CN114813001A - Vibration fatigue test system and method for low additional stiffness of airplane - Google Patents
Vibration fatigue test system and method for low additional stiffness of airplane Download PDFInfo
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- CN114813001A CN114813001A CN202210732790.7A CN202210732790A CN114813001A CN 114813001 A CN114813001 A CN 114813001A CN 202210732790 A CN202210732790 A CN 202210732790A CN 114813001 A CN114813001 A CN 114813001A
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- airplane
- air bag
- low additional
- airfoil structure
- airbag
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- 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
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0005—Repeated or cyclic
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/04—Chucks, fixtures, jaws, holders or anvils
- G01N2203/0411—Chucks, fixtures, jaws, holders or anvils using pneumatic or hydraulic pressure
Abstract
The invention relates to the technical field of airplane testing, and discloses a vibration fatigue testing system and a testing method for low additional stiffness of an airplane; the test system comprises a main mounting frame which is vertical to the horizontal ground and used for mounting the airplane airfoil structure, and a loading device which is used for applying load to the airplane airfoil structure; the loading device comprises a first loading device and a second loading device which are arranged on the airfoil structure of the airplane; the first loading device and the second loading device both comprise low additional rigidity air bag pairs; the low additional stiffness airbag pair consists of two low additional stiffness airbags which are respectively and correspondingly arranged on the upper surface and the lower surface of the airplane airfoil structure; the test method comprises the following steps: s1, clamping the airplane airfoil structure; s2, loading, adjusting pressure and carrying out a fatigue vibration test; the invention provides a vibration fatigue test system with low additional rigidity and small additional damping, which can improve the reliability of a vibration fatigue test of an airplane airfoil structure.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a vibration fatigue testing system and a vibration fatigue testing method for low additional stiffness of an airplane.
Background
The attendance rate and safety of the military aircraft are one of basic guarantees that the air force guarantees continuous fighting capacity and masters air control right; however, when the active battle aircrafts at home and abroad are examined, the severe vibration fatigue failure phenomenon appears to different degrees; one of the main reasons influencing the normal attendance rate of the military aircraft is the problems of vibration fatigue and the like; the aircraft structure is always in a vibration environment with a non-zero mean value in the use process, the static load, the conventional fatigue load and the vibration load are superposed on the aircraft structure to cause the aircraft structure to generate very complex vibration response, and when the response is excessive, the structure is subjected to fatigue damage, and then damage, namely vibration fatigue damage, is generated.
At the present stage, the vibration fatigue problem is more and more prominent due to the requirements of military aircraft stealth, multiple purposes, supersonic cruise, short-distance take-off and landing, high maneuverability and the like; although many times damage occurs to secondary load-bearing structures, it severely affects the safe flight and attendance of the aircraft. In order to timely and thoroughly solve the vibration fatigue problem exposed in the test flight process and the vibration fatigue problem occurring in the outfield use, a vibration fatigue ground test method based on a typical structure of an airplane needs to be developed urgently, so that the actual load of the airplane under the flying condition of the wings of the airplane can be accurately simulated, and the flying safety and the service life of the airplane are ensured;
the unit proposes to adopt the air bag to carry out vibration fatigue test on the airplane airfoil structure in the past years, and the problems of high additional rigidity and large additional damping of the air bag provided by the prior art in the test are deeply discovered along with the practice, so that the reliability of the vibration fatigue test of the airplane airfoil structure is greatly reduced, and the accurate vibration fatigue data is not easy to obtain.
Disclosure of Invention
Aiming at the technical problems, the invention provides a vibration fatigue test system with low additional rigidity and small additional damping, which improves the reliability of the vibration fatigue test of the airplane airfoil structure and is convenient to solve the problem of vibration fatigue of the airplane airfoil structure.
