaft and is located on one side of the rotating shaft, and each of the inertia discs is detachably arranged on the inertia disc mounting seat; the inertia disc mounting seat includes two mounting plates spaced apart along the axial direction of the rotating shaft, the two support plates are respectively arranged corresponding to the two mounting plates, and the mounting plates can rotate relative to the support plates.

[0015] Furthermore, a plurality of rotary actuators are provided at intervals on the base, the torque loading mechanism and the axial load loading mechanism are respectively provided at two ends of the rotary actuator, a plurality of the rotary actuators share one axial load loading mechanism, and the output end of the axial load loading mechanism is connected to the rotary shaft of the rotary actuator; the rotary power output unit provided corresponding to each rotary actuator is a motor, a through hole is provided through the output shaft of the motor, and the rotary shafts of two adjacent rotary actuators are connected via a connecting shaft passing through the through hole.

[0016] The working principle and beneficial effects of the present invention are: The aircraft door actuator full-state load simulation technology provided by the present invention fixes the rotary actuator on a base, and sets a torque loading mechanism and an axial load loading mechanism on the base, so that when the axial load loading mechanism applies an axial load to the rotary shaft to simulate the axial load on the rotary shaft, the torque loading mechanism applies a torque to the rotary shaft to simulate the pneumatic hinge moment actually received by the rotary actuator. By setting the above-mentioned load loading unit, the thrust seat rotatably mounted on the telescopic rod applies an axial load to the rotary shaft, so that when the torque is applied to the rotary shaft, the coupling influence of the axial load loading mechanism can be avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0018] Figure 1 A three-dimensional diagram of a full-state load simulation technology for an aircraft door actuator provided by an embodiment of the present invention; Figure 2 A cross-sectional view of a full-state load simulation technology for an aircraft door actuator provided by an embodiment of the present invention; Figure 3 for Figure 2 A partial enlarged view of the middle A; Figure 4 A three-dimensional diagram from another angle of the full-state load simulation technology for aircraft door actuators provided by an embodiment of the present invention; Figure 5 for Figure 4 A partial enlarged view of point B in the middle; Figure 6 A three-dimensional diagram of another inertia simulation mechanism provided by an embodiment of the present invention; Figure 7 for Figure 6 A partial enlarged view of point C in the middle; In the figure: 100, base; 110, limit plate; 200, rotary actuator; 210, cylinder; 211, static ear; 220, rotating shaft; 221, movable ear; 300, torque loading mechanism; 310, motor; 400, axial load loading mechanism; 410, first linear power output unit; 420, telescopic rod; 430, thrust bearing; 440, thrust seat; 500, connecting shaft; 600, radial load loading mechanism; 610, second linear power output unit; 611, pressure sensor, 612, connecting piece; 620, bearing seat; 621, support plate; 622, pin; 601, limit hole; 700, inertia simulation mechanism; 710, mounting plate; 711, connecting sleeve; 720, connecting plate; 730, inertia disk; 740, adapter. DETAILED DESCRIPTION

[0019] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0020] This embodiment provides a full-state load simulation technology for an aircraft door actuator, hereinafter referred to as the simulation technology, Figure 1 and Figure 2 As shown, it includes a base 100 and a rotary actuator 200, wherein a cylinder 210 of the rotary actuator 200 is fixedly arranged on the base 100, and it also includes a torque loading mechanism 300 and an axial load loading mechanism 400. The torque loading mechanism 300 includes a rotary power output unit 310 arranged on the base 100, and an output shaft 311 of the rotary power output unit 310 is connected to the rotary shaft 220 of the rotary actuator 200, and can drive the rotary shaft 220 of the rotary actuator 200 to rotate.

[0021] The axial load loading mechanism 400 includes a first linear power output unit 410 disposed on the base 100, and a load loading unit disposed on the telescopic rod 420 of the first linear power output unit 410, and the load loading unit includes a thrust seat 440, which is rotatably sleeved on the telescopic rod 420 and connected to the rotating shaft 220, and the thrust seat 440 can be pushed or pulled by the telescopic rod 420 to apply a force along the axial direction of the rotating shaft 220 to the rotating shaft 220. The force applied by the first linear power output unit to the rotating shaft is preferably in the same straight line as the axis of the rotating shaft.

