CN114858389A

CN114858389A - Buffeting fatigue test device and method

Info

Publication number: CN114858389A
Application number: CN202210793324.XA
Authority: CN
Inventors: 王彬文; 何石; 黄文超; 傅波; 张治君
Original assignee: AVIC Aircraft Strength Research Institute
Current assignee: AVIC Aircraft Strength Research Institute
Priority date: 2022-07-07
Filing date: 2022-07-07
Publication date: 2022-08-05

Abstract

The invention provides a buffeting fatigue test device which is used for performing buffeting fatigue test on a vertical tail structure. In the buffeting fatigue test device, the supporting device is supported by the base frame and supports the vertical tail structure, and the fatigue loading actuator, the random vibration load loading actuator and the static load loading actuator are all supported by the base frame. The support device is arranged to be switchable between a first position and a second position relative to the base frame, in the first position, the fatigue loading actuator applies fatigue loads to the vertical tail structure supported by the support device, and in the second position, the static load loading actuator and the random vibration load loading actuator respectively apply static loads and random vibration loads to the vertical tail structure supported by the support device. The invention also provides a buffeting fatigue test method. The buffeting fatigue test device can meet fatigue life assessment of a vertical tail structure.

Description

Buffeting fatigue test device and method

Technical Field

The invention relates to a buffeting fatigue test device and a buffeting fatigue test method.

Background

The maneuvering flight capability of the large attack angle is an important technical index of the advanced fighter, and when the large attack angle flies, the vortex formed by airflow passing through the front airframe is broken, and a strong excitation effect is formed on the vertical tail structure, so that the vertical tail structure is seriously buffeted. The vertical tail structure can bear stronger buffeting random vibration load besides conventional maneuvering load during flying at a large attack angle, buffeting not only can influence the flight control performance and the flight quality of an airplane, and the fatigue life of the vertical tail structure can be remarkably shortened under the combined action of the conventional maneuvering load and the buffeting random vibration load. Therefore, for an advanced fighter with large attack angle maneuvering capability, the conventional fatigue test cannot reflect the real fatigue life of the vertical tail structure, and a buffeting fatigue test needs to be carried out.

Therefore, it is necessary to provide a buffeting fatigue test device capable of meeting fatigue life tests of the vertical tail structure.

Disclosure of Invention

The invention aims to provide a buffeting fatigue test device which can meet fatigue life assessment of a vertical fin structure.

The invention provides a buffeting fatigue test device which is used for performing buffeting fatigue test on a vertical tail structure. In the buffeting fatigue test device, the supporting device is supported by the base frame and supports the vertical tail structure, and the fatigue loading actuator, the random vibration load loading actuator and the static load loading actuator are all supported by the base frame. The support device is arranged to be switchable between a first position and a second position relative to the base frame, in the first position, the fatigue loading actuator applies a fatigue load to the vertical tail structure supported by the support device, and in the second position, the static load loading actuator and the random vibration load loading actuator respectively apply a static load and a random vibration load to the vertical tail structure supported by the support device.

In one embodiment, the base frame comprises a slide rail and the support device comprises a slide carriage slidably arranged on the slide rail, whereby the support device is arranged to be slidable from the first station to the second station.

In one embodiment, the buffeting fatigue testing apparatus includes a single random vibratory load loading actuator, a plurality of fatigue loading actuators, and a plurality of static loading actuators, wherein the single random vibratory load loading actuator applies a concentrated load to the airfoil of the vertical tail structure, and the plurality of fatigue loading actuators and the plurality of static loading actuators each apply a distributed load to the airfoil of the vertical tail structure.

In one embodiment, the slide rail has a first end and a second end in the sliding direction. The plurality of fatigue loading actuators are disposed in alignment with a first end of the slide rail, and the single random vibration load loading actuator and the plurality of static load loading actuators are disposed in alignment with a second end of the slide rail.

