CN112298603A - Landing and falling shock test system for aircraft landing gear - Google Patents
Landing and falling shock test system for aircraft landing gear Download PDFInfo
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- CN112298603A CN112298603A CN202011278266.4A CN202011278266A CN112298603A CN 112298603 A CN112298603 A CN 112298603A CN 202011278266 A CN202011278266 A CN 202011278266A CN 112298603 A CN112298603 A CN 112298603A
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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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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a landing and falling shock testing system for an aircraft landing gear, which comprises a jack, an ejection platform upright post, an ejector, a support, a slide rail, a connecting rail, a horizontal beam, a plurality of vibration measuring instruments and a rising and falling tester, wherein the ejector is fixed on the upper surface of the ejection platform upright post, the jack is positioned below the right side of the ejector, the slide rail is fixed on the upper surface of the support, two ends of the connecting rail are respectively connected with the slide rail and the horizontal beam, the horizontal beam is connected with the jack, the vibration measuring instruments are fixed below the support and embedded in the middle of the horizontal beam, and the rising and falling tester is hung on the horizontal beam. The landing tester can adjust the landing angle, can be matched with the slide rail to realize multi-angle landing, is convenient for generalization of later experiments, and can also find the most suitable landing angle of the landing frame through experiments.
Description
Technical Field
The invention relates to a landing and falling shock test system for an aircraft landing gear, in particular to a landing and falling shock test system for an aircraft landing gear, and belongs to the field of landing and falling shock test application of aircraft landing gears.
Background
With the continuous improvement of the economic level and the beautiful living standard of China, the demand and the comfort degree of people for daily travel are gradually improved, and the safety and the comfort degree of airplane landing are just the problems of people who pay more attention to the safety and the comfort degree. Aircraft landing systems with high safety and comfort are undoubtedly a milestone for technology and even life advancement. However, as the safe landing of the landing gear of the airplane involves a plurality of complex factors, the research on the omnibearing process is a difficult point and is particularly important.
Most of the active test equipment is difficult to support an efficient experimental process. The landing and landing drop test system for the aircraft landing gear can effectively provide more efficient and accurate experimental data, the efficient accuracy of the landing and landing drop test system can improve the difficult points existing in the field at present, a clear thought is provided for future extension experiments, and the landing and landing drop test system has high experimental value, research value and market value.
Disclosure of Invention
The invention aims to solve the problems and provide a landing gear landing and falling shock testing system for an aircraft.
The landing and falling shock testing system comprises a jack, an ejection platform upright post, an ejector, a support post, a slide rail, a connecting rail, a horizontal beam, a plurality of vibration measuring instruments and a landing and falling tester, wherein the ejector is fixed on the upper surface of the ejection platform upright post, the jack is positioned below the right side of the ejector, the slide rail is fixed on the upper surface of the support post, two ends of the connecting rail are respectively connected with the slide rail and the horizontal beam, the horizontal beam is connected with the jack, the vibration measuring instruments are fixed below the support post and embedded in the middle of the horizontal beam, and the landing and falling tester is hung on the horizontal beam.
Preferably, the vibration measuring instruments are uniformly distributed on the horizontal beam at intervals, and the interval distance of the vibration measuring instruments is 1/10-1/8 of the length of the horizontal beam.
Preferably, the ejector comprises an ejection table and an ejection plate, the ejection table is fixed to the bottom of the ejection table, an ejection groove is formed in the surface of the ejection table, a first spring column is fixed in the ejection groove, the ejection plate is fixed to the end face of the first spring column, and the ejector and the ejection plate are arranged on the same side.
Preferably, the tester that rises and falls includes a fixed plate, No. two fixed plates, No. three fixed plates, two track splint, pneumatic cylinder, counter weight, the support and the pulley of rising and falling, two track splint pass through the strengthening rib relatively fixed No. one the fixed plate upper surface, the pneumatic cylinder is fixed No. one the fixed plate with between No. two fixed plates, the counter weight presss from both sides and establishes No. two fixed plates with between No. three fixed plates, the support that rises and falls is fixed No. three fixed plate bottoms, the pulley is fixed support bottom of rising and falling.
