Fatigue testing apparatus

Abstract

The application discloses a fatigue test device and relates to the technical field of transportation. The carrying device comprises a driving cabin and a carrying platform which are connected, the driving cabin contains a driving mechanism which is used for driving the carrying device to travel along a preset track; the driving cabin and the carrying platform are arranged along the traveling direction of the carrying device; along the direction of gravity, the top surface of the driving cabin is higher than that of the carrying platform; a frame structure is fixedly connected with the top surface of the carrying platform, the driving cabin and the frame structure are arranged at intervals along the traveling direction of the carrying device, and the top surface of the frame structure is used for mounting a manned aircraft. The carrying device can simulate the forward flight speed of the manned aircraft, the frame structure can improve the overall structural strength of the carrying platform, the carrying platform can offset the vibration caused by the manned aircraft, the influence of the manned aircraft on the structure thereof under the working condition of output flight lift can be verified, the number of cycles of the load spectrum can be reduced, and the verification efficiency of the fatigue test can be improved.

Description

Technical Field

[0001] This application relates to the field of transportation technology, and in particular to a fatigue testing device. Background Technology

[0002] With the rapid development of low-altitude flight, the application scenarios of manned aircraft such as rotorcraft are becoming increasingly diverse; correspondingly, the market demand for low-altitude aircraft products is becoming stronger. If product development and verification can be completed more efficiently, the competitiveness of the corresponding manned aircraft in the field of low-altitude flight will be improved.

[0003] In related technologies, fatigue testing of rotorcraft manned aircraft typically involves considering the operating conditions that the manned aircraft may encounter throughout its service life, thereby analyzing the stress state of the aircraft's airframe structure, compiling a fatigue load spectrum, and then building a test rig on the ground to install the aircraft airframe and loading system. The aircraft's operating conditions are then simulated by loading according to the load spectrum to complete the equivalent fatigue life verification.

[0004] However, the load states that the airframe structure of manned aircraft are subjected to are numerous and complex. The compilers have to go through tedious statistical analysis, screening, merging, conversion, simplification and arrangement to obtain a reasonable load spectrum that is representative of fatigue damage. The verification efficiency of fatigue life verification tests for manned aircraft needs to be improved. Summary of the Invention

[0005] The main objective of this application is to propose a fatigue testing device to improve the verification efficiency of fatigue testing.

[0006] To achieve the above objectives, the fatigue testing equipment proposed in this application is used to conduct fatigue tests on manned aircraft. The fatigue testing equipment includes a carrier device and a frame structure. The carrier device includes a drive cabin and a carrier platform connected to each other. The drive cabin houses a drive mechanism for driving the carrier device to travel along a preset trajectory. The drive cabin and the carrier platform are arranged along the travel direction of the carrier device. Along the direction of gravity, the top surface of the drive cabin is higher than the top surface of the carrier platform. The frame structure is fixedly connected to the top surface of the carrier platform. The drive cabin and the frame structure are spaced apart along the travel direction of the carrier device. The top surface of the frame structure is used to mount the manned aircraft.

[0007] In one implementation, the frame structure includes a support bracket, an elastic element, and a frame body. The support bracket is used to fix the crew cabin of the manned aircraft. The support bracket is located on the top side of the frame body, and at least one elastic element is provided between the support bracket and the frame body. The two ends of the elastic element are respectively connected to the support bracket and the frame body.

[0008] In another implementation, the frame structure further includes a limiting member, one end of which is rotatably connected to the frame body, and the other end of which is rotatably connected to the support bracket.

[0009] In another implementation, the frame body is provided with a first pivot that projects along the direction of gravity, and the axial direction of the first pivot forms an angle with the travel direction of the transport device; the end of the limiting member is rotatably connected to the first pivot, and the end of the limiting member can move axially along the first pivot; and / or, the support bracket is provided with a second pivot that projects along the direction of gravity, and the axial direction of the second pivot forms an angle with the travel direction of the transport device; the end of the limiting member is rotatably connected to the second pivot, and the end of the limiting member can move axially along the second pivot.

[0010] In another implementation, the frame body has first abutting protrusions at both ends of the first pivot, and the first abutting protrusions are spaced apart from the limiting member along the axial direction of the first pivot; the width of the limiting member is set along the axial direction of the first pivot, and the distance between the first abutting protrusions and the limiting member is less than or equal to the width of the limiting member; and / or, the support bracket has second abutting protrusions at both ends of the second pivot, and the second abutting protrusions are spaced apart from the limiting member along the axial direction of the second pivot; the width of the limiting member is set along the axial direction of the second pivot, and the distance between the second abutting protrusions and the limiting member is less than or equal to the width of the limiting member.

[0011] In another implementation, the frame body is provided with a first support column, which is spaced apart from the bottom surface of the crew cabin of the manned aircraft and is used to abut against the bottom surface of the crew cabin.

[0012] In another implementation, the frame structure includes a connecting frame, an adjustable frame, and a fixing mechanism. The connecting frame is fixedly connected to the top surface of the transport platform, and the adjustable frame is rotatably connected to the top surface of the connecting frame. The rotation axis of the adjustable frame is parallel to the horizontal plane and perpendicular to the travel direction of the transport device. One end of the fixing mechanism is connected to the connecting frame, and the other end of the fixing mechanism is connected to the adjustable frame. The fixing mechanism is used to fix the rotated adjustable frame relative to the connecting frame.

[0013] In another implementation, the frame body includes the connecting frame and the adjustable frame, the support bracket is disposed on the top side of the adjustable frame, and at least one elastic element is provided between the support bracket and the adjustable frame, with the two ends of the elastic element respectively connected to the support bracket and the adjustable frame.

[0014] In another implementation, the fixing mechanism includes a connecting rod and a fixing member. The connecting rod is rotatably connected to one of the connecting frame and the adjustable frame, and the fixing member is connected to the other of the connecting frame and the adjustable frame. After the adjustable frame is rotated, the fixing member is used to change the fixed position of the connecting rod.

[0015] In another implementation, the fixing member includes a rotating body and a positioning body. The rotating body is rotatably connected to the connecting frame or the adjustable frame. The rotating body has a through structure through which the connecting rod passes. Along the length of the connecting rod, the connecting rod has positioning bodies on both sides of the rotating body, and the positioning bodies on both sides of the rotating body abut against the rotating body.