In one embodiment, the base frame further comprises an outrigger column and an outrigger frame. The fatigue loading actuators are respectively arranged in a mode of protruding from the bearing upright columns along the horizontal direction, so that the fatigue load in the horizontal direction is applied to the vertical tail structure. The force bearing frame is provided with two supports, the two supports are respectively positioned on two sides of the vertical tail structure in the thickness direction of the vertical tail structure, the single random vibration load loading actuator is supported by one of the two supports, and the plurality of static load loading actuators are divided into two parts of static load loading actuators which are respectively supported by the two supports.

In one embodiment, the fatigue loading actuator and the random vibrational load loading actuator are both linear actuators. The static load loading actuator is an air bag or an elastic rope.

In one embodiment, the base frame further comprises a force bearing column, the fatigue loading actuator is supported on a first side of the force bearing column, the force bearing column is provided with a counterweight on a second side to balance the fatigue loading actuator, wherein the first side and the second side are two opposite sides in a horizontal direction.

In one embodiment, the buffeting fatigue testing apparatus further includes a load sensor for sensing an applied load of the fatigue loading actuator, the random vibration load loading actuator, and/or the static load loading actuator.

In one embodiment, the buffeting fatigue testing apparatus further comprises a clamping mechanism, wherein the clamping mechanism comprises two clamping parts, and the clamping mechanism clamps the vertical tail structure through the two clamping parts. And the fatigue loading actuator and/or the random vibration load loading actuator applies load to the vertical tail structure through the clamping mechanism.

The invention also provides a buffeting fatigue test method, which adopts the buffeting fatigue test device and comprises the following steps: step S1, combing load working conditions and load spectrums which can generate buffeting according to airplane flight envelope lines and task profiles, decomposing airplane vertical tail buffeting fatigue load spectrums into maneuvering fatigue spectrums and buffeting random vibration load spectrums superposed with maneuvering mean value static loads, and determining two load cycle times according to airplane vertical tail expected fatigue life; step S2, mounting a vertical tail structure simulating the vertical tail of the airplane on a supporting device of the buffeting fatigue testing device, and enabling the supporting device to be located at a first station; step S3, starting the fatigue loading actuator to carry out fatigue loading; step S4, after fatigue loading of one cycle time is completed, the supporting device and the vertical tail structure are integrally switched to a second station; step S5, starting the static load loading actuator and the random vibration load loading actuator, and performing vibration superposition static load loading; step S6, after the vibration superposition static load test of the cycle time is completed, the supporting device returns to the first station; and S7, repeating the steps S3 to S6 until the whole service life buffeting fatigue test is completed or the vertical tail structure is broken, and stopping the test.

In the buffeting fatigue test device and method, the real load spectrum of the vertical tail structure is divided into the conventional maneuvering fatigue load spectrum and the buffeting random vibration load spectrum superposed with maneuvering static load, and the actual load condition of the vertical tail structure can be accurately simulated by switching the vertical tail structure between two sets of loading systems, so that the real fatigue life of the vertical tail structure can be accurately reflected, and the fatigue life test of the vertical tail structure is met.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a schematic view showing a vertical fin structure at a first station.

FIG. 2 is a schematic view showing the vertical fin structure at a second station.

FIG. 3 is a schematic diagram illustrating the loading of a pendulous structure by a fatigue loading actuator.

FIG. 4 is a schematic diagram illustrating a fatigue loading actuator.

FIG. 5 is a schematic diagram showing a static load actuator and a random vibratory load actuator loading a vertical tail structure.

Fig. 6 is a schematic diagram showing a static load applying actuator and a random vibration load applying actuator.

Detailed Description

The invention is further described in the following description with reference to the specific embodiments and the drawings, in which further details are set forth to provide a thorough understanding of the invention, but it will be obvious that the invention may be practiced otherwise than as described herein, and that the invention may be similarly generalized and deduced by those skilled in the art without departing from the spirit of the invention and therefore should not be limited by the contents of this specific embodiment.