Preferably, the number of pneumatic cylinder is 4, fixed plate bottom is connected with angle adjusting plate through the hinge joint, fixed plate surface is equipped with two screw thread round pin and leads to the groove, angle adjusting plate surface is equipped with two screw thread round pin fixed slots, the screw thread round pin leads to the groove and goes up the spiral fastening has the screw thread round pin, the screw thread round pin goes up the scroll cover and is equipped with fastening nut, the screw thread round pin leads to groove bottom and is fixed with No. two spring posts, the screw thread round pin spiral runs through the screw thread round pin leads to the groove and the cover is established in No. two spring posts, the screw thread round pin bottom is fixed on the screw thread round pin fixed slot, fastening nut spiral is fixed the screw.
Preferably, three ribbed slabs are fixed to the bottom of the third fixing plate, a ribbed slab beam is connected between every two adjacent ribbed slabs, the lifting support comprises a main support and a torsion bar, the ribbed slab beam and the torsion bar are respectively fixed with a connecting shaft, the connecting shaft is connected with a coupler, the ribbed slab beam, the ribbed slabs and the top of the main support are fixed together through the coupler, the torsion bar is fixed to the main support through the coupler, and the pulley is fixed to the bottom of the main support.
Preferably, the pulley includes connecting rod, stripper bar, wheel hub and tire, main support bottom with the connecting rod links to each other, the stripper bar is fixed respectively the connecting rod both ends, wheel hub fixes the stripper bar front end, the tire is fixed on the wheel hub, the stripper bar includes outer pole and interior pole, interior pole one end is fixed on the connecting rod, interior pole other end cover is established in the outer pole, the outer pole other end with wheel hub links to each other, be connected with No. three spring posts on the interior pole terminal surface, No. three spring post front ends are fixed in the outer pole.
Preferably, be equipped with two spouts that are symmetrical structure on the outer pole inner wall, be fixed with two sliders that are symmetrical structure on the interior pole outer wall, the slider inlays in the spout.
The invention has the beneficial effects that:
1. the landing drop test system of the aircraft landing gear disclosed by the invention adopts a slide rail structure, and has the characteristics of high adjustability and wide application range;
2. the landing gear is also provided with the hydraulic cylinder, so that the landing angle of the landing gear can be adjusted, multi-angle landing can be realized by matching with the sliding rail, the comprehension of later experiments is facilitated, and the angle which is most suitable for landing of the landing gear can be found through the experiments;
3. the invention has comprehensive design consideration factors and high adjustability, lays a foundation for subsequent experiments and has the characteristic of high cost performance;
4. under the condition of developed aviation industry in the current society, the invention can carry out powerful test and improvement on the safety performance and the comfort performance of the aircraft landing, and has very high experimental value, research value and market value.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the position of the jack and the column of the ejection table of the present invention;
FIG. 3 is a schematic view of the ejector and the slide rail according to the present invention;
FIG. 4 is a schematic view of the connection structure of the vibration measuring device and the landing measuring device of the present invention with the horizontal beam;
FIG. 5 is a schematic view of the landing tester of the present invention;
FIG. 6 is a schematic view of the ejector of the present invention;
FIG. 7 is a schematic view of a connection structure of a first fixing plate and an angle adjustment plate according to the present invention;
fig. 8 is a schematic view of the pulley structure of the present invention.
In the figure: 1. the device comprises a jack, 2, an ejection platform upright post, 3, an ejector, 4, a support post, 5, a sliding rail, 6, a connecting rail, 7, a horizontal beam, 8, a vibration measuring instrument, 9, a rise and fall tester, 10, a first fixing plate, 11, a rail clamping plate, 12, a hydraulic cylinder, 13, a counterweight, 14, a torsion bar, 15, a pulley, 16, an ejection platform, 17, an ejection groove, 18, a first spring column, 19, an ejection plate, 20, a second fixing plate, 21, a third fixing plate, 22, an angle adjusting plate, 23, a reinforcing rib, 24, a threaded pin through groove, 25, a threaded pin fixing groove, 26, a threaded pin, 27, a fastening nut, 28, a second spring column, 29, a rib plate, 30, a limiting groove, 31, a rise and fall support, 32, a connecting shaft, 33, a rib plate cross beam, 34, a coupler, 35, a connecting rod, 36, a hub, 37, an extrusion rod, 38, a tire, 39, an inner, Outer pole, 41, No. three spring posts, 42, slider, 43, spout.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner" and "outer" indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring now to figures 1-8 of the drawings,
the utility model provides an aircraft undercarriage landing drop test system, includes ground jack 1, launches platform stand 2, catapult 3, pillar 4, slide rail 5, connecting track 6, horizontal beam 7, a plurality of vibration measuring apparatu 8 and rise and fall tester 9, catapult 3 fixes launch 2 upper surfaces of platform stand, ground jack 1 is located 3 right side below of catapult, slide rail 5 is fixed 4 upper surfaces of pillar, connecting track 6 both ends are connected respectively slide rail 5 with horizontal beam 7, horizontal beam 7 with ground jack 1 links to each other, vibration measuring apparatu 8 is fixed 4 below of pillar is inlayed in the middle of horizontal beam 7, rise and fall tester 9 is hung on horizontal beam 7.
