CN117048845B - Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method - Google Patents
Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method Download PDFInfo
- Publication number
- CN117048845B CN117048845B CN202311308636.8A CN202311308636A CN117048845B CN 117048845 B CN117048845 B CN 117048845B CN 202311308636 A CN202311308636 A CN 202311308636A CN 117048845 B CN117048845 B CN 117048845B
- Authority
- CN
- China
- Prior art keywords
- sliding
- landing gear
- obstacle
- mounting
- impact test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000009863 impact test Methods 0.000 title claims abstract description 46
- 238000010998 test method Methods 0.000 title abstract description 6
- 238000012360 testing method Methods 0.000 claims abstract description 24
- 238000000034 method Methods 0.000 claims abstract description 6
- 238000009434 installation Methods 0.000 claims description 91
- 230000004888 barrier function Effects 0.000 claims description 26
- 238000004088 simulation Methods 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 7
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 230000000903 blocking effect Effects 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 239000010687 lubricating oil Substances 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 3
- 230000003116 impacting effect Effects 0.000 claims description 2
- 230000008878 coupling Effects 0.000 claims 2
- 238000010168 coupling process Methods 0.000 claims 2
- 238000005859 coupling reaction Methods 0.000 claims 2
- 238000013461 design Methods 0.000 abstract description 2
- 238000003780 insertion Methods 0.000 description 4
- 230000037431 insertion Effects 0.000 description 4
- 238000010304 firing Methods 0.000 description 3
- 230000013011 mating Effects 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- G01M7/08—Shock-testing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention provides a carrier-based aircraft landing gear running obstacle-surmounting impact test device and a test method, and belongs to the technical field of aircraft tests. The test equipment comprises a mounting chassis, a hanging basket assembly, a landing gear and an obstacle surmounting impact test assembly, wherein the upper end of the mounting chassis is provided with a mounting bracket, the hanging basket assembly is arranged on the mounting bracket, the landing gear is connected with the hanging basket assembly, and the obstacle surmounting impact test assembly is arranged on the bottom surface of the mounting chassis; the landing gear obstacle crossing process of the carrier-based aircraft is simulated in a laboratory, the landing gear obstacle crossing performance under different sliding speeds can be obtained by adjusting the inflation pressure of the air cannon launching element, the landing gear obstacle crossing performance under different heights can be obtained by adjusting the height of the obstacle module through the miniature hydraulic cylinder, more parameter characteristics are provided for an obstacle crossing impact test, the accuracy of a test result is improved, and corresponding basis is provided for evaluating and judging the impact of the carrier-based aircraft landing gear performance design, service life estimation and sliding obstacle crossing load on the carrier-based aircraft body structure.
Description
Technical Field
The invention belongs to the technical field of aircraft tests, and particularly relates to a ship-based aircraft landing gear running obstacle-surmounting impact test device and a test method.
Background
The aircraft can cross obstacles in the sliding process, a transient impact force can be generated to act on the aircraft body and the landing gear, particularly when the sliding speed of the carrier-based aircraft is higher, the carrier-based aircraft is more complex, the obstacle crossing impact load can be overlapped on the landing load which is already high, so that the strength of the aircraft body and the landing gear is more severely checked, the dynamic process and the impact load are required to be calculated and predicted, and the ground obstacle crossing test is used for verifying whether the landing gear structure, the buffer and the tire meet the obstacle crossing impact performance requirement.
The aircraft carrier deck barriers can be divided into a lamp cover, a camera cover and a blocking rope, wherein the obstacle crossing modes of the lamp cover and the camera cover are the same, so that the test verification scheme of the carrier-based aircraft landing gear crossing the lamp cover and the camera cover and crossing the blocking rope is mainly researched. Therefore, in the development process of the carrier-based aircraft, the landing gear sliding obstacle surmounting capability of the carrier-based aircraft needs to be simulated in a laboratory environment, so that the pilot flight test risk is reduced.
The existing ship-based aircraft laboratory simulated landing gear sliding obstacle surmounting test equipment does not have the test functions of adjusting sliding speed and crossing obstacles with different lifting heights, so that the accuracy of test results is greatly reduced, and evaluation and judgment results are affected.
Disclosure of Invention
Aiming at the problems, the invention provides a carrier-based aircraft landing gear running obstacle-surmounting impact test device and a test method.