[0022] Based on the above structure, the simulation technology of this embodiment can apply an axial load to the rotating shaft 220 of the rotary actuator 200 by the axial load loading mechanism 400 to simulate the axial load that the rotary actuator 200 is subjected to during actual use, and then apply torque to the rotating shaft 220 by the torque loading mechanism 300 to simulate the pneumatic hinge torque that the rotary actuator 200 is subjected to during actual use.

[0023] In this embodiment, reference Figure 1 As shown, the rotary actuator 200 is fixedly connected to the base 100 via the static ears 211 on the cylinder 210. The structure of the rotary actuator 200 can refer to the prior art, and the structure of the base 100 can be set as needed, which will not be described in detail here.

[0024] In this embodiment, reference Figure 2 As shown, the first linear power output unit 410 is a hydraulic cylinder, and the telescopic rod 420 of the first linear power output unit 410 is a cylinder rod of the hydraulic cylinder. In some embodiments, the first linear power output unit 410 may also be a cylinder, an electric cylinder, or a component driven by a motor to move in a straight line, for example, the telescopic rod 420 may be a rack driven by a motor through a gear.

[0025] In this embodiment, the output force of the first linear power output unit is in the same straight line as the rotation axis, which ensures that the output force of the first linear power output unit is only used to simulate the axial force of the rotary actuator 200 and does not generate torque on the rotary actuator 200.

[0026] refer to Figure 2 and Figure 3As shown, a thrust bearing 430 is fixedly sleeved on the telescopic rod 420, and the above-mentioned thrust seat 440 is fixedly sleeved on the thrust bearing 430, so that the thrust seat 440 can rotate on the telescopic rod 420. By rotatably sleeved on the telescopic rod 420, the axial load output by the axial load loading mechanism 400 can be prevented from affecting the torque applied by the torque loading mechanism 300 to the rotating shaft 220, and the coupling of the axial load and the rotational torque is avoided. Specifically, if the thrust seat 440 is fixedly connected to the telescopic rod 420, the torque applied by the torque loading mechanism 300 to the rotating shaft 220 will cause the thrust seat 440 to apply a reverse torque to the rotating shaft 220, affecting the test results. By sleeved on the thrust seat 440 on the thrust bearing 430, it is possible to avoid the thrust seat 440 from applying a reverse torque to the rotating shaft 220.

[0027] It should be noted that, in some embodiments, an extension rod coaxial with and fixedly connected to the telescopic rod 420 may be provided on the top of the telescopic rod 420 , and the thrust seat 440 may be sleeved on the extension rod, which should also be deemed as sleeved on the telescopic rod 420 .

[0028] In this embodiment, the above-mentioned rotational power output unit 310 is a motor, wherein the motor 310 can be an existing product, specifically a blade swing motor disclosed in publication number CN106499690A, and its structure is not described in detail here. The output shaft 311 of the blade swing motor is coaxial and fixedly connected with the rotating shaft 220 of the rotary actuator 200 to apply torque to the rotating shaft 220.

[0029] In this embodiment, a through hole is provided on the output shaft 311 of the blade swing motor, which penetrates the output shaft 311 along its axial direction. By providing the through hole, it is convenient to test multiple rotary actuators 200 at the same time. In terms of specific structure, the torque loading mechanism 300 and the axial load loading mechanism 400 are respectively arranged at both ends of the rotary actuator 200. Multiple rotary actuators 200 are arranged at intervals on the base 100, and the multiple rotary actuators 200 share one axial load loading mechanism 400. The output end of the above-mentioned axial load loading mechanism 400 is connected to the rotating shaft 220 of the rotary actuator 200, refer to Figure 2As shown, the rotating shafts 220 of two adjacent rotary actuators 200 are connected by a connecting shaft 500 passing through the through hole, and the connecting shaft 500 is coaxial with the two rotating shafts 220 and fixedly connected, so that the axial load is sequentially transmitted to the rotating shafts 220 of each rotary actuator 200 through each connecting shaft 500. It should be noted that other rotary actuators 200 are not shown in the drawings of this embodiment because it does not affect understanding. In this embodiment, by installing the torque loading mechanism 300 and the axial load loading mechanism 400 at both ends of the rotary actuator 200, it is convenient to apply the rotary torque and axial load to the rotary actuator 200.