The technical scheme of the invention is as follows: a vibration fatigue test system for low additional stiffness of an airplane comprises a main mounting frame, a loading device and a vibration fatigue test device, wherein the main mounting frame is perpendicular to a horizontal ground and is used for mounting an airplane airfoil structure;
one end of the airplane wing surface structure is vertically connected with the main mounting frame through a connecting structure, and the other end of the airplane wing surface structure is suspended in the air;
the loading device comprises a first loading device and a second loading device which are arranged on the airplane airfoil structure;
the first loading device and the second loading device both comprise low additional rigidity air bag pairs; the low additional rigidity air bag pair consists of two low additional rigidity air bags which are respectively and correspondingly arranged on the upper surface and the lower surface of the airplane airfoil structure;
the low additional stiffness airbag includes an airbag contact portion in contact with an aircraft airfoil structure, an airbag loading portion disposed above the airbag contact portion, an airbag float portion disposed between the airbag contact portion and the airbag loading portion;
the air bag contact part comprises a contact clamping piece which is in contact with the surface of the airplane airfoil structure, and a rigid embedded piece which is arranged on the contact clamping piece and is used for enhancing rigidity;
the contact clamping piece comprises a circular contact layer and an arc-shaped turnover connecting ring arranged on the edge part of the circular contact layer; the rigid embedded part comprises first embedded strips, arc-shaped embedded strips and second embedded strips, wherein the first embedded strips are arranged on the circular contact layer and are uniformly distributed in the circumferential direction of the circular contact layer, the arc-shaped embedded strips are arranged on the first embedded strips and are positioned in the arc-shaped turnover connecting ring, and the second embedded strips are uniformly arranged on the first embedded strips and are annular;
the air bag floating part comprises a corrugated expansion ring with one end hermetically connected with the arc turnover connecting ring, and a rubber sealing cover which is arranged at the other end of the corrugated expansion ring and corresponds to the round contact layer;
the gasbag loading portion is in including setting up the outer outside rigidity safety cover of rubber seal lid evenly sets up gasbag on the outside rigidity safety cover, and set up and communicate on the gasbag the pressure regulating connecting piece of gasbag.
Further, the external rigid protection cover comprises a protection ring which is uniformly arranged on the rubber sealing cover and the center of the protection ring is superposed with the rubber sealing cover, an edge protection piece which is uniformly arranged on the protection ring, and a fixing structure which is arranged on the protection ring and used for fixing the air bag;
the fixing structure comprises a limiting stop lever, a clamping hook and a rigid connecting plate, wherein the lower end of the limiting stop lever is connected with the protection ring and evenly arranged around the side face of the air bag, the clamping hook is arranged at the upper end of the limiting stop lever and is in surface contact with the upper surface of the air bag, and the rigid connecting plate is arranged on the air bag and is connected with the clamping hook.
The rubber sealing cover can be effectively and rigidly protected by the arrangement of the external rigid protection cover, so that the rubber sealing cover is effectively prevented from being greatly expanded under high pressure; effective protection is implemented on the air bag loading part; the arrangement of the limiting stop lever, the clamping hook and the rigid connecting plate can effectively protect the outside of the air bag in a rigid way, so that the safety of the air bag is ensured.
Furthermore, an expansion assembly is arranged on the periphery of the arc-shaped turnover connecting ring;
expansion subassembly is including enclosing the clamping ring of establishing at the arc and turning over a curb periphery and contacting with aircraft airfoil structure, evenly sets up just run through the arc on the clamping ring and turn over a limit portion gas cell of curb and gasbag intercommunication, and set up and be in the annular air flue of clamping ring middle part and intercommunication limit portion gas cell.
The contact surface of the air bag contact part and the airplane airfoil structure can be further expanded through the arrangement of the expansion assembly; expanding the volume of the air bag contact part, wherein under the condition that the loading pressure is not changed, the larger the contact area of the air bag contact part is, the smaller the additional rigidity generated by the air bag is; in the case of the loading frequency determination, the smaller the additional stiffness is, the smaller the equivalent viscous damping coefficient of the airbag is, thereby ensuring that accurate vibration fatigue data is obtained.