Different weights assigned to the take-off and landing tester 9 when landing different models of aircraft can be simulated by changing the weight of the counterweight 13.
The vibration measuring instruments 8 are uniformly distributed on the horizontal beam 7 at intervals, and the interval distance of the vibration measuring instruments 8 is 1/10-1/8 of the length of the horizontal beam 7.
The ejector 3 comprises an ejection table 16 and an ejection plate 19, the ejection table upright 2 is fixed at the bottom of the ejection table 16, an ejection groove 17 is formed in the surface of the ejection table 16, a first spring column 18 is fixed in the ejection groove 17, the ejection plate 19 is fixed on the end face of the first spring column 18, and the ejector 3 and the ejection plate 19 are arranged on the same side.
The catapult 3 can accurately catapult the rise-fall tester 9, give the rise-fall tester 9 initial speed and acceleration, reach the highest point of the slide rail 5.
The ejector 3 is designed to reduce the maximum height of the support 4, reduce the height of the support 4 and meet the speed required by the rise and fall tester 9 during testing, save materials and reduce cost.
The tester 9 that rises and falls includes fixed plate 10, No. two fixed plates 20, No. three fixed plates 21, two track splint 11, pneumatic cylinder 12, counter weight 13, the support 31 and the pulley 15 rise and fall, two track splint 11 pass through strengthening rib 23 relatively fixed No. 10 upper surfaces of fixed plate, pneumatic cylinder 12 is fixed No. 10 fixed plate with between No. two fixed plates 20, counter weight 13 presss from both sides and establishes No. two fixed plates 20 with between No. three fixed plates 21, the support 31 that rises and falls is fixed No. three fixed plates 21 bottoms, the pulley 15 is fixed the support 31 bottom that rises and falls.
The number of pneumatic cylinder 12 is 4, No. 10 bottoms of fixed plate are connected with angle adjusting plate 22 through hinged joint, No. 10 surfaces of fixed plate are equipped with two screw thread round pin and lead to groove 24, angle adjusting plate 22 surfaces are equipped with two screw thread round pin fixed slots 25, screw thread round pin leads to groove 24 and goes up the spiral fastening has screw thread round pin 26, the swivel nut is equipped with fastening nut 27 on the screw thread round pin 26, screw thread round pin leads to groove 24 bottoms and is fixed with No. two spring posts 28, screw thread round pin 26 spiral runs through screw thread round pin leads to groove 24 and cover and establishes in No. two spring posts 28, screw thread round pin 26 bottom is fixed on the screw thread round pin fixed slot 25, fastening nut 27 spiral is fixed screw thread round pin leads to groove 24 surfaces.
By adjusting the distance between the angle adjusting plate 22 and the first fixing plate 10, the landing of the aircraft landing gear at multiple angles can be simulated.
Three floor 29 is fixed with to No. three fixed plate 21 bottom, is connected with floor crossbeam 33 between two adjacent floor 29, the support 31 that rises and falls includes main support 30 and torsion and does 14, floor crossbeam 33 with be fixed with even axle 32 on the torsion is done 14 respectively, be connected with shaft coupling 34 on even axle 32, floor crossbeam 33, floor 29 with main support 30 top is together fixed through shaft coupling 34, torsion is done 14 and is fixed through shaft coupling 34 on the main support 30, pulley 15 is fixed main support 30 bottom.