[0016] In another implementation, at least one of the rotation axis of the connecting rod and the rotation axis of the rotating body is parallel to the rotation axis of the adjustable frame.

[0017] In another implementation, along the travel direction of the transport device, a fixing mechanism is provided between the rotation axis of the drive compartment and the adjustable frame; the connecting frame is provided with a second support column for supporting the bottom surface of the adjustable frame; along the travel direction of the transport device, the second support column is located on the side of the rotation axis of the adjustable frame opposite to the drive compartment, and / or another fixing mechanism is provided on the side of the rotation axis of the adjustable frame opposite to the drive compartment; and / or, one of the adjustable frame and the connecting frame is provided with a rotating frame, and the other of the adjustable frame and the connecting frame is provided with a fixing frame; the rotating frame includes two spaced-apart uprights, the two uprights are parallel, and the surface of the uprights is parallel to the travel direction of the transport device; the fixing frame is at least partially accommodated between the two uprights. The two oppositely arranged outer sides of the fixed frame respectively abut against the surfaces of the two upright plates, and the fixed frame is rotatably connected to the upright plates; and / or, the frame structure includes a first frame and a second frame, the first frame is fixedly connected to the top surface of the transport platform; the second frame is fixedly connected to the top surface of the transport platform, and the first frame and the second frame are spaced apart along the travel direction of the transport device; the second frame is located on the side of the first frame facing away from the drive cabin, and the top surface of the second frame is used to install the manned aircraft; the second frame includes the connecting frame, the adjustable frame, and the fixing mechanism, and the connecting frame and the adjustable frame constitute the frame body; the first frame and the connecting frame are spaced apart along the travel direction of the transport device, and the connecting frame is located on the side of the first frame facing away from the drive cabin.

[0018] In another implementation, the frame structure includes a first frame and a second frame. The first frame is fixedly connected to the top surface of the carrier platform. The second frame is fixedly connected to the top surface of the carrier platform. The first frame and the second frame are spaced apart along the travel direction of the carrier device. The second frame is located on the side of the first frame facing away from the drive cabin. The top surface of the second frame is used to install the manned aircraft.

[0019] In another implementation, the manned aircraft includes a crew cabin and a flight rotor for operation during fatigue testing; the drive mechanism includes a fuel engine, and the fatigue testing equipment further includes a fuel tank system connected to the fuel engine for supplying fuel to the fuel engine; the first frame has a first accommodating space, and the fuel tank system is accommodated within the first accommodating space and installed on the transport platform.

[0020] In another implementation, the fatigue testing equipment includes a first wheel set and a second wheel set spaced apart along the travel direction of the transport device, the first wheel set and the second wheel set being respectively connected to the transport platform; projecting along the gravity direction, at least a portion of the first frame is located between the first wheel set and the second wheel set; and / or, the manned aircraft further includes a drive motor, the drive motor being drively connected to the flight rotor, the drive motor being used to drive the flight rotor to operate; the fatigue testing equipment further includes a power supply system, the power output terminal of the power supply system being connected to the drive motor, the power supply system being used to provide power to the drive motor; the second frame has a second accommodating space, the power supply system being accommodated in the second accommodating space and installed on the transport platform or the second frame; and / or, the fatigue testing equipment further includes a connecting frame, one end of the connecting frame being fixedly connected to the first frame, and the other end of the connecting frame being fixedly connected to the second frame; along the gravity direction, the top surface of the first frame is lower than the top surface of the second frame; from the first frame to the second frame, the connecting frame is inclined upwards.

[0021] In another implementation, along the direction of gravity, a support bracket disposed on the top surface of the second frame is higher than the top surface of the drive compartment, and the length direction of the support bracket is arranged along the travel direction of the transport device; along the travel direction of the transport device, the distance from the surface of the drive compartment facing the second frame to the support bracket is greater than the length of the support bracket.

[0022] In another implementation, along the direction of gravity, the height difference between the support bracket and the top surface of the drive compartment is greater than or equal to 1.5 meters; along the direction of travel of the transport device, the distance from the surface of the drive compartment facing the second frame to the support bracket is greater than or equal to 4.5 meters.

[0023] The technical solution of this application sets the fatigue testing equipment to include a carrier device and a frame structure. The carrier device includes a drive cabin and a carrier platform connected to each other. The drive cabin houses a drive mechanism for driving the carrier device along a preset trajectory. The drive cabin and the carrier platform are arranged along the direction of travel of the carrier device. Along the direction of gravity, the top surface of the drive cabin is higher than the top surface of the carrier platform. The frame structure is fixedly connected to the top surface of the carrier platform. The drive cabin and the frame structure are spaced apart along the direction of travel of the carrier device. The top surface of the frame structure is used to install a manned aircraft, thereby enabling the carrier device to travel along the preset trajectory to... It can simulate the forward flight speed of a manned aircraft; when the manned aircraft is subjected to fatigue testing by outputting flight lift, the flight lift of the manned aircraft can be offset by the gravity of the carrier device through the frame structure, and the frame structure fixed to the top surface of the carrier platform can improve the overall structural strength of the carrier platform. This is beneficial for the carrier platform to offset the vibration caused by the output flight lift of the manned aircraft, thus facilitating the verification of the impact of the manned aircraft on its own structure under the condition of outputting flight lift, thereby reducing the number of cycles of the load spectrum, shortening the test cycle, and improving the verification efficiency of fatigue testing. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0025] Figure 1 A schematic diagram illustrating the use of an embodiment of the fatigue testing equipment provided in this application;

[0026] Figure 2 This is a partial structural diagram of the second frame in one embodiment of this application;

[0027] Figure 3 This is a schematic diagram of the connection of the fixing mechanism in one embodiment of this application;

[0028] Figure 4 This is a schematic diagram of the connection frame in one embodiment of this application;

[0029] Figure 5 This is a schematic diagram of the connection of the support bracket in one embodiment of this application;

[0030] Figure 6 This is a schematic diagram of the connection of the limiting member in one embodiment of this application.