Further, the first loading device further comprises a movement control assembly for moving the low additional stiffness airbag pair;
the mobile control assembly comprises side supports arranged at two sides of the airplane airfoil structure, a mobile truss movably arranged on the side supports, and a fixedly-connected moving piece movably arranged on the mobile truss and fixedly connected with the low-additional-rigidity air bag;
the rapid adjustment of the position of the air bag with low additional rigidity can be realized through the arrangement of the mobile control assembly, the effective clamping of different positions of the wing surface structure of the airplane is facilitated, and the test efficiency of the vibration fatigue test is improved.
Further, a first sliding groove is horizontally arranged on the side bracket;
the movable truss comprises two first rolling wheel sets which are movably arranged on the first sliding grooves respectively, two U-shaped steel rails which are arranged between the first rolling wheel sets in parallel and are positioned above and below the wing surface structure of the airplane respectively, and second sliding grooves which are arranged on the side edges of the U-shaped steel rails;
the fixed connection moving piece comprises a rigid connection cover arranged on the air bag loading part, a sliding connection plate fixed on the rigid connection cover and parallel to the U-shaped steel rail, and a second rolling wheel group arranged on the sliding connection plate and connected with a second sliding groove.
Through the arrangement of the first rolling wheel set and the first sliding groove, the movable truss can transversely move on the airplane wing surface; through the arrangement of the second rolling wheel set and the second sliding groove, the fixed connection moving piece can longitudinally move on the airplane airfoil surface, so that the low additional rigidity air bag can completely cover the airplane airfoil surface structure, and the vibration fatigue test can be rapidly carried out conveniently.
Furthermore, a telescopic assembly is arranged between the fixed connection moving piece and the movable truss;
because the aircraft wing surface structure is the curved surface structure, can adjust the vertical height of the solid joint moving member through the setting of flexible subassembly to guarantee that low additional rigidity gasbag can implement effectual centre gripping in the different positions of aircraft wing surface structure.
Further, the second loading device also comprises two brackets which are respectively arranged above and below the airplane airfoil structure, and two actuators which are respectively arranged between each bracket and the low additional rigidity air bag;
conventional fatigue loads can be applied to the aircraft airfoil structure through the provision of actuators.
Further, a vibration table is arranged on the airplane airfoil surface structure; the vibration table is used for exciting the airplane wing surface structure, so that the vibration frequency and the vibration amplitude of the airplane wing surface structure can be conveniently controlled.
The invention also discloses a vibration fatigue test method of the low additional stiffness of the airplane, and the vibration fatigue test system based on the low additional stiffness of the airplane comprises the following steps:
s1 airplane wing clamping structure
Connecting one end of the airplane wing surface structure with the main mounting frame, and suspending the other end of the airplane wing surface structure;
then selecting a position close to a suspended end of the airplane airfoil structure, and clamping the surface of the airplane airfoil structure up and down by adopting a low additional stiffness air bag;
s2, loading, adjusting pressure and carrying out fatigue vibration test
The pressure in the contact part of the air bag is increased and reaches the loading pressure by inflating the air bag through the pressure regulating connecting piece; reducing the additional rigidity of the airbag by increasing the contact area of the airbag contact portion;
by applying vibration to the airplane airfoil structure, the air bag floating part floats in the vibration state of the airplane airfoil structure, and meanwhile, the pressure of the low-additional-rigidity air bag pair is adjusted by combining the inflation and deflation of the pressure adjusting connecting piece until the vibration fatigue test is completed.
The invention has the beneficial effects that: the invention provides a vibration fatigue test system with low additional stiffness for an airplane.A wing surface structure of the airplane is clamped by arranging an air bag with low additional stiffness, and the actual using environment of the airplane is also air as the actuating medium of the air bag is air; the fatigue vibration condition of the airplane airfoil structure in a real environment can be effectively simulated; the air storage volume of the air bag with low additional rigidity is greatly improved by arranging the air bag contact part and the air bag floating part under the traditional air bag; under the same load pressure, due to the increase of the contact surface of the low additional rigidity airbag and the airplane airfoil structure, the additional rigidity and the additional damping of the low additional rigidity airbag body are greatly reduced; therefore, the influence on the vibration frequency of the airplane airfoil structure is effectively reduced, and accurate vibration fatigue data can be obtained conveniently.
