CN114674547B - Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test - Google Patents
Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test Download PDFInfo
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- CN114674547B CN114674547B CN202210596264.2A CN202210596264A CN114674547B CN 114674547 B CN114674547 B CN 114674547B CN 202210596264 A CN202210596264 A CN 202210596264A CN 114674547 B CN114674547 B CN 114674547B
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- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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Abstract
The invention provides a boundary rigidity simulation system in a full-motion vertical fin buffeting test of an airplane strength test, and belongs to the technical field of airplane tests. The device comprises an installation bottom plate connected with the ground through foundation bolts, a boundary dynamic stiffness simulation assembly arranged on the installation bottom plate, and a rotary dynamic stiffness simulation assembly arranged on the installation bottom plate, wherein the boundary dynamic stiffness simulation assembly and the rotary dynamic stiffness simulation assembly are connected with a vertical tail of an airplane; the bending support dynamic stiffness of the full-motion vertical tail structure in a real state is simulated through the boundary dynamic stiffness simulation assembly, and the corresponding box section thickness can be designed according to the modal frequency of the first bending and the second bending of the vertical tail; the rotating rigidity simulation assembly simulates the rotating supporting dynamic rigidity of the full-motion vertical tail, different elastic element thicknesses can be designed according to the torsional mode frequency and the torsional mode frequency of the full-motion vertical tail, the consistency of the main modal frequency of the vertical tail structure in the ground installation state and the main modal frequency of the real flight state is effectively ensured, and the precision of the buffeting test result of the full-motion vertical tail in the airplane strength test is improved.
Description
Technical Field
The invention belongs to the technical field of airplane testing, and particularly relates to a boundary rigidity simulation system in a full-motion vertical tail buffeting test for airplane strength testing.
Background
The advanced fighter in China adopts a full-motion vertical tail design, and a vertical tail structure in the flight process of the fighter is subjected to conventional maneuvering load and random vibration load which covers the main modal frequency of the structure of the vertical tail and is caused by unsteady aerodynamic force when the fighter flies at a large attack angle.
In order to verify the reliability of the vertical tail structure under the superposition effect of the conventional maneuvering load and the buffeting random vibration load, a buffeting test of the vertical tail of the airplane needs to be carried out on the ground. An important key link for developing a ground test is to simulate a real installation state to fix the vertical fin structure on the ground, and the ground fixing device of the conventional static and fatigue test only simulates a support mode of the real structure and ensures that the strength of the fixing device meets the loading requirement, and the simulation of boundary dynamic stiffness is not considered, so that the main modal frequency of the vertical fin structure in the ground installation state is inconsistent with the main modal frequency of the real flight state. In a vertical tail buffeting test, the inconsistency of the main modal frequencies of the vertical tail structure can cause the inconsistency of the response and the real state of the vertical tail structure under buffeting random vibration loads, so that the effectiveness of a full-motion vertical tail buffeting test result is influenced. Therefore, a buffeting test system capable of simulating the dynamic stiffness of the vertical tail boundary is needed.
Disclosure of Invention
Aiming at the existing problems, the invention provides a boundary rigidity simulation system in a full-motion vertical tail buffeting test of an airplane strength test.
The technical scheme of the invention is as follows: a boundary stiffness simulation system in a full-motion vertical fin buffeting test for an airplane strength test comprises an installation base plate, a boundary dynamic stiffness simulation assembly and a rotary dynamic stiffness simulation assembly, wherein the installation base plate is connected with the ground through foundation bolts;
the boundary dynamic stiffness simulation assembly comprises a supporting box section arranged on an installation base plate, a lower bearing connecting flange arranged on the installation base plate, and an upper bearing connecting flange arranged at the upper end of the supporting box section and distributed opposite to the lower bearing connecting flange, wherein the inner walls of the lower bearing connecting flange and the upper bearing connecting flange are tightly pressed through a bearing cover plate, the thickness of a wall plate of the supporting box section is adjustable, and the side wall of the supporting box section is provided with an extending port;
the rotary rotation rigidity simulation assembly comprises a connecting base, an elastic element, two length adjusting pieces and connecting joints, wherein the connecting base is arranged on the mounting base plate and is distributed opposite to the extending inlet;
the aircraft vertical fin includes the vertical fin main part, locates bearing flange and upper bearing flange's connecting axle down just is used for connecting to hang down fin main part bottom, the connecting axle outer wall is from last to being equipped with upper bearing, rocking arm and lower bearing down in proper order, the upper bearing outer lane is connected with upper bearing flange inner race interference fit, the lower bearing outer lane is connected with lower bearing flange inner race interference fit, the rocking arm passes through joint bearing and extends to the attach fitting connection who supports in the box section.