For example, a first feature described later in the specification may be formed over or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

In the conventional buffeting fatigue test method for the vertical tail structure, a common method is to equate buffeting random vibration loads into a conventional maneuvering fatigue load spectrum and perform examination and verification in a full-machine fatigue test. In the method, the load equivalence can only ensure the damage equivalence of the main structure at the root of the vertical fin structure, and the fatigue life of the self structure of the vertical fin, particularly the local structures such as a stringer, an airfoil and the like, can not be verified to meet the design requirements, and the cycle number of the buffeting random vibration load after equivalence is very large and is far greater than the cycle number of the conventional maneuvering load spectrum, so that the fatigue test period can be greatly prolonged, and the test cost is increased.

Therefore, the invention provides a buffeting fatigue test device and method, which are used for decomposing the real load spectrum of the vertical tail structure and respectively providing the loading actuators, so that the real fatigue life of the vertical tail structure can be more accurately tested.

The buffeting fatigue test apparatus 10 is shown in fig. 1 and 2. The buffeting fatigue test apparatus 10 is used for performing a buffeting fatigue test on the vertical fin structure 20.

The buffeting fatigue test apparatus 10 includes a base frame 1 and a support device 2. The holding device 2 is supported by the base frame 1 and supports the vertical fin structure 20.

The buffeting fatigue testing device 10 further comprises a fatigue loading actuator 3, a random vibration load loading actuator 4 and a static load loading actuator 5. The fatigue loading actuator 3, the random vibration load loading actuator 4 and the static load loading actuator 5 are all supported by the base frame 1.

The support device 2 is arranged to be switchable between a first station P1 and a second station P2 with respect to the base frame 1. At a first station P1, the fatigue loading actuator 3 applies a fatigue load to the vertical fin structure 20 supported by the support device 2. At the second station P2, the static load applying actuators 5 and the random vibration load applying actuators 4 apply static loads and random vibration loads, respectively, to the vertical fin structure 20 supported by the support device 2.

The support means 2 is located at the bottom of the vertical fin structure 20 and may be connected to the large shaft of the vertical fin structure 20, for example, to support the vertical fin structure 20.

The fatigue loading actuator 3 may be a controllable actuator such as a hydraulic cylinder or an electric cylinder, for example, and applies a fatigue load. The random vibration load applying actuator 4 may be, for example, a high-frequency hydraulic actuator.

At the first station P1, the fatigue loading actuator 3 applies a fatigue load, i.e., a conventional motorized fatigue load, to the tail structure 20 supported by the support device 2. The first station P1 may also be referred to as a conventional motorized fatigue loading station. At the second station P2, the static load applying actuators 5 and the random vibratory load applying actuators 4 apply static loads and random vibratory loads, respectively, to the vertical tail structure 20 supported by the support device 2, i.e., buffeting random vibratory loads that superimpose the motor mean static loads on the vertical tail structure 20 as a whole. The second station P2 may also be referred to as a buffeting random vibratory load loading station.

In the buffeting fatigue test device 10, the real load spectrum of the vertical tail structure 20 is divided into a conventional maneuvering fatigue load spectrum and a buffeting random vibration load spectrum of superposed maneuvering static load, so that the fatigue loading actuators 3, the random vibration load loading actuators 4 and the static load loading actuators 5 which are respectively positioned at two stations are arranged, so that two sets of parallel loading systems can be used for respectively loading, the vertical tail structure 20 can be circularly switched between the two sets of loading systems, the real loading condition of the vertical tail structure 20 can be effectively simulated, and the fatigue life assessment of the vertical tail structure can be met. Moreover, the buffeting fatigue test device 10 is simple in structure, low in construction cost and short in period, and coupling among loads can be avoided, so that loading accuracy is guaranteed.