[0031] Explanation of icon numbers:

[0032] 10. Fatigue testing equipment; 100. Transport device; 110. Drive compartment; 120. Transport platform;

[0033] 130. First frame; 131. First accommodating space;

[0034] 140. Second frame; 141. Second containment space;

[0035] 142. Support bracket; 1421. Second pivot; 1422. Second abutment protrusion;

[0036] 143. Connecting frame; 1431. Fixing frame;

[0037] 144. Adjustable frame; 1441. Rotating frame; 1442. Vertical plate; 1443. First pivot; 1444. First abutting protrusion;

[0038] 145. Fixing mechanism; 1451. Connecting rod; 1452. Rotating body; 1453. Through structure;

[0039] 146. Second support column; 1471. Elastic element; 1472. Limiting element;

[0040] 148. First support column; 151. First wheel assembly; 152. Second wheel assembly; 160. Connecting frame;

[0041] 200. Manned aircraft; 210. Crew cabin; 220. Flight rotor.

[0042] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0043] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0044] It should be noted that if the embodiments of this application involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0045] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0046] With the rapid development of low-altitude flight, the application scenarios of manned aircraft such as rotorcraft are becoming increasingly diverse; correspondingly, the market demand for low-altitude aircraft products is becoming stronger. If product development and verification can be completed more efficiently, the competitiveness of the corresponding manned aircraft in the field of low-altitude flight will be improved.

[0047] In related technologies, fatigue testing of rotorcraft manned aircraft typically involves considering the operating conditions that the manned aircraft may encounter throughout its service life, thereby analyzing the stress state of the aircraft's airframe structure, compiling a fatigue load spectrum, and then building a test rig on the ground to install the aircraft airframe and loading system. The aircraft's operating conditions are then simulated by loading according to the load spectrum to complete the equivalent fatigue life verification.

[0048] However, the load states that the airframe structure of manned aircraft are subjected to are numerous and complex. The compilers have to go through tedious statistical analysis, screening, merging, conversion, simplification and arrangement to obtain a reasonable load spectrum that is representative of fatigue damage. The verification efficiency of fatigue life verification tests for manned aircraft needs to be improved.

[0049] Therefore, this application proposes a fatigue testing device to improve the verification efficiency of fatigue testing.

[0050] Reference Figure 1In one embodiment of this application, the fatigue testing equipment 10 is used to conduct fatigue tests on the manned aircraft 200, which can be understood as verifying the fatigue life of the manned aircraft 200. The manned aircraft 200 can be configured as a rotorcraft, for example, the manned aircraft 200 may include a crew cabin 210 and flight rotors 220. The crew cabin 210 can be used to carry passengers or cargo, and the flight rotors 220 provide lift through the rotation of their blades. Furthermore, multiple flight rotors 220 can be spaced apart on the top of the crew cabin 210; the top of the crew cabin 210 may be equipped with a frame, which may include arms, and the flight rotors 220 may be located at the end of the arms away from the crew cabin 210, which can be understood as the flight rotors 220 being located at the ends of the arms. For example, in... Figure 1 In the middle, the support on the top of the crew cabin 210 includes six arms, and six flight rotors 220 are respectively installed at the ends of the six arms; of course, the support on the top of the crew cabin 210 may include four arms, and four flight rotors 220 are respectively installed at the ends of the four arms.

[0051] It is understandable that the manned aircraft 200 may also provide lift through the airfoil of the wing or through the rotor duct, and this embodiment does not limit this.

[0052] Please continue to refer to Figure 1 The aforementioned fatigue testing equipment 10 includes a transport device 100 and a frame structure. The transport device 100 includes a drive compartment 110 and a transport platform 120 connected to each other. The drive compartment 110 houses a drive mechanism used to drive the transport device 100 along a preset trajectory. For example, the transport device 100 can be configured as a truck, the drive compartment 110 as the truck cab, and the transport platform 120 as the truck trailer. The truck-type transport device 100 can travel on roads such as circular tracks or straight tracks, thereby achieving travel along the preset trajectory. Of course, the transport device 100 can also be installed on a track, thereby achieving travel along the preset trajectory through the shape of the track; for example, the track corresponding to the transport device 100 can be configured as a circular track, a straight track, etc.

[0053] The drive compartment 110 and the transport platform 120 are arranged along the travel direction of the transport device 100, wherein the travel direction of the transport device 100 can be along... Figure 1 The X1 direction setting in the text, for example, the carrier 100 can be directed towards... Figure 1 Proceed to the left. Along the direction of gravity, for example, along... Figure 1 In the Z1 direction, the top surface of the drive compartment 110 is higher than the top surface of the transport platform 120, which can be understood as the drive compartment 110 protruding upwards from the transport platform 120. Furthermore, Figure 1 The width of the transport device 100 can be set along the Y1 direction in the figure.

[0054] In some embodiments, the frame structure may include a first frame 130 and a second frame 140; of course, the frame structure may also be configured as a single unit. The frame structure is fixedly connected to the top surface of the transport platform, for example, by fixing the first frame 130 and the second frame 140 to the top surface of the transport platform 120, for example, through welding, bolts, or other fasteners. The drive bay 110 and the frame structure (e.g., including the first frame 130 and the second frame 140) are spaced apart along the travel direction of the transport device 100, for example, along... Figure 1 The X1 direction is spaced apart. Where the frame structure includes a first frame 130 and a second frame 140, the first frame 130 and the second frame 140 can also be spaced apart along the travel direction of the transport device 100, for example, along... Figure 1 The X1 direction spacing is set; in addition, the second frame 140 can also be located on the side of the first frame 130 facing away from the drive compartment 110, for example... Figure 1 The drive compartment 110, the first frame 130, and the second frame 140 are arranged sequentially from left to right. The frame structure can be constructed using square steel pipes, round steel pipes, steel plates, etc. For example, the first frame 130 and the second frame 140 can be constructed using square steel pipes and round steel pipes, respectively, and the first frame 130 and the second frame 140 can also be constructed using steel plates, etc.

[0055] The top surface of the frame structure is used to mount the manned aircraft 200. For example, the manned aircraft 200 can be mounted on the top surface of the second frame 140, and the manned aircraft 200 can be fixed by means of fasteners such as snap-fit ​​structures, bolts, and binding ropes. After the manned aircraft 200 is mounted on the top surface of the frame structure, such as the top surface of the second frame 140, the travel direction X2 of the manned aircraft 200 can be parallel to the travel direction X1 of the transport device 100, the width direction Y2 of the manned aircraft 200 can be parallel to the width direction Y1 of the transport device 100, and the height direction Z2 of the manned aircraft 200 can be parallel to the height direction Z1 of the transport device 100, so that the travel direction X1 of the transport device 100 can represent the travel direction X2 of the manned aircraft 200.