Drawings
FIG. 1 is a schematic view of the overall structure of embodiment 1 of the present invention;
FIG. 2 is a schematic view showing the structure of a low additional rigidity bladder according to example 1 of the present invention;
FIG. 3 is a schematic view showing the structure of an air bag contact portion in example 1 of the present invention;
FIG. 4 is a schematic structural view of an airbag loading section in embodiment 1 of the invention;
FIG. 5 is a flow chart of the test method of example 2 of the present invention;
FIG. 6 is a schematic structural diagram of an expansion assembly according to embodiment 3 of the present invention;
FIG. 7 is a schematic structural diagram of a motion control assembly according to embodiment 4 of the present invention;
FIG. 8 is a schematic structural view of a movable truss according to embodiment 4 of the present invention;
FIG. 9 is a schematic view showing a structure of fixed moving parts according to embodiment 4 of the present invention;
FIG. 10 is a schematic structural view of an actuator according to embodiment 5 of the present invention;
the device comprises a main mounting frame 1, a 10-connecting structure, a 2-first loading device, a 20-side support, a 21-moving truss, a 22-fixedly-connected moving piece, a 200-first sliding groove, a 210-first rolling wheel group, a 211-U-shaped steel rail, a 212-second sliding groove, a 220-rigid connecting cover, a 221-sliding connecting plate, a 222-second rolling wheel group, a 3-second loading device, a 30-support, a 31-actuator, a 4-low additional rigidity air bag pair, a 40-air bag contact part, a 41-air bag loading part, a 42-air bag floating part, a 400-contact clamping part, a 401-rigid embedded part, a 402-circular contact layer, a 403-arc turnover connecting ring, a 404-first embedded strip, a 405-arc embedded strip, 406-a second embedded strip, 410-an external rigid protective cover, 411-an air bag, 412-a pressure regulating connector, 413-a protective ring, 414-an edge protector, 415-a limit stop lever, 416-a snap hook, 417-a rigid connecting plate, 420-a corrugated expansion ring, 421-a rubber sealing cover, 5-an expansion component, 50-a pressing ring, 51-an edge inflatable bag, 52-an annular air passage and 6-a vibration table.
Detailed Description
Examples
The vibration fatigue test system with low additional rigidity for the airplane as shown in FIG. 1 comprises a main mounting frame 1 which is perpendicular to a horizontal ground and is used for mounting an airplane airfoil structure, and a loading device which is used for applying load to the airplane airfoil structure;
one end of the airplane wing surface structure is vertically connected with the main mounting frame 1 through a connecting structure 10, and the other end of the airplane wing surface structure is suspended in the air;
the loading device comprises a first loading device 2 and a second loading device 3 which are arranged on the airplane airfoil structure;
the first loading device 2 and the second loading device 3 both comprise an airbag pair 4 with low additional rigidity; the low additional rigidity air bag pair 4 consists of two low additional rigidity air bags which are respectively and correspondingly arranged on the upper surface and the lower surface of the airplane airfoil structure;
as shown in fig. 2, the low additional stiffness airbag includes an airbag contact portion 40 that contacts the aircraft airfoil structure, an airbag loading portion 41 disposed above the airbag contact portion 40, an airbag floating portion 42 disposed between the airbag contact portion 40 and the airbag loading portion 41;
as shown in fig. 3, the airbag contact portion 40 includes a contact clamp 400 that contacts the surface of the aircraft airfoil structure, and a rigid embedded part 401 provided on the contact clamp 400 for enhancing rigidity;
the contact clamping piece 400 comprises a circular contact layer 402 and an arc-shaped turnover connecting ring 403 arranged at the edge of the circular contact layer 402; the rigid embedded part 401 comprises first embedded strips 404 which are arranged on the circular contact layer 402 and are uniformly distributed in the circumferential direction of the circular contact layer 402, arc-shaped embedded strips 405 which are arranged on the first embedded strips 404 and are positioned in the arc-shaped turnover connecting ring 403, and annular second embedded strips 406 which are uniformly arranged on the first embedded strips 404;
as shown in fig. 4, the airbag floating portion 42 includes a bellows 420 having one end hermetically connected to the arc-shaped folding connection ring 403, and a rubber sealing cover 421 disposed at the other end of the bellows 420 and corresponding to the circular contact layer 402;
the air bag loading part 41 comprises an external rigid protection cover 410 arranged on the outer layer of the rubber sealing cover 421, air bags 411 evenly arranged on the external rigid protection cover 410, and pressure regulating connecting pieces 412 arranged on the air bags 411 and communicated with the air bags 411.