The base frame 1 comprises a slide rail 11. The support device 2 comprises a slide 21. The slide 21 is slidably arranged on the slide rail 11, whereby the support device 2 is arranged to be slidable from the first station P1 to the second station P2.

Referring to fig. 1, the chord direction of the vertical tail structure 20 coincides with the sliding direction X0 of the sliding base 21. The vertical fin structure 20 has two airfoil surfaces 201 on both sides in the thickness direction T0 of the vertical fin structure 20.

It will be understood that references herein to two directions being "perpendicular", "coincident", "parallel", etc. do not necessarily satisfy mathematically strict angular requirements, but allow for a range of tolerances, for example, within 20 ° compared to mathematically required angles, whereas "along" a direction means that there is at least a component in that direction, preferably within 45 ° and more preferably within 20 ° or even 5 ° from that direction.

Referring to FIG. 1, a buffeting fatigue test apparatus 10 includes a single random vibratory load applying actuator 4, a plurality of fatigue applying actuators 3, and a plurality of static load applying actuators 5. It is understood that "plurality" herein means more than two, including two, three, four, five, etc.

The single random vibratory load applying actuator 4 applies a concentrated load to the airfoil 201 of the vertical tail structure 20, while the plurality of fatigue loading actuators 3 and the plurality of static load applying actuators 5 each apply a distributed load to the airfoil 201 of the vertical tail structure 20. It will be appreciated that "concentrated loads", i.e. the single random vibratory load applying actuator 4, applies a random vibratory load to the vertical tail structure 20 at only one location, whereas "distributed loads", i.e. the plurality of fatigue loading actuators 3 or the plurality of static load applying actuators 5, each apply a load to the airfoil 201 of the vertical tail structure 20 at a plurality of locations, i.e. at least two locations, and not only one location.

With reference to fig. 1-6, a plurality of static load actuators 5 are symmetrically distributed across the vertical tail structure 20 in the thickness direction T0, thereby applying a distributed load to both airfoils 201.

Referring to fig. 1 and 2, the slide rail 11 may have a first end 111 and a second end 112 along the sliding direction X0. The plurality of fatigue loading actuators 3 are positioned to be aligned with a first end 111 of the slide rail 11 and the single random vibration load loading actuator 4 and the plurality of static load loading actuators 5 are positioned to be aligned with a second end 112 of the slide rail 11. Thus, when the slide rail 11 slides to the two ends, the two stations are respectively corresponded. For example, a stop device 113 may be provided at the first end 111,

with continued reference to fig. 1, the base frame 1 may further include a load-bearing column 12. The plurality of fatigue loading actuators 3 may be respectively provided to project from the force-bearing columns 12 in the horizontal direction, thereby applying a fatigue load in the horizontal direction to the vertical fin structure 20. The load-bearing columns 12 may be secured to the ground, for example by anchor bolts, to support the fatigue loading actuators 3. The root of the fatigue loading actuator 3 can be hinged with the bearing upright 12 through a connecting pin, for example.

The base frame 1 may further include an anchor frame 13. The force-bearing frame 13 may have two supports 131, and the two supports 131 are respectively located on both sides of the vertical fin structure 20 in the thickness direction T0 of the vertical fin structure 20. The aforementioned single random vibration load applying actuator 4 may be supported by one bracket 131 of the two brackets 131. The plurality of static load actuators 5 may be divided into two parts of the static load actuators 5 supported by the two brackets 131, respectively.

In the illustrated embodiment, the fatigue loading actuator 3 and the random vibrational load loading actuator 4 may both be linear actuators, for example. For example, the fatigue loading actuator 3 may be a hydraulic ram, the load applying ram of which is the piston rod of the hydraulic ram. The deadweight loading actuator 5 may be, for example, an air bag or a bungee cord. In particular, the air bag acts as a static load actuator 5 with low additional stiffness.