[0056] In the above embodiment, the transport device 100 traveling along a preset trajectory can simulate the forward flight speed of the manned aircraft 200; when the manned aircraft 200 is subjected to fatigue testing by outputting flight lift (output through the operation of the flight rotor 220, or output through the airfoil of the wing), the flight lift of the manned aircraft 200 can be offset by the gravity of the transport device 100 through the frame structure (e.g., through the second frame 140), which can be understood as the transport device 100 with the manned aircraft 200 installed can be kept on the ground; and, fixed to the transport platform 120 The top frame structure (e.g., the first frame 130, the second frame 140) can improve the overall structural strength of the transport platform 120, which is beneficial for the transport platform 120 to offset the vibration caused by the output lift of the manned aircraft 200. It can be understood that the transport device 100 can withstand the vibration caused by the operation of the flight rotor 220, the vibration caused by the airfoil and airflow of the wing, etc., which makes it easier to verify the impact of the manned aircraft 200 on its own structure under the condition of outputting flight lift, thereby reducing the number of load spectrum cycles, shortening the test cycle, and improving the verification efficiency of fatigue test.

[0057] In some embodiments, where the manned aircraft 200 includes a rotor 220, the rotor 220 is used to operate in fatigue tests, thereby facilitating the simulation of the impact of vibrations generated by the operation of the rotor 220 on the structure of the manned aircraft 200, such as the crew cabin 210. The drive mechanism includes a fuel engine, and the fatigue testing equipment 10 also includes a fuel tank system, which may include at least one fuel reservoir. The fuel tank system is connected to the fuel engine, for example, via a fuel pipeline, and is used to supply fuel to the fuel engine, enabling the fuel engine to output power by burning fuel. The power output by the fuel engine can be transmitted via a drive shaft. (Refer to...) Figure 1 The first frame 130 has a first accommodating space 131, which can be understood as the first frame 130 being hollow inside to form the first accommodating space 131; the fuel tank system is accommodated in the first accommodating space 131 and installed on the transport platform 120, thereby saving the space occupied.

[0058] In this embodiment, the fuel tank system can provide fuel to the fuel engine by storing fuel; in addition, since the first frame 130 is located between the drive cabin 110 and the second frame 140 on which the manned aircraft 200 is installed, the fuel tank system housed in the first housing space 131 can further suppress the vibration in the middle of the transport platform 120 by the weight of the fuel, which is beneficial to better verify the impact of the vibration caused by the operation of the flight rotor 220 on the structure of the manned aircraft 200, such as the crew cabin 210.

[0059] In some implementations, refer to Figure 1 The fatigue testing equipment 10 includes a first wheel group 151 and a second wheel group 152 arranged at intervals along the travel direction of the transport device 100. For example, the first wheel group 151 and the second wheel group 152 are arranged along... Figure 1 The wheels are arranged sequentially along the X1 direction. The first wheel group 151 and the second wheel group 152 each include at least one pair of wheels. The first wheel group 151 and the second wheel group 152 are connected to the transport platform 120, for example, through a suspension or other structure. The projection is along the direction of gravity, for example, along... Figure 1 Projecting Z1, at least a portion of the first frame 130 is located between the first wheel group 151 and the second wheel group 152, thereby enabling the first frame 130 to better suppress the vibration of the portion of the transport platform 120 located between the first wheel group 151 and the second wheel group 152. Of course, referring to... Figure 1 The fatigue testing equipment 10 may also include a third wheel assembly, which can be connected to the aforementioned drive compartment 110, for example, through a suspension or other structure.

[0060] In some embodiments, the manned aircraft 200 also includes a drive motor, which is connected to the rotor 220 via a drive shaft, for example, in an indirect manner. This allows the drive motor to drive the rotor 220, for example, to rotate its blades. The fatigue testing equipment 10 also includes a power supply system, the power output of which is connected to the drive motor. The power supply system provides power to the drive motor; for example, it may include a generator connected to the aforementioned fuel engine to generate electricity; or it may include a power battery to provide power to the drive motor using the stored electrical energy. (See reference...) Figure 1 The second frame 140 has a second accommodating space 141, which can be understood as the second frame 140 being hollow to form the second accommodating space 141. The power supply system is housed in the second accommodating space 141 and installed on the transport platform 120 or the second frame 140. This reduces the space occupied by the second accommodating space 141 and helps to further suppress the vibration of the rear of the transport platform 120 by the weight of the power supply system. This helps to better verify the impact of the vibration caused by the operation of the flight rotor 220 on the structure of the manned aircraft 200, such as the crew cabin 210.

[0061] In some implementation methods, please continue to refer to Figure 1The fatigue testing equipment 10 also includes a connecting frame 160. One end of the connecting frame 160 is fixedly connected to the first frame 130, and the other end is fixedly connected to the second frame 140. This fixed connection can be achieved through welding or fasteners, thereby improving the relative stability between the first frame 130 and the second frame 140, and thus better verifying the impact of the operation of the flight rotor 220 on the structure of the manned aircraft 200. The connecting frame 160 can be constructed using steel pipes, steel plates, or similar structures. (The last sentence appears to be incomplete and possibly refers to a different topic: "along the direction of gravity, for example along...") Figure 1 In the Z1 direction, the top surface of the first frame 130 is lower than the top surface of the second frame 140, which can be understood as the second frame 140 protruding upward relative to the first frame 130; the direction from the first frame 130 to the second frame 140, for example along Figure 1 From left to right, the connecting frame 160 is tilted upwards, which facilitates further improvement of the relative stability between the first frame 130 and the second frame 140, thereby better verifying the impact of the operation of the flight rotor 220 on the structure of the manned aircraft 200 itself.

[0062] In some implementations, refer to Figure 1 The top surface of the second frame 140 is provided with a support bracket 142, which can be understood as the support bracket 142 being installed on the top surface of the aforementioned frame structure; the support bracket 142 is used to fix the crew cabin 210 of the manned aircraft 200; that is, the support bracket 142 can be understood as a frame structure that supports and supports the manned aircraft 200. Along the direction of gravity, for example along... Figure 1 In the Z1 direction, the support bracket 142 is higher than the top surface of the drive compartment 110, and the length direction of the support bracket 142 is arranged along the travel direction of the transport device 100, for example along... Figure 1 The X1 direction is set; along the travel direction of the transport device 100, for example along Figure 1 In the X1 direction, the drive compartment 110 faces the surface of the second frame 140 (e.g. Figure 1 The distance G from the right surface of the support bracket 142 to the support bracket 142 is greater than the length L of the support bracket 142.