Furthermore, a plurality of reinforcing plates are arranged between the connecting base and the mounting bottom plate, two reinforcing beams which are distributed in a crossed mode are arranged between every two adjacent reinforcing plates, the connecting tightness between the connecting base and the mounting bottom plate can be improved through the arrangement of the reinforcing plates, the overall dynamic rigidity of the connecting base is improved through the arrangement of the reinforcing beams, and the reliability of the simulation system is improved.
Furthermore, the left end and the right end of the length adjusting piece are respectively provided with a rotating thread, the left end and the right end of the length adjusting piece are respectively connected with the connecting joint and the elastic element through the rotating threads, each connecting part is provided with a locking nut, the length of the rotating dynamic stiffness simulation assembly can be changed through rotation along the axis, the change of the length can drive the rocker arm to move along the axis direction of the rotating dynamic stiffness simulation assembly, and the movement of the rocker arm can enable the full-motion vertical tail to rotate along the axis direction of the vertical tail large shaft, so that the purposes of adjusting and controlling the deflection angle and the full-motion vertical tail posture of the vertical tail are achieved.
Further, the boundary constraint conditions of the aircraft vertical fin are as follows: the upper bearing can translate along X, Y, Z three directions at the joint of the upper bearing and the upper bearing connecting flange and rotate around the X-axis and the Y-axis, and has 5 degrees of freedom, the lower bearing can translate along X, Y two directions at the joint of the lower bearing and the lower bearing connecting flange and rotate around the X-axis and the Y-axis, and has 4 degrees of freedom, and the rocker arm can translate along the X direction at the joint of the rocker arm and the connecting joint by 1 degree of freedom.
Further, elastic element includes the elasticity regulation section, locates the fixed connection section of elasticity regulation section left and right sides, the fixed connection section is connected with the length adjustment spare, the elasticity regulation section include the elasticity adjust the base member, with a plurality of thickness increase boards of elasticity regulation base member lateral wall joint, adjacent two the joint between the thickness increase board through add up a plurality of thickness increase boards layer by layer on the elasticity regulation base member to adjust the thickness of elasticity regulation base member, and the big dynamic stiffness of thickness numerical value is big more, satisfies the requirement that different borders supported dynamic stiffness.
Further, the cross-section of elasticity regulation section is U type or annular, and when the cross-section of elasticity regulation section was the annular, a plurality of thickness increase board cross-sections were the loop configuration, and each thickness increase board outside-in and radius reduce in proper order, and wherein, the biggest thickness increase board of radius and the inner wall joint of elasticity regulation section.
Furthermore, a plurality of mounting ports are arranged on the mounting base plate, a fastening connecting device is arranged in each mounting port, each fastening connecting device comprises a T-shaped fastening main body which is clamped in the mounting port and provided with a conical head at the bottom, a fastening mounting cavity arranged in the T-shaped fastening main body, a plurality of fastening insertion rods which are radially distributed in the circumferential direction of the T-shaped fastening main body and provided with first insertion ports at the side walls in a penetrating manner, a moving adjusting rod which is arranged in the fastening mounting cavity and provided with a sharp end at the bottom, sliding ports which are in one-to-one correspondence with the fastening insertion rods and communicated with the inside of the fastening mounting cavity are arranged on the outer wall of the T-shaped fastening main body, the fastening insertion rods extend to the inside of the fastening mounting cavity through the sliding ports, an adjusting spring is arranged between the outer wall of the fastening insertion rods and the sliding ports, a plastic film is pasted on the outer part of the first insertion ports, a plurality of second insertion ports which are in one-to-one correspondence with the first insertion ports are vertically arranged on the T-shaped fastening main body, the second socket is connected with the first socket through a screw, when the mounting bottom plate is required to be connected with the ground, the T-shaped fastening main body is rotated, the T-shaped fastening main body is inserted into the ground through a conical head at the bottom of the T-shaped fastening main body, the mounting bottom plate is fixed in the vertical direction, then the movable adjusting rod is moved towards the lower end of the fastening mounting cavity through an external tool, in the moving process, the tip end can push each fastening insertion rod to move towards the outside of the fastening mounting cavity, at the moment, each soil drilling cone moves towards each direction of the ground in a divergent mode, then each screw is inserted into the second socket through the corresponding first socket, the mounting bottom plate is fixedly connected with the ground through the fastening insertion rods in multiple points in the horizontal direction, through the process, the mounting bottom plate is firmly connected with the ground in the vertical and horizontal directions, and when external force is applied to the vertical tail of an airplane is avoided, the mounting bottom plate is separated from the ground, the normal operation of the airplane full-motion vertical fin buffeting test is influenced, and the overall reliability of the simulation system is improved.