[0030] refer to Figure 4 As shown, the simulation technology of this embodiment also includes a radial load loading mechanism 600, which is installed on the circumference of the rotating shaft 220 of the rotary actuator 200. It includes two second linear power output units 610 and a bearing seat 620. The rotating shaft 220 can rotate relative to the bearing seat 620, and the two second linear power output units 610 are arranged at intervals along the circumference of the rotating shaft 220, and the cylinder ends of the two second linear power output units 610 are respectively hinged to the base 100, and the rod ends of the two second linear power output units 610 are respectively hinged to the bearing seat 620. And preferably, the two second linear power output units 610 intersect the axis of the rotating shaft 220 at the same point.

[0031] In this embodiment, the radial load loading mechanism 600 is installed on the circumference of the rotating shaft 220 to facilitate the application of radial load to the rotating shaft 220, while avoiding position interference with the torque loading mechanism 300 and the radial load loading mechanism 400 at both ends of the rotating shaft 220; by setting the above-mentioned bearing seat 620 sleeved on the rotating shaft 220, and having two second linear power output units 610 apply a load along the radial direction of the rotating shaft 220 to the bearing seat 620, it is possible to avoid applying torque to the rotating shaft 220.

[0032] Specifically, the rotating shaft 220 can only rotate relative to the bearing seat 620, and the bearing seat 620 is fixed on the base 100 through the second linear power output unit 610, that is, the radial force output by the second linear power output unit 610 is transmitted to the rotating shaft 220 through the bearing seat 620, because the output forces of the two second linear power output units 610 intersect with the axis of the rotating shaft 220 at the same point. That is, the output force of one second linear power output unit 610 intersects with the axis of the rotating shaft 220 at a first point, and the output force of the other second linear power output unit 610 intersects with the axis of the rotating shaft 220 at a second point, and the first point coincides with the second point, which ensures that the two second linear power output units 610 only apply radial force to the rotating shaft 220, and do not generate torque on the rotating shaft 220, and also avoids coupling effects on the torque loading mechanism 300.

[0033] In this embodiment, the two second linear power output units 610 are hydraulic cylinders, whose barrel ends are cylinder barrels of the hydraulic cylinders, and whose rod ends are cylinder rods of the hydraulic cylinders. In some embodiments, the second linear power output units 610 may also be pneumatic cylinders or electric cylinders.

[0034] refer to Figure 4 and Figure 5 As shown, the bearing seat 620 of this embodiment includes two support plates 621 and two pins 622. The two support plates 621 are sleeved on the rotating shaft 220, and the rotating shaft 220 can rotate relative to the two support plates 621. The two support plates 621 are spaced apart along the axial direction of the rotating shaft 220, and the two pins 622 are respectively connected to the two support plates 621. The rod ends of the two second linear power output units 610 are respectively rotatably connected to the two pins 622.

[0035] The two rod ends are rotatably connected to the corresponding pins 622 as follows: Figure 5 As shown. A pressure sensor 611 and a connecting member 612 are provided on the two rod ends respectively. The connecting member 612 is rotatably sleeved on the corresponding pin shaft 622. The pressure sensor 611 is provided between the second straight rod end and the connecting member 612. The pressure sensor 611 is used to detect the pressure applied by the rod end to the connecting member 612, so that the radial load applied to the rotating shaft 220 can be calculated according to the detection result of the pressure sensor 611.

[0036] refer to Figure 4 As shown, in this embodiment, a limiting hole 601 is provided on a support plate 621 and penetrates the support plate 621 along the thickness direction of the support plate 621, and a limiting plate 110 inserted into the limiting hole 601 is fixedly provided on the base 100. Through the limiting plate 110, the support plate 621 can be prevented from rotating when the second linear power output unit 610 is installed.

[0037] In this embodiment, the simulation technology further includes an inertia simulation mechanism 700 disposed on the rotating shaft 220 to simulate the inertia moment of the rotating shaft 220 when rotating, and simulate the centrifugal force of the rotating shaft 220 when rotating. The inertia simulation mechanism 700 of this embodiment specifically includes an inertia disk mounting seat and a plurality of inertia disks 730. The inertia disk mounting seat is fixedly connected to the rotating shaft 220 and is located on one side of the rotating shaft 220. Each inertia disk 730 is detachably disposed on the inertia disk mounting seat.