[0063] In this embodiment, the fatigue testing equipment 10 reduces the interference of the drive cabin 110 on the incoming flow of the manned aircraft 200 in the height direction by making the support bracket 142 higher than the top surface of the drive cabin 110, thereby more accurately verifying the fatigue life of the manned aircraft 200; the distance G from the surface of the drive cabin 110 facing the second frame 140 to the support bracket 142 is greater than the length L of the support bracket 142, which helps to reduce the interference of the drive cabin 110 on the incoming flow of the manned aircraft 200 in the horizontal direction, thereby more accurately verifying the fatigue life of the manned aircraft 200.

[0064] In some embodiments, the height difference between the support bracket 142 and the top surface of the drive cabin 110 along the direction of gravity is greater than or equal to 1.5 meters (for example, it can be further set to greater than or equal to 2 meters), thereby further reducing the interference of the drive cabin 110 on the incoming flow of the manned aircraft 200 in the height direction, thus more accurately verifying the fatigue life of the manned aircraft 200. Along the travel direction of the carrier 100, the surface of the drive cabin 110 facing the second frame 140 is, for example... Figure 1 The distance G from the right side surface of the manned aircraft 110 to the support bracket 142 is greater than or equal to 4.5 meters (for example, it can be further set to greater than or equal to 6 meters), which helps to reduce the interference of the drive cabin 110 on the incoming flow of the manned aircraft 200 in the horizontal direction, thereby more accurately verifying the fatigue life of the manned aircraft 200.

[0065] In some implementations, refer to Figure 1 and Figure 2 The aforementioned frame structure includes a connecting frame 143, an adjustable frame 144, and a fixing mechanism 145. For example, the second frame 140 can include the connecting frame 143, the adjustable frame 144, and the fixing mechanism 145. The connecting frame 143 is fixedly connected to the top surface of the transport platform 120, for example, by welding, fastener connection, snap-fit, etc. The first frame 130 and the connecting frame 143 can be spaced apart along the travel direction of the transport device 100, with the connecting frame 143 located on the side of the first frame 130 facing away from the drive compartment 110. For example... Figure 2 The drive bay 110, the first frame 130, and the connecting frame 143 are arranged sequentially from left to right. The adjustable frame 144 is rotatably connected to the top surface of the connecting frame 143, thereby enabling adjustment of the spatial attitude of the adjustable frame 144. The rotation axis of the adjustable frame 144 can be referenced... Figure 2 The centerline of the adjustable frame 144, whose rotation axis is parallel to the horizontal plane and perpendicular to the direction of travel of the transport device 100, for example... Figure 2 The rotation axis of the adjustable frame 144 is parallel to the Y1 direction. One end of the fixing mechanism 145 is connected to the connecting frame 143, and the other end is connected to the adjustable frame 144. The fixing mechanism 145 is used to fix the adjusted frame 144 relative to the connecting frame 143 after rotation, so as to facilitate fixing the adjustable frame 144 after the spatial attitude adjustment is completed. The operator can first adjust the spatial attitude of the adjustable frame 144, and then fix the adjustable frame 144 using the fixing mechanism 145, before conducting fatigue tests.

[0066] Manned aircraft 200 with flight rotors 220 typically need to tilt forward to move forward. This means the manned aircraft 200 maintains a relatively long period of steady forward flight while tilted forward, which may affect its fatigue life. In the above embodiment, the fatigue testing equipment 10, with the rotation axis of the adjustable frame 144 parallel to the horizontal plane and perpendicular to the direction of travel of the carrier device 100, combined with the fixing mechanism 145, keeps the manned aircraft 200 tilted forward. This facilitates the verification of the impact of the forward tilting condition of the manned aircraft 200 on its fatigue life.

[0067] In some implementations, refer to Figure 2 and Figure 3 The fixing mechanism 145 includes a connecting rod 1451 and a fixing member. The connecting rod 1451 is rotatably connected to one of the connecting frame 143 and the adjustable frame 144, and the fixing member is connected to the other of the connecting frame 143 and the adjustable frame 144. For example, the connecting rod 1451 can be rotatably connected to the connecting frame 143, and the fixing member can be connected to the adjustable frame 144; of course, the connecting rod 1451 can also be rotatably connected to the adjustable frame 144, and the fixing member can be connected to the connecting frame 143. This embodiment does not limit this. After the adjustable frame 144 rotates, the fixing member is used to change the fixed position of the fixing connecting rod 1451, thereby conveniently and quickly fixing the adjustable frame 144.

[0068] Specifically, the fixing component may include a rotating body 1452 and a positioning body, wherein the rotating body 1452 is rotatably connected to the connecting frame 143 or the adjustable frame 144; wherein the rotating body 1452 may be configured as a pin, etc. (Refer to...) Figure 3 The rotating body 1452 is provided with a through structure 1453, which can be a through hole or a notch. The connecting rod 1451 passes through the through structure 1453. Along the length of the connecting rod 1451, positioning bodies are provided on both sides of the rotating body 1452. The positioning bodies on both sides of the rotating body 1452 abut against the rotating body 1452, thereby facilitating and quickly fixing the adjustable frame 144. For example, the connecting rod 1451 can be provided with external threads, and the positioning bodies can be set as nuts, so that by tightening the nut-like positioning bodies, the positioning bodies on both sides of the rotating body 1452 abut against the rotating body 1452. Of course, the positioning bodies can also be set as inserts, binding ropes, etc., so that by inserting them into the insert holes or binding them, the positioning bodies on both sides of the rotating body 1452 abut against the rotating body 1452.

[0069] In some embodiments, at least one of the rotation axis of the connecting rod 1451 and the rotation axis of the rotating body 1452 is parallel to the rotation axis of the adjustable frame 144, thereby facilitating more accurate forward tilting of the manned aircraft 200 with the adjustable frame 144. For example, the rotation axis of the connecting rod 1451 and the rotation axis of the rotating body 1452 can be parallel to the rotation axis of the adjustable frame 144, for example, the rotation axis of the connecting rod 1451, the rotation axis of the rotating body 1452, and the rotation axis of the adjustable frame 144 can be parallel to... Figure 2 , Figure 3 The Y1 direction in the middle.