Pulley 15 includes connecting rod 35, squeeze bar 37, wheel hub 36 and tire 38, main support 30 bottom with connecting rod 35 links to each other, squeeze bar 37 is fixed respectively connecting rod 35 both ends, wheel hub 36 is fixed squeeze bar 37 front end, tire 38 is fixed on wheel hub 36, squeeze bar 37 includes outer pole 40 and interior pole 39, interior pole 39 one end is fixed on connecting rod 35, interior pole 39 other end cover is established in outer pole 40, the outer pole 40 other end with wheel hub 36 links to each other, be connected with No. three spring post 41 on the interior pole 39 terminal surface, No. three spring post 41 front ends are fixed in outer pole 40.
The inner wall of the outer rod 40 is provided with two sliding grooves 43 which are of symmetrical structures, the outer wall of the inner rod 39 is fixed with two sliding blocks 42 which are of symmetrical structures, and the sliding blocks 42 are embedded in the sliding grooves 43.
The pulley is fixed on the slide rail 5 by the elasticity of the third spring column 41 in the extrusion rod 37.
Examples
When testing, an operator should take out the corresponding counterweight 13, place the counterweight 13 of a certain specification on the third fixing plate 21 to fix it, adjust the distance between the angle adjusting plate 22 and the first fixing plate 10 to adjust different landing angles when the airplane lands, then fix the landing tester 9 on the jack 1, lift the landing tester 9 on the ejection table 16 by using the jack 1, ensure that the pulley 15 on the landing tester 9 is embedded in the slide rail 5 and can slide relative to the slide rail 5, adjust the elasticity and direction of the first spring column 18, the ejection plate 19 plays an ejection pushing role for the landing tester 9, make the landing tester 9 obtain different required initial speeds by changing the deformation of the first spring column 18, the pulley 15 slides on the slide rail 5 by the acceleration of the ejector 3 and reaches the highest point of the slide rail 5, then the landing tester 9 slides downwards at the highest point rapidly by gravity, the speed requirement and the angle requirement of the simulated aircraft during landing are met.
When the landing tester 9 accelerates to pass through the connecting track 6 between the slide rail 5 and the horizontal beam 7, the landing tester 9 slides on the horizontal beam 7 at the moment, and the horizontal traveling state is always kept, namely the landing tester 9 is in contact with the ground, the pulley 15 starts to bear the falling shock force, the falling shock fluctuation is transmitted to the horizontal beam 7 through the conduction of a stress structure, each small section of track on the horizontal beam 7 is provided with the vibration measuring instrument 8, and the vibration measuring instruments 8 can measure the fluctuation size on the horizontal beam 7 through sensors, so that the falling shock fluctuation condition of airplanes of different specifications at each moment during multi-angle landing is measured.
After waiting to rise and fall tester 9 to stop to slide, give the horizontal pulling force of tester 9 again that rises and falls, will rise and fall tester 9 toward initial position pulling, at connection track 6 department, remove the connection between slide rail 5 and the horizontal beam 7, continue to follow horizontal beam 7 and stimulate tester 9 to jack 1 department that rises and falls backward, carry out the experiment next time, realize many experiments, multi-angle, multi-speed simulation, conveniently arrange experimental data in order, carry out accurate effectual data analysis.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (8)
1. The utility model provides an aircraft undercarriage landing drop test system which characterized in that: including ground jack (1), ejection platform stand (2), catapult (3), pillar (4), slide rail (5), connecting track (6), horizontal beam (7), a plurality of vibration measuring instrument (8) and tester (9) that rises and falls, catapult (3) are fixed ejection platform stand (2) upper surface, ground jack (1) is located catapult (3) right side below, slide rail (5) are fixed pillar (4) upper surface, connecting track (6) both ends are connected respectively slide rail (5) with horizontal beam (7), horizontal beam (7) with ground jack (1) links to each other, vibration measuring instrument (8) are fixed pillar (4) below is embedded in the middle of horizontal beam (7), tester (9) that rises and falls hang on horizontal beam (7).
2. An aircraft landing gear drop test system according to claim 1, wherein: the vibration measuring instruments (8) are uniformly distributed on the horizontal beam (7) at intervals, and the interval distance of the vibration measuring instruments (8) is 1/10-1/8 of the length of the horizontal beam (7).