Further, the height that highly is greater than the installation base plate thickness of T type fastening main part, and T type fastening main part outer wall all is equipped with the external screw thread, the bottom of screw rod is equipped with and is used for puncturing plastic film's puncture sword increases the connection compactness of T type fastening main part through the external screw thread, through setting up plastic film, makes the second socket covered, avoids boring the soil awl and makes the second socket take place to block up when removing to the horizontal direction.
Furthermore, each one side of being close to the fastening installation cavity on the fastening inserted bar is equipped with the draw runner, most advanced bottom be equipped with draw runner sliding connection's spout, the fastening inserted bar is last to keep away from fastening installation cavity one side and is equipped with the boring soil awl, boring soil awl outer wall is equipped with a plurality of needles of loosening the soil, through the connection of draw runner and spout, makes the fastening inserted bar can not break away from with most advanced bottom when removing, and interconnect between each component, increases the firm degree of integral connection.
The working process of the boundary rigidity simulation system in the full-motion vertical tail buffeting test of the airplane strength test is as follows:
s1, firstly, mounting the mounting bottom plate through the fastening and connecting devices at the mounting openings, wherein the specific mounting process is as follows: rotating the T-shaped fastening main body, inserting the T-shaped fastening main body into the ground through a conical head at the bottom of the T-shaped fastening main body, fixing the mounting bottom plate in the vertical direction, then enabling the movable adjusting rod to move towards the lower end of the fastening mounting cavity through an external tool, and in the moving process, pushing each fastening insertion rod to move towards the outside of the fastening mounting cavity through a tip end, wherein each soil drilling cone moves towards each direction of the ground in a divergent manner, and then inserting each screw rod into a second socket through a corresponding first socket, so that the mounting bottom plate is fixedly connected with the ground at multiple points in the horizontal direction through the fastening insertion rods;
s2, secondly, connecting the vertical tail of the airplane with the boundary dynamic stiffness simulation assembly and the rotary dynamic stiffness simulation assembly, wherein the specific connection process is as follows: connecting an upper bearing outer ring and an upper bearing connecting flange inner ring in an interference fit manner, connecting a lower bearing outer ring and a lower bearing connecting flange inner ring in an interference fit manner, and connecting a rocker arm with a connecting joint through a joint bearing;
s3, secondly, applying vibration load to the vertical tail main body to carry out a full-motion vertical tail buffeting test, wherein the specific test process is as follows: by applying the vibration load which is vertical to the wing surface of the vertical fin main body, at the moment, the vibration load can be twisted along the Z axis when being transmitted to the connecting shaft, and the twisting load can be transmitted to the supporting box section in the twisting process, at the moment, the supporting box section can simulate the bending supporting dynamic stiffness of the vertical fin main body in the real state, the dynamic stiffness of the bending boundary is determined by the dynamic stiffness of the supporting box section, and the dynamic stiffness of the supporting box section can be adjusted by changing the thickness of the wall plate of the supporting box section; when the vibration load is transmitted to the connecting shaft, the vertical tail main body rotates along the Z axis in the process of torsion, and due to the connecting action of the rocker arm, an axial load can be applied to the rotary dynamic stiffness simulation assembly, at the moment, the rotary dynamic stiffness simulation assembly can simulate the rotary supporting dynamic stiffness of the vertical tail main body, and the rotary dynamic stiffness of the vertical tail main body can be adjusted through the thickness of the elastic element;
and S4, finally, because the length of the length adjusting piece is adjustable, and the left end and the right end are respectively provided with the rotating threads, the length of the rotating dynamic stiffness simulation assembly can be changed by rotating along the axis, the change of the length can drive the rocker arm to move along the axis direction of the rotating dynamic stiffness simulation assembly, and the movement of the rocker arm can enable the vertical tail main body to rotate, so that the purpose of adjusting and controlling the deflection angle of the vertical tail main body is achieved, and the full-motion vertical tail posture is controlled.