As mentioned above, the base frame 1 may further include a bearing upright 12. The fatigue loading actuator 3 may be supported on a first side of the load bearing column 12. The force bearing upright 12 is provided with a counterweight 6 on the second side to balance the fatigue loading actuator 3. Wherein the first side and the second side are two sides opposite to each other in the horizontal direction. For example, the first side is the side of the force-bearing column 12 that is closer to the vertical tail structure 20 or the slide rail 11, and the second side is the side of the force-bearing column 12 that is farther from the vertical tail structure 20 or the slide rail 11.

In the illustrated embodiment, the buffeting fatigue testing apparatus 10 may further include a load sensor 7 for sensing the applied load of the fatigue loading actuator 3, the random vibration loading actuator 4 and/or the static loading actuator 5. In the figure, the fatigue loading actuator 3, the random vibration load loading actuator 4, and the static load loading actuator 5 are denoted by a fatigue load sensor 7a, a static load sensor 7b, and a random load sensor 7c, respectively. The fatigue load sensor 7a may be connected to the front end of the fatigue loading actuator 3 so as to control the amount of load applied by the fatigue loading actuator 3 to the vertical fin structure 20.

Referring to fig. 3 and 4, the buffeting fatigue testing apparatus 10 may further include a holding mechanism 8. The gripping mechanism 8 includes two gripping portions 81. The clamping mechanism 8 can clamp the lug structure 20 by means of two clamping portions 81. The fatigue loading actuators 3 and/or the random vibration loading actuators 4 may apply a load to the droop structure 20 via the clamping mechanism 8.

For example, the clamping mechanism 8 to which the fatigue loading actuator 3 is attached may be a removable lever-catch plate 8 a. As mentioned above, the actuating rod 31 at the front end of the fatigue loading actuator 3 may be connected to one end of the fatigue load cell 7 by a screw thread, for example, and the other end of the fatigue load cell 7 may be hinged to the detachable lever-catch plate 8a by a connecting pin, for example. The detachable lever-catch plate 8a distributes the fatigue load applied by the fatigue loading actuator 3 to the loading points on the surface of the vertical fin structure 20 in the lever design ratio. Referring to fig. 1, the counterweight 6 can be connected to the detachable lever-clamp plate 8a connected to the fatigue loading actuator 3 by a weight-fastening wire rope 61 bypassing the pulley 62 disposed on the bearing upright 12, so as to avoid the influence of the deadweight of the fatigue loading actuator 3 and the detachable lever-clamp plate 8a on the loading precision, and the deadweight can be deducted by the counterweight 6 and the weight-fastening wire rope 61.

The clamping mechanism 8 to which the random vibrational load applying actuator 4 is attached may be a clamping type attachment device 8 b.

In the buffeting fatigue test device 10, the force-bearing upright post 12, the fatigue loading actuator 3, the detachable lever-clamping plate 8a, the fatigue load sensor 7a and the like can form a conventional maneuvering fatigue loading system, and conventional maneuvering fatigue spectrum loads can be applied to the vertical tail structure 20.

The force bearing frame 13, the random vibration load loading actuator 4, the static load loading actuator 5, the clamping type connecting device 8b, the

load sensors

7b and 7c and the like can form a buffeting random vibration loading system for superposing the dynamic mean value static load, and can apply vibration superposition static load to the vertical tail structure 20. The force bearing frame 13 can be fixed on the ground for example, so as to support the static load actuator 5 with low additional rigidity and the random vibration load actuator 4. One end of the static load actuator 5 can be connected to the force bearing frame 13 through the static load sensor 7b, and the other end acts on the surface of the vertical tail structure 20 as a test piece, so that static load loading is realized. Meanwhile, the low additional rigidity can avoid the influence of static load on the dynamic characteristics of the vertical tail structure 20, so that the effectiveness of the test is ensured. One end of the random vibration load loading actuator 4 can be connected with the bearing frame 13, and the other end can act on the vertical tail structure 20 through the random load sensor 7c, so that random vibration load is applied to the vertical tail structure 20. The random load sensor 7c may be a spoke type load sensor, for example. The force bearing frame 13 provides enough rigid support for the vibration loading actuator comprising the random vibration load loading actuator 4 and the static load loading actuator 5, so that the loading precision of the buffeting random vibration load is ensured.