The external rigid protection cover 410 comprises a protection ring 413 uniformly arranged on the rubber sealing cover 421 and the center of the protection ring is overlapped with the rubber sealing cover 421, an edge protection piece 414 uniformly arranged on the protection ring 413, and a fixing structure arranged on the protection ring 413 and used for fixing the air bag 411;
the fixing structure comprises a limit stop lever 415, a clamping hook 416 and a rigid connecting plate 417, wherein the lower end of the limit stop lever 415 is connected with a protection ring 413 and evenly arranged around the side face of the air bag 411, the clamping hook 416 is arranged at the upper end of the limit stop lever 415 and is in contact with the upper surface of the air bag, and the rigid connecting plate 417 is arranged on the air bag 411 and is connected with the clamping hook 416.
Wherein, the pressure regulating connector 412 is a pressure regulating device capable of regulating the air bag 411; the pressure regulating connector 412 is controlled by an existing servo control system;
wherein, gasbag 411, pressure regulating connecting piece 412 all adopt prior art product, and specific product model field technical staff can select as required.
Example 2
As shown in fig. 5, a method for testing vibration fatigue of an aircraft with low additional stiffness based on the system for testing vibration fatigue of an aircraft with low additional stiffness described in embodiment 1 includes the following steps:
s1 airplane wing clamping structure
Connecting one end of the airplane wing surface structure with the main mounting frame 1 to enable the other end of the airplane wing surface structure to be suspended;
then selecting a position close to a suspended end of the airplane airfoil structure, and clamping the surface of the airplane airfoil structure up and down by adopting a low additional stiffness air bag;
s2, loading, adjusting pressure and carrying out fatigue vibration test
The pressure in the airbag contact portion 40 is increased and reaches the loading pressure by inflating the airbag 411 through the pressure-regulating connector 412; the additional rigidity of the airbag 411 is reduced by the increase of the contact area of the airbag contact portion 40;
by applying vibration to the aircraft airfoil structure, the air bag floating portion 42 floats in the vibration state of the aircraft airfoil structure, and the pressure of the low additional stiffness air bag pair 4 is adjusted in combination with the inflation and deflation of the pressure adjusting connector 412 until the vibration fatigue test is completed.
Example 3
The difference from example 1 is:
as shown in fig. 6, the periphery of the arc-shaped turnover connection ring 403 is provided with an expansion assembly 5;
expansion subassembly 5 is including enclosing the clamping ring 50 of establishing in that the arc turns over a curb 403 peripheral and contact with aircraft airfoil structure, evenly sets up on the clamping ring 50 and run through the arc and turn over an limit portion gas cell 51 that curb 403 and gasbag 411 communicate, and set up clamping ring 50 middle part and the annular air flue 52 that communicates limit portion gas cell 51.
Example 4
The difference from example 1 is:
the first loading device 2 further comprises a movement control assembly for moving the low additional stiffness airbag pair 4;
as shown in fig. 7, the movement control assembly includes side supports 20 disposed on both sides of the aircraft airfoil structure, a movable truss 21 movably disposed on the side supports 20, and a fixed link moving member 22 movably disposed on the movable truss 21 and fixedly connected to the low additional stiffness airbag.