Compared with the prior art, the invention has the beneficial effects that:
(1) the boundary rigidity simulation system provided by the invention has a simple structure, can simulate the first-bending, one-twisting, two-bending and two-twisting fourth-order modal frequencies of a full-motion vertical fin structure, can realize the attitude adjustment control of the full-motion vertical fin, and effectively solves the problem that the main modal frequency of the vertical fin structure in a ground installation state is inconsistent with the main modal frequency of a real flight state in a ground buffeting test of the full-motion vertical fin;
(2) in the full-motion vertical fin buffeting test, the boundary rigidity simulation system can simulate the constraint mode of a full-motion vertical fin structure in a real airplane structure and can simulate the boundary bending and torsional support dynamic rigidity of the full-motion vertical fin structure in the real airplane structure, so that the main modal frequency of the vertical fin structure is consistent with the real state in the ground buffeting test, meanwhile, the system can also simply adjust the rotation angle of the full-motion vertical fin to realize the posture control of the full-motion vertical fin structure, and the simulation of different support dynamic rigidities is realized simply by designing and replacing part of the structure of the system according to the different boundary support dynamic rigidity requirements of different vertical fins;
(3) according to the invention, the fastening connection device is arranged, so that the mounting bottom plate is firmly connected with the ground in the vertical and horizontal directions, the mounting bottom plate is prevented from being separated from the ground when external force is applied to the vertical tail of the airplane, the normal operation of a buffeting test of the full-motion vertical tail of the airplane is prevented from being influenced, and the overall reliability of the system is improved.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a view of the mounting of the rotary dynamic stiffness simulator assembly of the present invention on a mounting base;
FIG. 3 is a schematic view of the length adjustment member of the present invention;
FIG. 4 is a schematic view of the structure of the elastic member of the present invention;
FIG. 5 is a schematic structural view of an aircraft vertical fin of the present invention;
FIG. 6 is a schematic view of the installation of the fastening attachment of the present invention on a mounting plate;
wherein, 1-mounting bottom plate, 10-mounting opening, 2-boundary dynamic stiffness simulation component, 20-supporting box section, 200-extending opening, 21-lower bearing connecting flange, 22-upper bearing connecting flange, 23-bearing cover plate, 3-rotary dynamic stiffness simulation component, 30-connecting base, 300-reinforcing plate, 301-reinforcing beam, 31-elastic element, 310-elastic adjusting section, 311-fixed connecting section, 312-elastic adjusting base body, 313-thickness increasing plate, 32-length adjusting piece, 320-connecting double lugs, 321-connecting pin, 322-rotary thread, 33-connecting joint, 330-locking nut, 4-airplane vertical tail, 40-vertical tail main body, 41-connecting shaft, 410-upper bearing, 411-rocker arm, 412-lower bearing, 413-knuckle bearing, 5-fastening connecting device, 50-T-shaped fastening main body, 500-conical head, 501-sliding opening, 502-second socket, 503-screw, 504-external thread, 505-piercing cutter, 51-fastening mounting cavity, 52-fastening inserted rod, 520-first socket, 521-plastic film, 522-sliding strip, 523-earth-drilling cone, 524-ripping needle, 53-movable adjusting rod, 530-tip, 531-sliding chute and 54-adjusting spring.
Detailed Description
In order to further understand the contents of the present invention, the present invention is described in detail by examples below.
Example 1
As shown in fig. 1 and 2, the boundary stiffness simulation system in the full-motion vertical fin buffeting test for the airplane strength test comprises an installation base plate 1 connected with the ground through foundation bolts, a boundary dynamic stiffness simulation component 2 arranged on the installation base plate 1 and used for simulating the dynamic stiffness of the bending boundary of the full-motion vertical fin, and a rotary dynamic stiffness simulation component 3 arranged on the installation base plate 1 and used for simulating the rotary dynamic stiffness of the full-motion vertical fin, wherein the boundary dynamic stiffness simulation component 2 and the rotary dynamic stiffness simulation component 3 are connected with an airplane vertical fin 4;
three reinforcing plates 300 are arranged between the connecting base 30 and the mounting base plate 1, and two reinforcing beams 301 which are distributed in a crossed manner are arranged between two adjacent reinforcing plates 300;
the boundary dynamic stiffness simulation assembly 2 comprises a supporting box section 20 arranged on the mounting base plate 1, a lower bearing connecting flange 21 arranged on the mounting base plate 1, and an upper bearing connecting flange 22 arranged at the upper end of the supporting box section 20 and distributed opposite to the lower bearing connecting flange 21, wherein the inner walls of the lower bearing connecting flange 21 and the upper bearing connecting flange 22 are tightly pressed through a bearing cover plate 23, the thickness of a wall plate of the supporting box section 20 is adjustable, and the side wall of the supporting box section 20 is provided with an extending port 200;