The slide rail 11, the limiting device 113 and the supporting device 2 can form a ground supporting simulation system of the vertical tail structure, so that the real installation state of the vertical tail structure 20 can be simulated, and the force transmission path and the dynamic characteristics of the vertical tail structure 20 are consistent with those of the real structure. The ground support simulation system for the vertical fin structure can fix the vertical fin structure 20 on the ground, and simulate the support mode and the support dynamic stiffness of the vertical fin structure 20 in a real installation state. The supporting device 2 is positioned at the root of the vertical tail structure 20 and connected with the vertical tail large shaft to form a whole, the whole can circularly move between two sets of parallel loading systems along the slide rail 11 through the actuating device only by separating the loading device from the vertical tail wing surface, and meanwhile, the position consistency of the whole after each movement can be ensured through the limiting device 113.

The buffeting fatigue test apparatus 10 described above makes it possible to independently develop buffeting fatigue test verifications on the ground from the aircraft vertical tail structure 20. The buffeting fatigue testing device 10 may further include a coordinated loading controller, so as to perform coordinated loading control on the conventional maneuvering fatigue load and the maneuvering average static load. The buffeting fatigue test apparatus 10 described above may further include a vibration load loading controller to control buffeting random vibration load loading.

The invention also provides a buffeting fatigue test method. The buffeting fatigue test method uses the buffeting fatigue test apparatus 10 described above. The buffeting fatigue test method includes the following steps.

And S1, combing load working conditions and load spectrums which can generate buffeting according to the flight envelope lines and the task profiles of the airplane, decomposing the buffeting fatigue load spectrums of the vertical tails of the airplane into maneuvering fatigue spectrums and buffeting random vibration load spectrums which are superposed with maneuvering average static loads, and determining the cycle time of two loads according to the expected fatigue life of the vertical tails of the airplane.

Typically, the single cycle time does not exceed 15% of the expected life. For example, two load cycle times are determined to be 800 flight hours.

Step S2 is to attach the vertical fin structure 20 simulating the vertical fin of the aircraft to the support device 2 of the buffeting fatigue testing apparatus 10 so that the support device 2 is located at the first station P1.

That is, the vertical fin structure 20 may be installed in the support device 2 as desired, and then the support device 2 may be fixed to the first station P1 of the slide rail 11. The position of the vertical tail structure 20 can be determined by the limiting device 113 to meet the test requirements.

And step S3, starting the fatigue loading actuator 3 to carry out fatigue loading.

Namely, starting the conventional maneuvering fatigue load loading system and starting the conventional maneuvering fatigue test. Before the fatigue loading, it can be understood that the bearing upright post 12 and the bearing frame 13 can be installed at a designated position on the ground, the fatigue loading actuator 3 is installed at a specified loading point on the bearing upright post 12, the fatigue load sensor 7a is installed at the front end of the actuating rod 31 of the fatigue loading actuator 3, the detachable lever-clamping plate 8a is clamped at a specified position of the vertical tail structure 20, the position of the actuating rod 31 of the fatigue loading actuator 3 is adjusted, the fatigue load sensor 7 is connected with the detachable lever-clamping plate 8a, and the weight is connected with the counterweight 6 by the weight-fastening steel wire rope 61 bypassing the pulley 62, so that the influence of the dead weight of the detachable lever-clamping plate 8a on the loading precision is eliminated.

Step S4, after completing the fatigue loading for one cycle time, the supporting device 2 with the vertical fin structure 20 is entirely switched to the second station P2.