[0070] In some implementations, refer to Figure 1 and Figure 4 Along the direction of travel of the transport device 100, for example along Figure 4 In the X1 direction, the drive bay 110 (can be set in) Figure 4 (left side) and the rotation axis of the adjustable frame 144 (see left side) and the rotation axis of the adjustable frame 144 (see left side) Figure 4 The aforementioned fixing mechanism 145 is provided between the center lines of the adjustable frame 144; the connecting frame 143 is provided with a second support column 146, which can be supported by steel pipes or the like, and is used to support the bottom surface of the adjustable frame 144. An elastic buffer block can be provided on the top surface of the second support column 146 to reduce impact damage to the adjustable frame 144. Along the travel direction of the transport device 100, for example along... Figure 4 In the X1 direction, the second support column 146 is located on the side of the adjustable frame 144 opposite to the drive compartment 110 along the rotation axis. For example, the second support column 146 is located at... Figure 4 On the right side of the middle.

[0071] In this embodiment, when the adjustable frame 144 and the manned aircraft 200 swing backward from a forward tilting posture, the second support column 146 can prevent the adjustable frame 144 and the manned aircraft 200 from swinging backward excessively, which is beneficial to improving the safety of the fatigue testing equipment 10.

[0072] In some implementations, refer to Figure 4 The adjustable frame 144 has another fixing mechanism 145 on the side facing away from the drive compartment 110, for example... Figure 4 Another fixing mechanism 145 is provided on the right side of the adjustable frame 144, which facilitates the increase of fixing points for the adjustable frame 144 and helps to improve the reliability of fixing the adjustable frame 144.

[0073] In some implementations, refer to Figure 4One of the adjustable frame 144 and the connecting frame 143 is provided with a rotating frame 1441, and the other of the adjustable frame 144 and the connecting frame 143 is provided with a fixed frame 1431. For example, the adjustable frame 144 may be provided with a rotating frame 1441, and the connecting frame 143 may be provided with a fixed frame 1431; of course, the connecting frame 143 may also be provided with a rotating frame 1441, and the adjustable frame 144 may be provided with a fixed frame 1431. This embodiment does not limit this. The rotating frame 1441 includes two spaced-apart upright plates 1442, which are arranged in parallel. The surface of the upright plates 1442 is parallel to the traveling direction of the transport device 100. For example, Figure 4 The surface of neutral panel 1442 is parallel to plane X1Z1 in the figure. Figure 4 The adjustable frame 144 has two rotating frames 1441 on the front and rear sides respectively. Figure 4 The rotating frame 1441 on the front side only shows the outer upright plate 1442. Figure 4 The rotating frame 1441 on the middle and rear side can only see the inner upright plate 1442.

[0074] In addition, the fixed frame 1431 is at least partially accommodated between the two upright plates 1442. The two oppositely arranged outer surfaces of the fixed frame 1431 abut against the surfaces of the two upright plates 1442 respectively. It can be understood that the connection is made by surface contact. The fixed frame 1431 is rotatably connected to the upright plates 1442, so that the adjustable frame 144 can tilt forward more accurately.

[0075] In some implementations, refer to Figure 5 and Figure 6 The aforementioned frame structure also includes a support elastic element 1471 and a frame body, wherein the frame body may include the aforementioned connecting frame 143 and adjustable frame 144; furthermore, the frame body may only include the aforementioned connecting frame 143 and adjustable frame 144, which can be understood as the aforementioned connecting frame 143 and adjustable frame 144 constituting the frame body. The second frame 140 may include the aforementioned elastic element 1471.

[0076] The aforementioned support bracket 142 is located on the top side of the aforementioned frame body, for example, the support bracket 142 is located on the top side of the aforementioned adjustable frame 144; at least one elastic element 1471 is provided between the support bracket 142 and the frame body, for example, at least one elastic element 1471 is provided between the support bracket 142 and the adjustable frame 144, for example... Figure 5 The device includes four elastic elements 1471. Each elastic element 1471 may include a spring, or it may be configured as a spring damper, an air damper, or the like.

[0077] The two ends of the elastic element 1471 are respectively connected to the support bracket 142 and the frame body. For example, the two ends of the elastic element 1471 are respectively connected to the support bracket 142 and the adjustable frame 144, which can be abutment or plug-in connection. In addition, the frame structure also includes a limiting element 1472; one end of the limiting element 1472 is rotatably connected to the frame body, for example, one end of the limiting element 1472 is rotatably connected to the adjustable frame 144; in addition, the other end of the limiting element 1472 is rotatably connected to the support bracket 142. It is understandable that the rotatable connection between the limiting member 1472 and the frame body (e.g., the adjustable frame 144), and the rotatable connection between the limiting member 1472 and the support bracket 142, can each have movable space, thereby facilitating movement at the rotatable connection between the limiting member 1472 and the frame body (e.g., the adjustable frame 144), and the rotatable connection between the limiting member 1472 and the support bracket 142, when the elastic member 1471 changes length or length. Alternatively, the limiting member 1472 can also have a certain degree of elasticity to achieve extension and retraction. This allows the rotatable connection between the limiting member 1472 and the adjustable frame 144, and the rotatable connection between the limiting member 1472 and the support bracket 142 to be movable; or, the portions of the limiting member 1472, the frame body (e.g., the adjustable frame 144), and the support bracket 142 at the rotatable connection points can each have a certain elasticity and be able to extend and retract, for example, by providing a rubber pad layer, thereby allowing the rotatable connection between the limiting member 1472 and the frame body (e.g., the adjustable frame 144), and the rotatable connection between the limiting member 1472 and the support bracket 142 to be movable.

[0078] In this embodiment, if the carrier device 100 vibrates during travel due to bumps or other conditions, the elastic element 1471 can reduce the direct impact of the vibration from the carrier device 100 on the manned aircraft 200, which helps to reduce the impact of the carrier device 100, an external component, on verifying the fatigue life of the manned aircraft 200.