the rotary dynamic stiffness simulation assembly 3 comprises a connecting base 30, an elastic element 31, two length adjusting pieces 32 and connecting joints 33, wherein the connecting base 30 is arranged on the mounting base plate 1 and is distributed opposite to the extending port 200, the two length adjusting pieces 32 are symmetrically arranged on the left side and the right side of the elastic element 31, the connecting joints 33 are connected with one sides of the length adjusting pieces 32 far away from the elastic element 31, one side of one connecting joint 33 far away from the length adjusting piece 32 is connected with the side wall of the connecting base 30 through a connecting double lug 320 and a connecting pin 321, and one side of the other connecting joint 33 far away from the length adjusting piece 32 can extend into the supporting box section 20 through the extending port 200;
as shown in fig. 3, the left and right ends of the length adjusting member 32 are respectively provided with a rotary thread 322, and the left and right ends of the length adjusting member 32 are respectively connected with the connecting joint 33 and the elastic element 31 through the rotary thread 322, and each connection part is provided with a lock nut 330;
as shown in fig. 5, the aircraft vertical fin 4 includes a vertical fin main body 40, and a connecting shaft 41 disposed at the bottom of the vertical fin main body 40 and used for connecting the lower bearing connecting flange 21 and the upper bearing connecting flange 22, wherein an outer wall of the connecting shaft 41 is sequentially provided with an upper bearing 410, a rocker arm 411 and a lower bearing 412 from top to bottom, an outer ring of the upper bearing 410 is connected with an inner ring of the upper bearing connecting flange 22 in an interference fit manner, an outer ring of the lower bearing 412 is connected with an inner ring of the lower bearing connecting flange 21 in an interference fit manner, and the rocker arm 411 is connected with a connecting joint 33 extending into the support box section 20 through a joint bearing 413;
the boundary constraints of the aircraft vertical fin 4 are as follows: the upper bearing 410 can translate along X, Y, Z three directions at the joint of the upper bearing and the upper bearing connecting flange 22 and rotate around the X-axis and the Y-axis, 5 degrees of freedom are total, the lower bearing 412 can translate along X, Y two directions at the joint of the lower bearing and the lower bearing connecting flange 21 and rotate around the X-axis and the Y-axis, 4 degrees of freedom are total, and the rocker arm 411 can translate 1 degree of freedom along the X direction at the joint of the rocker arm and the connecting joint 33;
as shown in fig. 4, the elastic element 31 includes an elastic adjusting section 310 and fixed connection sections 311 disposed on the left and right sides of the elastic adjusting section 310, the fixed connection sections 311 are connected to the length adjusting member 32, the elastic adjusting section 310 includes an elastic adjusting base 312 and thickness increasing plates 313 clamped to the side walls of the elastic adjusting base 312, two adjacent thickness increasing plates 313 are clamped to each other, and the overall thickness of the elastic element 31 can be adjusted by the thickness increasing plates 313 of different numbers; the section of the elastic regulation section 310 and the thickness increasing plate 313 is U-shaped.
Example 2
The present embodiment is different from embodiment 1 in that:
the section of the elastic adjusting section 310 and the section of the thickness increasing plate 313 are annular, and the thickness increasing plate 313 is clamped with the inner wall of the elastic adjusting section 310.
Example 3
The present embodiment is different from embodiment 2 in that:
as shown in fig. 1 and 6, the mounting base plate 1 is provided with 4 mounting ports 10, each mounting port 10 is provided with a fastening connection device 5, each fastening connection device 5 includes a T-shaped fastening main body 50 clamped in the mounting port 10 and provided with a conical head 500 at the bottom, a fastening installation cavity 51 arranged in the T-shaped fastening main body 50, 4 fastening insertion rods 52 radially distributed in the circumferential direction of the T-shaped fastening main body 50 and provided with first insertion holes 520 at the side wall thereof, a moving adjustment rod 53 arranged in the fastening installation cavity 51 and provided with a pointed end 530 at the bottom thereof, the outer wall of the T-shaped fastening main body 50 is provided with sliding holes 501 corresponding to the fastening insertion rods 52 one by one and communicating with the inside of the fastening installation cavity 51, the fastening insertion rods 52 extend into the fastening installation cavity 51 through the sliding holes 501, an adjustment spring 54 is arranged between the outer wall of the fastening insertion rods 52 and the sliding holes 501, a plastic film 521 is adhered to the outside of the first insertion holes 520, 4 second insertion holes 502 corresponding to the first insertion holes 520 are vertically arranged on the T-shaped fastening main body 50, the second socket 502 is connected with the first socket 520 through a screw 503;
the height of the T-shaped fastening main body 50 is twice of the thickness value of the installation bottom plate 1, the outer walls of the T-shaped fastening main body 50 are provided with external threads 504, and the bottom of the screw 503 is provided with a puncture knife 505 for puncturing the plastic film 521;
a sliding strip 522 is arranged on one side, close to the fastening installation cavity 51, of each fastening insertion rod 52, a sliding groove 531 in sliding connection with the sliding strip 522 is arranged at the bottom of the tip 530, an earth drilling cone 523 is arranged on one side, far away from the fastening installation cavity 51, of each fastening insertion rod 52, and 10 soil loosening needles 524 are arranged on the outer wall of the earth drilling cone 523.