[0038] In this embodiment, by providing the above-mentioned inertia disk mounting seat and each inertia disk 730 , inertia disks 730 of different weights can be installed on the inertia disk mounting seat to simulate different inertia moments of the rotary actuator 200 .

[0039] In this embodiment, the inertia disk mounting seat includes two fan-shaped mounting plates 710 that are fixedly connected to the rotating shaft 220. The two mounting plates 710 are spaced apart along the axial direction of the rotating shaft 220 and are respectively fixedly connected to the movable ears 221 of the rotating shaft 220. A connecting plate 720 connecting the two mounting plates 710 is provided between the two mounting plates 710, and an inertia disk 730 is detachably provided on the outer surfaces of the two mounting plates 710. The output shaft of the aforementioned torque loading mechanism 300 is connected to the mounting plate 710 close to the torque loading mechanism 300 through a cross shaft.

[0040] For specific structure, refer to Figures 1 to 3 As shown, a connecting sleeve 711 is fixedly provided on the mounting plate 710, which is coaxial with the rotating shaft 220 and is suspended on the rotating shaft 220. The output shaft of the torque loading mechanism 300 is specifically coaxially and fixedly connected to the connecting sleeve 711 through a cross shaft. The aforementioned thrust seat 440 is coaxially and fixedly connected to the connecting sleeve 711 on the mounting plate 710 close to the thrust seat 440. Bearings are respectively sleeved on the connecting sleeves 711 of the two mounting plates 710, and the aforementioned two support plates 621 are correspondingly sleeved on the two connecting sleeves 711, so that the mounting plate 710 can rotate relative to the support plate 621. By providing the above-mentioned two connecting sleeves 711, it is convenient to connect the torque loading mechanism 300, the axial load loading mechanism 400 and the radial load loading mechanism 600 with the rotating shaft 220.

[0041] refer to Figure 1 As shown, the connecting plate 720 of this embodiment is sandwiched between the two mounting plates 710 and fixedly connected to the two mounting plates 710 to connect the two mounting plates 710. The outer side of the mounting plate 710 refers to the side of the mounting plate 710 facing away from the connecting plate 720, and the inertia disk 730 can be detachably connected to the mounting plate 710 by bolts, for example.

[0042] In some embodiments, Figure 7 As shown, the inertia disk mounting seat includes two mounting plates 710 spaced apart along the axial direction of the rotating shaft 220, and the two mounting plates 710 are respectively provided with connecting sleeves 711 coaxial with the rotating shaft 220 and suspended on the rotating shaft 220. An adapter 740 is fixed on the movable ear 221 of the rotating shaft 220, and a plurality of inertia disks are stacked and fixed on the end surfaces of the two mounting plates 710 and the adapter 740 away from the rotating shaft 220.

[0043] Based on the above overall structure, the aircraft door actuator full-state load simulation technology of this embodiment can apply torque to the rotating shaft 220 to test the performance of the rotary actuator 200 when an axial load, a radial load and an inertia moment are applied to the rotating shaft 220 of the rotary actuator 200, thereby better testing the performance of the rotary actuator 200. In addition, the rotation of the rotary actuator 200 and the torque loading mechanism 300 of the aircraft door actuator full-state load simulation technology will not be transmitted to the axial load loading mechanism 400 due to the setting of the thrust bearing 430, and the swing of the rotary actuator 200 and the torque output of the torque loading mechanism 300 will not cause the swing of the radial load loading mechanism 600, so the output forces or moments of the torque loading mechanism 300, the axial load loading mechanism 400 and the radial load loading mechanism 600 will not produce coupling phenomenon.

[0044] The above are only preferred embodiments of the present invention and are 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 protection scope of the present invention.

Claims

1. A full-state load simulation technology for an aircraft door actuator, comprising a base and a rotary actuator, wherein the cylinder of the rotary actuator is fixedly mounted on the base, characterized in that: Also includes: The torque loading mechanism comprises a rotary power output unit arranged on the base, wherein the output shaft of the rotary power output unit is connected to the rotary shaft of the rotary actuator and can drive the rotary shaft to rotate; The axial load loading mechanism includes a first linear power output unit arranged on the base, and a load loading unit arranged on the telescopic rod of the first linear power output unit, wherein the load loading unit includes a thrust seat, which is rotatably mounted on the telescopic rod and connected to the rotating shaft, and the thrust seat can be pushed or pulled by the telescopic rod to apply an axial force to the rotating shaft along the rotating shaft.