A first sliding groove 200 is horizontally arranged on the side bracket 20;
as shown in fig. 8, the movable truss 21 includes two first rolling wheel sets 210 movably disposed on the first sliding grooves 200, two U-shaped steel rails 211 disposed in parallel between the first rolling wheel sets 210 and located above and below the aircraft airfoil structure, and second sliding grooves 212 disposed at the sides of the U-shaped steel rails 211;
as shown in fig. 9, the fixed link moving member 22 includes a rigid connection cover 220 disposed on the airbag loading portion 41, a sliding connection plate 221 fixed on the rigid connection cover 220 and parallel to the U-shaped steel rail 211, and a second rolling wheel set 222 disposed on the sliding connection plate 221 and connected to the second sliding groove 212.
The U-shaped steel rail 211, the first rolling wheel set 210, and the second rolling wheel set 222 are all made of prior art products, and specific product types can be selected by those skilled in the art as needed.
Example 5
The difference from example 4 is:
as shown in fig. 10, the second loading unit 3 further includes two brackets 30 respectively disposed above and below the aircraft airfoil structure, and two actuators 31 respectively disposed between each bracket 30 and the low additional stiffness airbag.
The aircraft airfoil structure is provided with a vibration table 6.
A telescopic component is arranged between the fixed connection moving piece 22 and the movable truss 21.
Wherein, shaking table 6, telescoping assembly, actuator 31 all adopt prior art product, and specific product model field technical staff can select as required.
Claims (9)
1. A vibration fatigue test system for low additional rigidity of an airplane is characterized by comprising a main mounting frame (1) which is perpendicular to a horizontal ground and used for mounting an airplane airfoil structure, and a loading device used for applying load to the airplane airfoil structure;
one end of the airplane wing surface structure is vertically connected with the main mounting frame (1) through a connecting structure (10), and the other end of the airplane wing surface structure is suspended in the air;
the loading device comprises a first loading device (2) and a second loading device (3) which are arranged on the airplane airfoil structure;
the first loading device (2) and the second loading device (3) comprise low additional rigidity air bag pairs (4); the low additional rigidity air bag pair (4) consists of two low additional rigidity air bags which are respectively and correspondingly arranged on the upper surface and the lower surface of the airplane airfoil structure;
the low additional stiffness airbag includes an airbag contact portion (40) in contact with an aircraft airfoil structure, an airbag loading portion (41) disposed above the airbag contact portion (40), an airbag float portion (42) disposed between the airbag contact portion (40) and the airbag loading portion (41);
the airbag contact part (40) comprises a contact clamping piece (400) which is in contact with the surface of the airplane airfoil structure, and a rigid embedded part (401) which is arranged on the contact clamping piece (400) and is used for enhancing rigidity;
the contact clamping piece (400) comprises a circular contact layer (402), and an arc-shaped turnover connecting ring (403) arranged at the edge part of the circular contact layer (402); the rigid embedded part (401) comprises first embedded strips (404) which are arranged on the circular contact layer (402) and are uniformly distributed in the circumferential direction of the circular contact layer (402), arc-shaped embedded strips (405) which are arranged on the first embedded strips (404) and are positioned in the arc-shaped turnover connecting ring (403), and annular second embedded strips (406) which are uniformly arranged on the first embedded strips (404);
the air bag floating part (42) comprises a corrugated expansion ring (420) with one end hermetically connected with the arc-shaped turnover connecting ring (403), and a rubber sealing cover (421) which is arranged at the other end of the corrugated expansion ring (420) and corresponds to the round contact layer (402);
gasbag loading portion (41) is including setting up the outer outside rigidity safety cover (410) of rubber seal lid (421), evenly set up gasbag (411) on outside rigidity safety cover (410), and set up on gasbag (411) and the intercommunication pressure regulating connecting piece (412) of gasbag (411).
2. The test system for testing the vibration fatigue of the aircraft with low additional rigidity according to claim 1, wherein the external rigid protective cover (410) comprises a protective ring (413) uniformly arranged on the rubber sealing cover (421) and having a center coinciding with the rubber sealing cover (421), an edge protector (414) uniformly arranged on the protective ring (413), and a fixing structure arranged on the protective ring (413) for fixing the air bag (411);
the fixing structure comprises a limiting stop lever (415) which is connected with the protection ring (413) at the lower end and is uniformly arranged around the side face of the air bag (411), a clamping hook (416) which is arranged at the upper end of the limiting stop lever (415) and is in contact with the upper surface of the air bag, and a rigid connecting plate (417) which is arranged on the air bag (411) and is connected with the clamping hook (416).