Example 4
The present embodiment describes that the working process of the boundary stiffness simulation system in the full-motion vertical tail buffeting test of the aircraft strength test in embodiment 3 is as follows:
s1, first, the installation of the installation bottom plate 1 is performed through the fastening connection devices 5 at the installation ports 10, and the specific installation process is as follows: rotating the T-shaped fastening body 50, inserting the T-shaped fastening body 50 into the ground through a conical head 500 at the bottom of the T-shaped fastening body 50, fixing the mounting bottom plate 1 in the vertical direction, then moving the moving adjusting rod 53 to the lower end of the fastening mounting cavity 51 through an external tool, wherein in the moving process, the tip 530 pushes each fastening insertion rod 52 to move towards the outside of the fastening mounting cavity 51, at the moment, each earth drilling cone 523 moves in a divergent manner towards each direction of the ground, and then inserting each screw 503 into the second insertion hole 502 through the corresponding first insertion hole 520, so that the mounting bottom plate 1 is fixedly connected with the ground at multiple point positions in the horizontal direction through the fastening insertion rods 52;
s2, secondly, connecting the airplane vertical fin 4 with the boundary dynamic stiffness simulation assembly 2 and the rotary dynamic stiffness simulation assembly 3, wherein the specific connection process is as follows: the outer ring of the upper bearing 410 is connected with the inner ring of the upper bearing connecting flange 22 in an interference fit manner, the outer ring of the lower bearing 412 is connected with the inner ring of the lower bearing connecting flange 21 in an interference fit manner, and the rocker arm 411 is connected with the connecting joint 33 through the joint bearing 413;
s3, secondly, carrying out a full-motion vertical tail buffeting test by applying a vibration load to the vertical tail main body 40, wherein the specific test process is as follows: by applying the vibration load which is perpendicular to the wing surface of the vertical fin main body 40, at the moment, the vibration load can be twisted along the Z axis when being transmitted to the connecting shaft 41, and the twisting load can be transmitted to the supporting box section 20 in the twisting process, at the moment, the supporting box section 20 can simulate the bending supporting dynamic stiffness of the vertical fin main body 40 in the real state, the dynamic stiffness of the bending boundary is determined by the dynamic stiffness of the supporting box section 20, and the dynamic stiffness of the supporting box section 20 can be adjusted by changing the thickness of the wall plate of the supporting box section 20; when the vibration load is transmitted to the connecting shaft 41 and is twisted along the Z axis, the vertical fin main body 40 rotates, and due to the connecting action of the rocker 411, an axial load is applied to the rotary dynamic stiffness simulation assembly 3, at this time, the rotary dynamic stiffness simulation assembly 3 simulates the rotary supporting dynamic stiffness of the vertical fin main body 40, and the rotary dynamic stiffness of the vertical fin main body 40 can be adjusted through the thickness of the elastic element 31;
and S4, finally, because the length of the length adjusting piece 32 is adjustable, and the left end and the right end are respectively provided with the rotating threads 322, the length of the rotating dynamic stiffness simulation component 3 can be changed by rotating along the axis, the change of the length can drive the rocker 411 to move along the axis direction of the rotating dynamic stiffness simulation component 3, and the movement of the rocker 411 can enable the vertical tail main body 40 to rotate, so that the purpose of adjusting and controlling the deflection angle of the vertical tail main body 40 is achieved, and the full-motion vertical tail posture is controlled.