[0079] In some implementations, refer to Figure 5 and Figure 6 The frame body may be provided with a first pivot 1443, for example, the adjustable frame 144 may be provided with the first pivot 1443, and projected along the direction of gravity, for example along... Figure 6Projecting along the Z1 direction, the axial direction of the first pivot 1443 has an angle with the travel direction of the carrier 100. For example, the axial direction of the first pivot 1443 has an angle with the X1 direction and the Y1 direction in the figure, respectively, while the travel direction of the carrier 100 is parallel to the X1 direction in the figure. The end of the limiting member 1472 is rotatably connected to the first pivot 1443. The end of the limiting member 1472 can move along the axial direction of the first pivot 1443, thereby facilitating the manned aircraft 200 to sway relative to the first pivot 1443 along the travel direction and the width direction of the carrier 100. The swaying is buffered by the elastic member 1471, reducing the structural damage caused by the swaying of the manned aircraft 200.

[0080] In some implementations, refer to Figure 5 and Figure 6 The support bracket 142 may be provided with a second pivot 1421, which projects along the direction of gravity, for example along... Figure 6 Projecting along the Z1 direction, the axial direction of the second pivot 1421 forms an angle with the travel direction of the carrier 100. For example, the axial direction of the second pivot 1421 forms an angle with the X1 direction and the Y1 direction in the figure, respectively, while the travel direction of the carrier 100 is parallel to the X1 direction in the figure. The end of the limiting member 1472 is rotatably connected to the second pivot 1421, and the end of the limiting member 1472 can move along the axial direction of the second pivot 1421, thereby facilitating the manned aircraft 200 to sway relative to the second pivot 1421 along the travel direction and the width direction of the carrier 100, and the sway is buffered by the elastic member 1471, reducing the structural damage caused by the sway of the manned aircraft 200.

[0081] In some implementations, refer to Figure 6 The frame body has first abutment protrusions 1444 at both ends of the first pivot 1443. For example, the adjustable frame 144 has first abutment protrusions 1444 at both ends of the first pivot 1443. The first abutment protrusions 1444 can be formed from plates such as steel plates. The first abutment protrusions 1444 and the limiting member 1472 are spaced apart along the axial direction of the first pivot 1443. The width of the limiting member 1472 is set along the axial direction of the first pivot 1443. It can be understood that the width direction of the limiting member 1472 is parallel to the axial direction of the first pivot 1443. The distance between the first abutment protrusions 1444 and the limiting member 1472 is less than or equal to the width of the limiting member 1472. It can be understood that the distance between the first abutment protrusions 1444 and the limiting member 1472 is small, which makes it easier to suppress the sway amplitude of the manned aircraft 200 through the first abutment protrusions 1444.

[0082] In some implementations, refer to Figure 6 The support bracket 142 has second abutment protrusions 1422 at both ends of the second pivot 1421. The second abutment protrusions 1422 can be formed from plates such as steel plates. The second abutment protrusions 1422 and the limiting member 1472 are spaced apart along the axial direction of the second pivot 1421. The width of the limiting member 1472 is set along the axial direction of the second pivot 1421. It can be understood that the width direction of the limiting member 1472 is parallel to the axial direction of the second pivot 1421. The distance between the second abutment protrusions 1422 and the limiting member 1472 is less than or equal to the width of the limiting member 1472. It can be understood that the distance between the second abutment protrusions 1422 and the limiting member 1472 is small, which makes it easier to suppress the sway amplitude of the manned aircraft 200 through the second abutment protrusions 1422.

[0083] In some implementations, refer to Figure 5 and Figure 6 The frame body is provided with a first support column 148, for example, the adjustable frame 144 is provided with a first support column 148, which can be formed of steel pipe or the like; the first support column 148 is spaced apart from the bottom surface of the crew cabin 210 of the manned aircraft 200, and the first support column 148 is used to abut against the bottom surface of the crew cabin 210, thereby suppressing the swaying amplitude of the crew cabin 210 and the manned aircraft 200. The top surface of the first support column 148 can be provided with an elastic pad, which can be made of elastic materials such as rubber, thereby reducing impact damage to the bottom surface of the crew cabin 210.

[0084] The above description is merely an exemplary embodiment of this application and does not limit the patent scope of this application. Any equivalent structural transformations made based on the technical concept of this application and the contents of the specification and drawings of this application, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this application.

Claims

1. A fatigue testing device, characterized in that, The fatigue testing equipment is used to conduct fatigue tests on manned aircraft, and the fatigue testing equipment includes: A transport device includes a drive compartment and a transport platform connected to each other. The drive compartment houses a drive mechanism for driving the transport device to travel along a preset trajectory. The drive compartment and the transport platform are arranged along the direction of travel of the transport device. Along the direction of gravity, the top surface of the drive compartment is higher than the top surface of the transport platform. A frame structure is fixedly connected to the top surface of the carrier platform. The drive cabin and the frame structure are spaced apart along the travel direction of the carrier device. The top surface of the frame structure is used to install the manned aircraft.

2. The fatigue testing equipment as described in claim 1, characterized in that, The frame structure includes a support bracket, elastic elements, and a frame body, wherein the support bracket is used to fix the crew cabin of the manned aircraft. The support bracket is located on the top side of the frame body, and at least one elastic element is provided between the support bracket and the frame body. The two ends of the elastic element are respectively connected to the support bracket and the frame body.

3. The fatigue testing equipment as described in claim 2, characterized in that, The frame structure also includes a limiting member, one end of which is rotatably connected to the frame body, and the other end of which is rotatably connected to the support bracket.

4. The fatigue testing equipment as described in claim 3, characterized in that, The frame body is provided with a first pivot, which is projected along the direction of gravity. The axial direction of the first pivot is at an angle to the traveling direction of the transport device. The end of the limiting member is rotatably connected to the first pivot, and the end of the limiting member can move along the axial direction of the first pivot. And / or, The support bracket is provided with a second pivot, which is projected along the direction of gravity. The axial direction of the second pivot is at an angle to the traveling direction of the transport device. The end of the limiting member is rotatably connected to the second pivot, and the end of the limiting member can move along the axial direction of the second pivot.

5. The fatigue testing equipment as described in claim 4, characterized in that, The frame body has first abutting protrusions at both ends of the first pivot, and the first abutting protrusions are spaced apart from the limiting member along the axial direction of the first pivot; the width of the limiting member is set along the axial direction of the first pivot, and the distance between the first abutting protrusions and the limiting member is less than or equal to the width of the limiting member; and / or, The support bracket is provided with second abutting protrusions at both ends of the second pivot. The second abutting protrusions are spaced apart from the limiting member along the axial direction of the second pivot. The width of the limiting member is set along the axial direction of the second pivot, and the distance between the second abutting protrusions and the limiting member is less than or equal to the width of the limiting member.