3. The aircraft low additional stiffness vibration fatigue test system according to claim 1, wherein an extension component (5) is arranged at the periphery of the arc-shaped turnover connecting ring (403);
expansion subassembly (5) are including enclosing establish in the arc turn over a clamping ring (50) that clamping ring (403) are peripheral and contact with aircraft airfoil structure, evenly set up on clamping ring (50) and run through arc turn over a limit portion gas cell (51) that clamping ring (403) and gasbag (411) communicate, and set up and be in clamping ring (50) middle part and the annular air flue (52) of intercommunication limit portion gas cell (51).
4. The aircraft low added stiffness vibration fatigue test system according to claim 1, wherein the first loading device (2) further comprises a movement control assembly for moving the low added stiffness airbag pair (4);
the movement control assembly comprises side supports (20) arranged on two sides of the airplane airfoil structure, a moving truss (21) movably arranged on the side supports (20), and a fixed connection moving piece (22) movably arranged on the moving truss (21) and fixedly connected with the low additional rigidity air bag.
5. The aircraft low additional stiffness vibration fatigue test system according to claim 4, wherein the side bracket (20) is horizontally provided with a first sliding groove (200);
the movable truss (21) comprises two first rolling wheel sets (210) which are respectively and movably arranged on the first sliding grooves (200), two U-shaped steel rails (211) which are arranged between the first rolling wheel sets (210) in parallel and are respectively positioned above and below the wing surface structure of the airplane, and second sliding grooves (212) which are arranged on the side edges of the U-shaped steel rails (211);
the fixedly-connected moving piece (22) comprises a rigid connecting cover (220) arranged on the air bag loading part (41), a sliding connecting plate (221) which is fixed on the rigid connecting cover (220) and is parallel to the U-shaped steel rail (211), and a second rolling wheel group (222) which is arranged on the sliding connecting plate (221) and is connected with the second sliding groove (212).
6. The test system for the vibration fatigue of the airplane with low additional rigidity according to claim 4, wherein a telescopic assembly is arranged between the fixed connection moving piece (22) and the movable truss (21).
7. A vibration fatigue test system for low added stiffness of aircraft according to claim 1, wherein the second loading unit (3) further comprises two brackets (30) respectively disposed above and below the aircraft airfoil structure, and two actuators (31) respectively disposed between each bracket (30) and the low added stiffness bladder.
8. A vibration fatigue test system for low additional stiffness of an aircraft according to claim 1, wherein the aircraft airfoil structure is provided with a vibration table (6).
9. A vibration fatigue test method for low additional stiffness of an airplane, which is based on the vibration fatigue test system for low additional stiffness of the airplane as claimed in any one of claims 1 to 8, and is characterized by comprising the following steps:
s1 airplane wing clamping structure
Connecting one end of the airplane wing surface structure with the main mounting frame (1) to enable the other end of the airplane wing surface structure to be suspended;
then selecting a position close to a suspended end of the airplane airfoil structure, and clamping the surface of the airplane airfoil structure up and down by adopting a low additional stiffness air bag;
s2, loading, adjusting pressure and carrying out fatigue vibration test
Inflating the air bag (411) through the pressure regulating connector (412) to increase the pressure in the air bag contact part (40) and reach the loading pressure; reducing the additional rigidity of the airbag (411) by an increase in the contact area of the airbag contact portion (40);
by applying vibration to the airplane airfoil structure, the air bag floating part (42) floats in the vibration state of the airplane airfoil structure, and meanwhile, the pressure of the low-additional-rigidity air bag pair (4) is adjusted by combining the inflation and deflation of the pressure adjusting connecting piece (412) until the vibration fatigue test is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210732790.7A CN114813001B (en) | 2022-06-27 | 2022-06-27 | Vibration fatigue test system and method for low additional stiffness of airplane |
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