3. An aircraft landing gear drop test system according to claim 1, wherein: the ejector (3) comprises an ejection table (16) and an ejection plate (19), the ejection table upright post (2) is fixed to the bottom of the ejection table (16), an ejection groove (17) is formed in the surface of the ejection table (16), a first spring post (18) is fixed in the ejection groove (17), the ejection plate (19) is fixed to the end face of the first spring post (18), and the ejector (3) and the ejection plate (19) are arranged on the same side.
4. An aircraft landing gear drop test system according to claim 1, wherein: the utility model discloses a take-up and landing tester (9) is including a fixed plate (10), No. two fixed plates (20), No. three fixed plates (21), two track splint (11), pneumatic cylinder (12), counter weight (13), support (31) and pulley (15) rise and fall, two track splint (11) are fixed relatively through strengthening rib (23) No. one fixed plate (10) upper surface, pneumatic cylinder (12) are fixed No. one fixed plate (10) with between No. two fixed plates (20), counter weight (13) press from both sides and are established No. two fixed plates (20) with between No. three fixed plates (21), support (31) that rises and falls are fixed No. three fixed plate (21) bottom, pulley (15) are fixed support (31) bottom rises and falls.
5. An aircraft landing gear drop test system according to claim 4, wherein: the number of pneumatic cylinder (12) is 4, fixed plate (10) bottom is connected with angle adjusting plate (22) through hinged joint, fixed plate (10) surface is equipped with two screw thread round pin and leads to groove (24), angle adjusting plate (22) surface is equipped with two screw thread round pin fixed slots (25), the screw thread round pin leads to groove (24) and goes up the spiral and is fixed with screw thread round pin (26), the screw thread cover is equipped with fastening nut (27) on screw thread round pin (26), the screw thread round pin leads to groove (24) bottom and is fixed with No. two spring posts (28), screw thread round pin (26) spiral runs through screw thread round pin leads to groove (24) and cover and establishes in No. two spring posts (28), screw thread round pin (26) bottom is fixed on screw thread round pin fixed slots (25), fastening nut (27) spiral is fixed the screw thread round pin leads to groove (24) surface.
6. An aircraft landing gear drop test system according to claim 4, wherein: no. three fixed plate (21) bottom is fixed with three floor (29), is connected with floor crossbeam (33) between two adjacent floor (29), support (31) rise and fall includes that main support (30) and torsion do (14), floor crossbeam (33) with be fixed with even axle (32) on torsion do (14) respectively, be connected with shaft coupling (34) on even axle (32), floor crossbeam (33), floor (29) and shaft coupling (34) are fixed together through shaft coupling (34) at main support (30) top, torsion do (14) fix through shaft coupling (34) on main support (30), pulley (15) are fixed main support (30) bottom.
7. An aircraft landing gear drop test system according to claim 6, wherein: pulley (15) include connecting rod (35), extrusion stem (37), wheel hub (36) and tire (38), main support (30) bottom with connecting rod (35) link to each other, extrusion stem (37) are fixed respectively connecting rod (35) both ends, wheel hub (36) are fixed extrusion stem (37) front end, tire (38) are fixed on wheel hub (36), extrusion stem (37) are including outer pole (40) and interior pole (39), interior pole (39) one end is fixed on connecting rod (35), interior pole (39) other end cover is established in outer pole (40), outer pole (40) other end with wheel hub (36) link to each other, be connected with No. three spring post (41) on interior pole (39) terminal surface, No. three spring post (41) front end is fixed in outer pole (40).
8. An aircraft landing gear drop test system according to claim 7, wherein: be equipped with two spout (43) that are symmetrical structure on outer pole (40) inner wall, be fixed with two slider (42) that are symmetrical structure on interior pole (39) outer wall, slider (42) inlay in spout (43).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011278266.4A CN112298603A (en) | 2020-11-16 | 2020-11-16 | Landing and falling shock test system for aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011278266.4A CN112298603A (en) | 2020-11-16 | 2020-11-16 | Landing and falling shock test system for aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112298603A true CN112298603A (en) | 2021-02-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011278266.4A Withdrawn CN112298603A (en) | 2020-11-16 | 2020-11-16 | Landing and falling shock test system for aircraft landing gear |
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| CN (1) | CN112298603A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
-
2020
- 2020-11-16 CN CN202011278266.4A patent/CN112298603A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
| CN114778050B (en) * | 2022-06-27 | 2022-09-02 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
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Application publication date: 20210202 |
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