6. The fatigue testing equipment as described in any one of claims 2 to 5, characterized in that, The frame body is provided with a first support column, which is spaced apart from the bottom surface of the crew cabin of the manned aircraft and is used to abut against the bottom surface of the crew cabin.

7. The fatigue testing equipment as described in claim 2, characterized in that, The frame structure includes a connecting frame, an adjustable frame, and a fixing mechanism. The connecting frame is fixedly connected to the top surface of the transport platform, and the adjustable frame is rotatably connected to the top surface of the connecting frame. The rotation axis of the adjustable frame is parallel to the horizontal plane and perpendicular to the travel direction of the transport device. One end of the fixing mechanism is connected to the connecting frame, and the other end of the fixing mechanism is connected to the adjustable frame. The fixing mechanism is used to fix the adjustable frame relative to the connecting frame after rotation.

8. The fatigue testing equipment as described in claim 7, characterized in that, The frame body includes the connecting frame and the adjustable frame. The support bracket is located on the top side of the adjustable frame. At least one elastic element is provided between the support bracket and the adjustable frame. The two ends of the elastic element are respectively connected to the support bracket and the adjustable frame.

9. The fatigue testing equipment as described in claim 7 or 8, characterized in that, The fixing mechanism includes a connecting rod and a fixing member. The connecting rod is rotatably connected to one of the connecting frame and the adjustable frame, and the fixing member is connected to the other of the connecting frame and the adjustable frame. After the adjustable frame is rotated, the fixing member is used to change the fixed position of the connecting rod.

10. The fatigue testing equipment as described in claim 9, characterized in that, The fixing component includes a rotating body and a positioning body, and the rotating body is rotatably connected to the connecting frame or the adjustable frame. The rotating body is provided with a through structure, and the connecting rod passes through the through structure; along the length direction of the connecting rod, the connecting rod is provided with positioning bodies on both sides of the rotating body, and the positioning bodies on both sides of the rotating body abut against the rotating body.

11. The fatigue testing equipment as described in claim 10, characterized in that, At least one of the rotation axis of the connecting rod and the rotation axis of the rotating body is parallel to the rotation axis of the adjustable frame.

12. The fatigue testing equipment as described in claim 7 or 8, characterized in that, Along the travel direction of the transport device, the fixing mechanism is provided between the rotation axis of the drive compartment and the adjustable frame; the connecting frame is provided with a second support column, which is used to support the bottom surface of the adjustable frame; along the travel direction of the transport device, the second support column is located on the side of the rotation axis of the adjustable frame opposite to the drive compartment, and / or another fixing mechanism is provided on the side of the rotation axis of the adjustable frame opposite to the drive compartment; And / or, One of the adjustable frame and the connecting frame is provided with a rotating frame, and the other of the adjustable frame and the connecting frame is provided with a fixed frame; the rotating frame includes two spaced-apart uprights, the two uprights are arranged in parallel, and the surface of the uprights is parallel to the traveling direction of the transport device; the fixed frame is at least partially accommodated between the two uprights, and the two oppositely arranged outer surfaces of the fixed frame abut against the surfaces of the two uprights respectively, and the fixed frame is rotatably connected to the uprights; And / or, The frame structure includes a first frame and a second frame. The first frame is fixedly connected to the top surface of the carrier platform. The second frame is also fixedly connected to the top surface of the carrier platform. The first frame and the second frame are spaced apart along the travel direction of the carrier device. The second frame is located on the side of the first frame facing away from the drive bay, and the top surface of the second frame is used to mount the manned aircraft. The second frame includes a connecting frame, an adjustable frame, and a fixing mechanism. The connecting frame and the adjustable frame constitute the frame body. The first frame and the connecting frame are spaced apart along the travel direction of the carrier device, and the connecting frame is located on the side of the first frame facing away from the drive bay.

13. The fatigue testing equipment as described in any one of claims 1 to 5, characterized in that, The frame structure includes a first frame and a second frame. The first frame is fixedly connected to the top surface of the carrier platform. The second frame is fixedly connected to the top surface of the carrier platform. The first frame and the second frame are spaced apart along the travel direction of the carrier device. The second frame is located on the side of the first frame facing away from the drive cabin. The top surface of the second frame is used to install the manned aircraft.

14. The fatigue testing equipment as described in claim 13, characterized in that, The manned aircraft includes a crew cabin and a flight rotor, which is used to operate during fatigue testing; The drive mechanism includes a fuel engine, and the fatigue testing equipment also includes a fuel tank system connected to the fuel engine, which is used to supply fuel to the fuel engine. The first frame has a first accommodating space, and the fuel tank system is accommodated in the first accommodating space and installed on the transport platform.

15. The fatigue testing equipment as described in claim 14, characterized in that, The fatigue testing equipment includes a first wheel group and a second wheel group arranged at intervals along the travel direction of the transport device, and the first wheel group and the second wheel group are respectively connected to the transport platform; Projected along the direction of gravity, at least a portion of the first frame is located between the first wheel set and the second wheel set; And / or, The manned aircraft also includes a drive motor, which is connected to the flight rotor and is used to drive the flight rotor to rotate; the fatigue testing equipment also includes a power supply system, the power output terminal of which is connected to the drive motor and is used to provide power to the drive motor; the second frame has a second accommodating space, and the power supply system is accommodated in the second accommodating space and installed on the carrier platform or the second frame; And / or, The fatigue testing equipment also includes a connecting frame, one end of which is fixedly connected to the first frame and the other end of which is fixedly connected to the second frame; Along the direction of gravity, the top surface of the first frame is lower than the top surface of the second frame; from the first frame to the second frame, the connecting frame is inclined upwards.

16. The fatigue testing equipment as described in claim 14, characterized in that, Along the direction of gravity, the support bracket provided on the top surface of the second frame is higher than the top surface of the drive compartment, and the length direction of the support bracket is arranged along the travel direction of the transport device; Along the direction of travel of the transport device, the distance from the surface of the drive compartment facing the second frame to the support bracket is greater than the length of the support bracket.

17. The fatigue testing equipment as described in claim 16, characterized in that, Along the direction of gravity, the height difference between the support bracket and the top surface of the drive compartment is greater than or equal to 1.5 meters; Along the direction of travel of the transport device, the distance from the surface of the drive compartment facing the second frame to the support bracket is greater than or equal to 4.5 meters.

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