Claims (8)
1. The boundary stiffness simulation system in the full-motion vertical fin buffeting test for the airplane strength test is characterized by comprising an installation base plate (1) connected with the ground through foundation bolts, a boundary dynamic stiffness simulation assembly (2) arranged on the installation base plate (1) and used for simulating the dynamic stiffness of the bending boundary of the full-motion vertical fin, and a rotary dynamic stiffness simulation assembly (3) arranged on the installation base plate (1) and used for simulating the rotary dynamic stiffness of the full-motion vertical fin, wherein the boundary dynamic stiffness simulation assembly (2) and the rotary dynamic stiffness simulation assembly (3) are connected with an airplane vertical fin (4);
the boundary dynamic stiffness simulation assembly (2) comprises a supporting box section (20) arranged on the mounting base plate (1), a lower bearing connecting flange (21) arranged on the mounting base plate (1), and an upper bearing connecting flange (22) arranged at the upper end of the supporting box section (20) and distributed opposite to the lower bearing connecting flange (21), wherein the inner walls of the lower bearing connecting flange (21) and the upper bearing connecting flange (22) are tightly pressed through a bearing cover plate (23), the thickness of a wall plate of the supporting box section (20) is adjustable, and the side wall of the supporting box section (20) is provided with an extending opening (200);
the rotary rigidity simulation assembly (3) comprises a connecting base (30) which is arranged on the installation base plate (1) and is distributed opposite to the extending port (200), an elastic element (31), two length adjusting pieces (32) which are symmetrically arranged on the left side and the right side of the elastic element (31), and a connecting joint (33) which is connected with one side, far away from the elastic element (31), of the length adjusting pieces (32), wherein one side, far away from the length adjusting pieces (32), of the connecting joint (33) is connected with the side wall of the connecting base (30) through a connecting double lug (320) and a connecting pin (321), and one side, far away from the length adjusting pieces (32), of the other connecting joint (33) can extend into the supporting box section (20) through the extending port (200);
aircraft vertical fin (4) include vertical fin main part (40), locate vertical fin main part (40) bottom just is used for connecting axle (41) of bearing flange (21) and upper bearing flange (22) down, connecting axle (41) outer wall is from last to being equipped with upper bearing (410), rocking arm (411) and lower bearing (412) down in proper order, upper bearing (410) outer lane is connected with upper bearing flange (22) inner circle interference fit, lower bearing (412) outer lane is connected with lower bearing flange (21) inner circle interference fit, rocking arm (411) are connected through joint bearing (413) and connector (33) that extend to in supporting box section (20).
2. The system for simulating the boundary stiffness in the full-motion vertical tail buffeting test for the aircraft strength test according to claim 1, wherein a plurality of reinforcing plates (300) are arranged between the connecting base (30) and the mounting base plate (1), and two reinforcing beams (301) which are distributed in a crossed mode are arranged between every two adjacent reinforcing plates (300).
3. The system for simulating boundary stiffness in a full-motion vertical tail buffeting test for aircraft strength test of claim 1, wherein the length adjusting piece (32) is provided with a rotary thread (322) at each of the left and right ends, the left and right ends of the length adjusting piece (32) are connected with the connecting joint (33) and the elastic element (31) through the rotary thread (322), and a locking nut (330) is arranged at each connection.
4. The system for simulating the boundary stiffness in the full-motion vertical tail buffeting test for the aircraft strength test according to claim 1, wherein the elastic element (31) comprises an elastic adjusting section (310) and fixed connecting sections (311) arranged on the left side and the right side of the elastic adjusting section (310), the fixed connecting sections (311) are connected with the length adjusting piece (32), the elastic adjusting section (310) comprises an elastic adjusting base body (312) and a plurality of thickness increasing plates (313) clamped with the side walls of the elastic adjusting base body (312), and two adjacent thickness increasing plates (313) are clamped.
5. The system for simulating boundary stiffness in a full-motion vertical tail buffeting test for aircraft strength testing according to claim 4, wherein the cross section of the elastic adjusting section (310) is U-shaped or annular, when the cross section of the elastic adjusting section (310) is annular, the cross sections of the thickness increasing plates (313) are all annular structures, the radius of each thickness increasing plate (313) is reduced from outside to inside, and the thickness increasing plate (313) with the largest radius is clamped with the inner wall of the elastic adjusting section (310).
6. The system for simulating the boundary stiffness in the full-motion vertical tail buffeting test for the aircraft strength test according to claim 1, wherein a plurality of installation ports (10) are formed in the installation base plate (1), a fastening and connecting device (5) is arranged in each installation port (10), the fastening and connecting device (5) comprises a T-shaped fastening main body (50) clamped in the installation ports (10) and provided with a conical head (500) at the bottom, a fastening and installation cavity (51) arranged in the T-shaped fastening main body (50), a plurality of fastening inserted rods (52) radially distributed in the circumferential direction of the T-shaped fastening main body (50) and provided with first insertion holes (520) at the side walls in a penetrating manner, a moving adjusting rod (53) arranged in the fastening and installation cavity (51) and provided with a tip end (530) at the bottom, sliding ports (501) which are in one-to-one correspondence with the fastening inserted rods (52) and are communicated with the inside of the fastening and installation cavity (51) are arranged on the outer wall of the T-shaped fastening main body (50), fastening inserted bar (52) pass through inside sliding port (501) extend to fastening installation cavity (51), be equipped with between fastening inserted bar (52) outer wall and sliding port (501) adjusting spring (54), first socket (520) outside subsides are equipped with plastic film (521), vertically on T type fastening main part (50) be equipped with a plurality of with second socket (502) of first socket (520) one-to-one, just connect through screw rod (503) between second socket (502) and first socket (520).