After a conventional fatigue loading of one cycle time, for example 800 flight hours, has been completed, the detachable lever-catch plate 8a can be removed and the remaining structure can remain. The entire vertical fin structure 20 and the support device 2 are then moved along the slide rails 11 to a second station P2, i.e., a designated position inside the outrigger frame 13, as shown in fig. 2.

And step S5, starting the static load loading actuator 5 and the random vibration load loading actuator 4, and performing vibration superposition static load loading.

It will be appreciated that prior to this, the static load applying actuator 5 and the random vibration load applying actuator 4 may be installed, and the random vibration load applying actuator 4 may be connected to the vertical fin structure 20 by the clamp-type connection means 8 b. That is, the static load applying actuator 5 and the random vibration load applying actuator 4 are connected to the vertical fin structure 20.

An air bag acting as a deadweight loading actuator 5 may be in contact with the vertical tail structure 20 after inflation. The load applied by each air bag can be controlled by a static load sensor 7c between the static load actuator 5 and the force bearing frame 13. After the static load is loaded to the load value of the specified working condition, the random vibration load loading actuator 4 can be started to load the random vibration load of the corresponding working condition, and the buffeting random vibration loading of all the superposed maneuvering average static loads within 800 flight hours of one-time circulation is completed in sequence.

Step S6, after the vibration superposition static load test of one cycle time is completed, the supporting device 2 is returned to the first station P1.

For example, the attachment of the static load applying actuators 5 and the random vibration load applying actuators 4 to the vertical fin structure 20 may be removed. Specifically, the clip-on connector 8b can be removed and the remaining structure held, after deflation of the air bag as the dead load actuator 5, disengaged from the surface of the vertical tail structure 20. The entire structure 20 and the support device 2 are then moved along the rails 11 to the first station P1, for example, by means of the stop device 113 ensuring that its position is identical to that previously.

And S7, repeating the steps S3 to S6 until the whole service life buffeting fatigue test is completed or the vertical tail structure 20 is broken, and stopping the test.

That is, after step S6, the detachable lever-catch plate 8a may be clamped and mounted to the vertical fin structure 20, the counterweight 6 may be further mounted, the position of the actuating rod 31 of the fatigue loading actuator 3 may be adjusted, the detachable lever-catch plate 8a may be connected to the fatigue load sensor 7, the conventional motorized fatigue loading system may be recovered, and then the process may be repeated. After the test is stopped, the whole test device can be dismantled.

The buffeting fatigue test method comprises the steps of combing the load working condition of a vertical tail structure under buffeting according to the load condition of the vertical tail structure under a real flight envelope curve and a mission profile, dividing the real load spectrum into a conventional maneuvering fatigue load spectrum and a buffeting random vibration load spectrum superposed with maneuvering static load based on a damage equivalence principle, respectively loading by utilizing two parallel loading systems, enabling the vertical tail structure to circularly move between the two loading systems, and setting a circulation period according to the flight mission profile to circularly load.

The buffeting fatigue test device and the buffeting fatigue test method can simultaneously realize fatigue life examination of the main structure and the local structure of the vertical fin, are simple in structure, low in construction cost and short in period, are simple and quick to disassemble in the cyclic loading process, and can avoid coupling among all loads, so that loading precision is guaranteed.

Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims

1. The utility model provides a buffeting fatigue test device for carry out buffeting fatigue test to the vertical fin structure, its characterized in that includes:

a base frame;

a support device supported by the base frame and supporting the vertical fin structure; and

the fatigue loading actuator, the random vibration load loading actuator and the static load loading actuator are all supported by the base frame;

the support device is arranged to be switchable between a first position and a second position relative to the base frame, in the first position, the fatigue loading actuator applies a fatigue load to the vertical tail structure supported by the support device, and in the second position, the static load loading actuator and the random vibration load loading actuator respectively apply a static load and a random vibration load to the vertical tail structure supported by the support device.