2. The aircraft door actuator full-state load simulation technology according to claim 1 is characterized in that: It also includes a radial load loading mechanism arranged in the circumference of the rotating shaft; the radial load loading mechanism includes two second linear power output units and a bearing seat, the rotating shaft can rotate relative to the bearing seat, the two second linear power output units are arranged at intervals in the circumference of the rotating shaft, and the cylindrical ends of the two second linear power output units are respectively hinged to the base, and the rod ends of the two second linear power output units are respectively hinged to the bearing seat.

3. The aircraft door actuator full-state load simulation technology according to claim 2 is characterized in that: The bearing seat includes two support plates and two pins; the two support plates are respectively mounted on the rotating shaft, and the rotating shaft can rotate relative to the two support plates. The two support plates are arranged at intervals along the axial direction of the rotating shaft, and the two pins are respectively connected between the two support plates; the rod ends of the two second linear power output units are correspondingly rotatably connected with the two pins.

4. The aircraft door actuator full-state load simulation technology according to claim 3 is characterized in that: A pressure sensor and a connecting piece are respectively provided on the rod ends of the two second linear power output units. The connecting piece is rotatably mounted on the corresponding pin shaft, and the pressure sensor is arranged between the rod end of the second linear power output unit and the connecting piece.

5. The aircraft door actuator full-state load simulation technology according to claim 2, characterized in that: The output forces of the two second linear power output units intersect the axis of the rotating shaft at the same point.

6. The aircraft door actuator full-state load simulation technology according to claim 1, characterized in that: It also includes an inertia simulation mechanism; the inertia simulation mechanism includes an inertia disc mounting seat and a plurality of inertia discs, the inertia disc mounting seat is fixedly connected to the rotating shaft and is located on one side of the rotating shaft, and each of the inertia discs is detachably arranged on the inertia disc mounting seat.

7. The aircraft door actuator full-state load simulation technology according to claim 6 is characterized in that: The inertia disk mounting seat includes two fan-shaped mounting plates which are fixedly connected to the rotating shaft, the two mounting plates are spaced apart along the axial direction of the rotating shaft, and a connecting plate connecting the two mounting plates is provided between the two mounting plates, and the inertia disks are detachably provided on the outer sides of the two mounting plates; the output shaft of the torque loading mechanism is connected to the mounting plate close to the torque loading mechanism through a cross shaft.

8. The aircraft door actuator full-state load simulation technology according to claim 6, characterized in that: The inertia disk mounting seat comprises two mounting plates spaced apart along the axial direction of the rotating shaft, and a conversion piece is fixed on the rotating shaft, and a plurality of inertia disks are stacked and fixed on the end surfaces of the two mounting plates and the conversion piece away from the rotating shaft.

9. The aircraft door actuator full-state load simulation technology according to claim 3, characterized in that: It also includes an inertia simulation mechanism; the inertia simulation mechanism includes an inertia disc mounting seat and a plurality of inertia discs, the inertia disc mounting seat is fixedly connected to the rotating shaft and is located on one side of the rotating shaft, and each of the inertia discs is detachably arranged on the inertia disc mounting seat; the inertia disc mounting seat includes two mounting plates spaced apart along the axial direction of the rotating shaft, the two supporting plates are respectively arranged corresponding to the two mounting plates, and the mounting plates can rotate relative to the supporting plates.

10. The aircraft door actuator full-state load simulation technology according to any one of claims 1 to 8, characterized in that: A plurality of rotary actuators are arranged at intervals on the base, the torque loading mechanism and the axial load loading mechanism are respectively arranged at two ends of the rotary actuator, and a plurality of the rotary actuators share one axial load loading mechanism, and the output end of the axial load loading mechanism is connected to the rotary shaft of the rotary actuator; the rotary power output unit arranged corresponding to each rotary actuator is a motor, and a through hole is provided through the output shaft of the motor, and the rotary shafts of two adjacent rotary actuators are connected via a connecting shaft passing through the through hole.

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