7. The system for simulating the boundary stiffness in the full-motion vertical tail buffeting test of the aircraft strength test according to claim 6, wherein the height of the T-shaped fastening body (50) is larger than the thickness of the mounting base plate (1), the outer walls of the T-shaped fastening body (50) are provided with external threads (504), and the bottom of the screw rod (503) is provided with a puncture knife (505) for puncturing the plastic film (521).
8. The system for simulating the boundary stiffness in the full-motion vertical tail buffeting test for the aircraft strength test is characterized in that a slide bar (522) is arranged on one side, close to a fastening installation cavity (51), of each fastening inserted rod (52), a sliding groove (531) connected with the slide bar (522) in a sliding mode is arranged at the bottom of the tip (530), a drilling cone (523) is arranged on one side, far away from the fastening installation cavity (51), of each fastening inserted rod (52), and a plurality of soil loosening needles (524) are arranged on the outer wall of the drilling cone (523).
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN104034497A (en) * | 2014-04-25 | 2014-09-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Dynamic stiffness simulating assembly of booster |
| CN104122067A (en) * | 2013-04-24 | 2014-10-29 | 成都飞机设计研究所 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
| CN104819816A (en) * | 2015-05-13 | 2015-08-05 | 中国飞机强度研究所 | Dynamic load loading system and airplane vertical tail test system, and method |
| CN205209758U (en) * | 2015-12-08 | 2016-05-04 | 中国飞机强度研究所 | Aircraft vertical fin dynamic load loading device |
| CN107063624A (en) * | 2017-06-06 | 2017-08-18 | 大连理工大学 | A kind of device for simulating all movable rudder face flutter model bending support stiffness |
| CN107345847A (en) * | 2017-08-28 | 2017-11-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of entirely dynamic hinge elasticity support structure of aerofoil two of flutter wind tunnel model |
| CN109668716A (en) * | 2018-12-05 | 2019-04-23 | 中国航空工业集团公司成都飞机设计研究所 | A kind of experimental rig buffeted with simulation and apply quasi-static loads function |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10260376B2 (en) * | 2017-06-01 | 2019-04-16 | General Electric Company | Engine test stand mounting apparatus and method |
| CN107345846B (en) * | 2017-07-28 | 2019-04-16 | 大连理工大学 | A kind of free vertical and twisted coupling vibration flow tunnel testing device of large amplitude |
-
2022
- 2022-05-30 CN CN202210596264.2A patent/CN114674547B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN104122067A (en) * | 2013-04-24 | 2014-10-29 | 成都飞机设计研究所 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
| CN104034497A (en) * | 2014-04-25 | 2014-09-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Dynamic stiffness simulating assembly of booster |
| CN104819816A (en) * | 2015-05-13 | 2015-08-05 | 中国飞机强度研究所 | Dynamic load loading system and airplane vertical tail test system, and method |
| CN205209758U (en) * | 2015-12-08 | 2016-05-04 | 中国飞机强度研究所 | Aircraft vertical fin dynamic load loading device |
| CN107063624A (en) * | 2017-06-06 | 2017-08-18 | 大连理工大学 | A kind of device for simulating all movable rudder face flutter model bending support stiffness |
| CN107345847A (en) * | 2017-08-28 | 2017-11-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of entirely dynamic hinge elasticity support structure of aerofoil two of flutter wind tunnel model |
| CN109668716A (en) * | 2018-12-05 | 2019-04-23 | 中国航空工业集团公司成都飞机设计研究所 | A kind of experimental rig buffeted with simulation and apply quasi-static loads function |
Non-Patent Citations (3)
| Title |
|---|
| Flutter Analysis of T-tail with the Different Supporting Stiffness;Qiu, Ju 等;《PROCEEDINGS OF THE SECOND INTERNATIONAL CONFERENCE ON MODELLING AND SIMULATION (ICMS2009)》;20091231;第1卷;全文 * |
| 双垂尾抖振实验研究;李劲杰 等;《西北工业大学学报》;20050831;第23卷(第4期);全文 * |
| 机翼连接支持刚度模拟技术研究;张丽红 等;《工程与实验》;20190930;第59卷(第3期);全文 * |
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