2. The buffeting fatigue testing apparatus recited in claim 1,

the base frame comprises a slide rail, and the support device comprises a slide seat which is slidably arranged on the slide rail, so that the support device is arranged to be slidable from the first station to the second station.

3. The buffeting fatigue testing apparatus recited in claim 2,

the chord direction of the vertical tail structure is consistent with the sliding direction of the sliding seat;

the buffeting fatigue test device comprises a single random vibration load loading actuator, a plurality of fatigue loading actuators and a plurality of static load loading actuators, wherein the single random vibration load loading actuator is right the airfoil of the vertical tail structure applies concentrated load, the plurality of fatigue loading actuators and the plurality of static load loading actuators are all right the airfoil of the vertical tail structure applies distributed load.

4. A buffeting fatigue testing apparatus as recited in claim 3 wherein said rail has a first end and a second end in the sliding direction;

the plurality of fatigue loading actuators are disposed in alignment with a first end of the slide rail, and the single random vibration load loading actuator and the plurality of static load loading actuators are disposed in alignment with a second end of the slide rail.

5. A buffeting fatigue testing apparatus according to claim 3,

the base frame further includes:

the fatigue loading actuators are respectively arranged in a protruding manner along the horizontal direction from the bearing upright column, so that the fatigue load in the horizontal direction is applied to the vertical tail structure; and

the force bearing frame is provided with two supports, the two supports are respectively positioned on two sides of the vertical tail structure in the thickness direction of the vertical tail structure, the single random vibration load loading actuator is supported by one of the two supports, and the plurality of static load loading actuators are divided into two parts of static load loading actuators which are respectively supported by the two supports.

6. A buffeting fatigue testing apparatus according to claim 1,

the fatigue loading actuator and the random vibration load loading actuator are both linear actuators;

the static load loading actuator is an air bag or an elastic rope.

7. The buffeting fatigue testing apparatus recited in claim 1,

the base frame further comprises a force bearing upright post, the fatigue loading actuator is supported on the first side of the force bearing upright post, a counterweight is arranged on the second side of the force bearing upright post to balance the fatigue loading actuator, and the first side and the second side are two opposite sides in the horizontal direction.

8. A buffeting fatigue testing apparatus as claimed in claim 1, further comprising a load sensor for sensing an applied load of said fatigue loading actuator, said random vibration load loading actuator and/or said dead load loading actuator.

9. The buffeting fatigue testing apparatus recited in claim 1,

the buffeting fatigue test device further comprises a clamping mechanism, wherein the clamping mechanism comprises two clamping parts, and the clamping mechanism clamps the vertical tail structure through the two clamping parts;

and the fatigue loading actuator and/or the random vibration load loading actuator applies load to the vertical tail structure through the clamping mechanism.

10. A buffeting fatigue testing method characterized by using the buffeting fatigue testing apparatus according to any one of claims 1 to 9, said buffeting fatigue testing method comprising:

step S1, combing load working conditions and load spectrums which can generate buffeting according to airplane flight envelope lines and task profiles, decomposing airplane vertical tail buffeting fatigue load spectrums into maneuvering fatigue spectrums and buffeting random vibration load spectrums superposed with maneuvering mean value static loads, and determining two load cycle times according to airplane vertical tail expected fatigue life;

step S2, mounting a vertical tail structure simulating the vertical tail of the airplane on a supporting device of the buffeting fatigue testing device, and enabling the supporting device to be located at a first station;

step S3, starting the fatigue loading actuator to carry out fatigue loading;

step S4, after fatigue loading of one cycle time is completed, the supporting device and the vertical tail structure are integrally switched to a second station;

step S5, starting the static load loading actuator and the random vibration load loading actuator, and performing vibration superposition static load loading;

step S6, after the vibration superposition static load test of the cycle time is completed, the supporting device returns to the first station;

and S7, repeating the steps S3 to S6 until the whole service life buffeting fatigue test is completed or the vertical tail structure is broken, and stopping the test.