The technical scheme of the invention is as follows: the landing gear running obstacle crossing impact test equipment for the carrier-based aircraft comprises a mounting chassis, a hanging basket assembly, a landing gear and an obstacle crossing impact test assembly, wherein the upper end of the mounting chassis is provided with a mounting bracket, the hanging basket assembly is arranged on the mounting bracket, the landing gear is connected with the hanging basket assembly, and the obstacle crossing impact test assembly is arranged on the mounting chassis;
the mounting chassis is provided with a sliding groove along the width direction, the bottom end of the vertical section of the mounting bracket is in sliding connection with the sliding groove, the lower side of the horizontal section of the mounting bracket is provided with a guide frame, the hanging basket assembly can slide up and down along the inner wall of the guide frame through external driving equipment, and the landing gear is connected with the bottom end of the hanging basket assembly;
the obstacle crossing impact test assembly comprises an emission installation main body arranged on the installation chassis, an air cannon emission element arranged on the emission installation main body and far away from one side of the landing gear, a high-speed sliding table arranged on the emission installation main body and near one side of the air cannon emission element, and an obstacle simulation element arranged on the high-speed sliding table;
a through sliding opening is formed in the launching installation main body and close to one side of the landing gear, one end of the high-speed sliding table passes through the through sliding opening and extends into the launching installation main body, the other end of the high-speed sliding table is positioned outside the launching installation main body, a sealing sliding block is arranged at one end of the high-speed sliding table positioned in the launching installation main body, the sealing sliding block can slide towards one side close to the landing gear along the launching installation main body through the driving of the air gun launching element, and an installation notch is formed in the high-speed sliding table;
the obstacle simulation element comprises a horizontal installation plate, a miniature hydraulic cylinder, a plurality of auxiliary telescopic rods and an obstacle module, wherein the horizontal installation plate is arranged on the left side and the right side, the first sliding strip is arranged in the installation notch, the miniature hydraulic cylinder is arranged at the center of the bottom of the horizontal installation plate, the auxiliary telescopic rods are arranged at the bottom of the horizontal installation plate and are uniformly distributed along the circumference of the horizontal installation plate, the obstacle module is arranged on the upper portion of the horizontal installation plate, the vertical sliding grooves are formed in the left side and the right side of the installation notch, and the first sliding strip is in corresponding sliding connection with the vertical sliding grooves.
Further, a plurality of sliding clamping grooves are formed in the mounting chassis along the horizontal direction, the sliding clamping grooves are distributed in parallel along the width direction of the mounting chassis, second sliding strips which are in one-to-one correspondence with the sliding clamping grooves and are in sliding connection with the sliding clamping grooves are arranged at the bottom end of the high-speed sliding table, and lubricating oil is filled between the sliding clamping grooves and the second sliding strips.
Description: when the high-speed sliding table is pushed to sideslip close to the landing gear by high-pressure air emitted by the air cannon emission element, the bottom end of the high-speed sliding table can be supported and limited by the mutual sliding between the bottom end of the high-speed sliding table and the sliding clamping groove on the installation chassis, so that the mechanical property of the high-speed sliding table is improved, and the service life of the high-speed sliding table is prolonged.
Further, the installation notch has a plurality ofly, and a plurality of installation notches distribute along the width direction of installation chassis, and all are equipped with horizontal installation dish in every installation notch, and the obstacle module that corresponds on every horizontal installation dish is used for simulating various obstacles on the aircraft carrier deck respectively, and the obstacle module periphery is equipped with the connection chimb, be equipped with the clamp frame through a plurality of fastening bolt connection and junction between connection chimb and the horizontal installation dish, the shape of clamp frame matches with the outward flange shape of obstacle module.
Description: through setting up a plurality of installation recesses, conveniently install different grade type barrier in each installation recess, for example lamp lid, camera lid and blocking rope etc. improve the authenticity of test and the accuracy of test result, through setting up at every barrier module periphery and connect the chimb for barrier module installation's is more firm, prolongs its life.
Further, the left and right sides of the vertical sliding groove are provided with strip-shaped metal plates, the left and right sides of the first sliding bar are provided with connecting grooves, and each connecting groove is internally and movably connected with an electromagnetic chuck, and the electromagnetic chuck is flush with the side wall of the first sliding bar.
Description: when the lifting height of the obstacle module needs to be adjusted, the corresponding obstacle module on the horizontal installation plate is driven to lift through the micro hydraulic cylinder, meanwhile, the horizontal installation plate vertically slides in the corresponding vertical sliding groove through the first sliding strips on the left side and the right side, after the micro hydraulic cylinder is closed, the horizontal installation plate stops sliding, at the moment, the electromagnetic chuck is electrified, the first sliding strips are adsorbed and fixed with the strip-shaped metal plate under the action of electromagnetic attraction, so that the installation of the horizontal installation plate is more stable and compact, the mechanical property of the obstacle module is improved, the service life of the obstacle module is greatly prolonged, and the operation reliability of the device is improved.
Further, the hanging basket assembly comprises a hanging basket frame body, wherein the left side and the right side are in sliding connection with the side wall of the guide frame, the upper end of the hanging basket frame body is connected with external driving equipment through a steel wire rope, the balancing weight is placed in the hanging basket frame body, the landing gear is connected with the bottom end of the hanging basket frame body, the hanging basket frame body is internally provided with a stable clamping assembly, the stable clamping assembly comprises a horizontal sliding groove arranged at the bottom end inside the hanging basket frame body, vertical installation strips symmetrically distributed at the left side and the right side inside the hanging basket frame body, two stable clamping blocks which are arranged between the vertical installation strips and are in sliding connection with the bottom end of the vertical installation strips, and an electric telescopic rod arranged between the vertical installation strips and the corresponding stable clamping blocks.
Description: when the height of the landing gear needs to be adjusted, external driving equipment is opened, the hanging basket frame body slides up and down along the inner wall of the guide frame and is free of clamping through the length of the lifting or releasing steel wire rope, the landing gear moves up and down synchronously, the total mass of the hanging basket frame body, the landing gear and the balancing weight is adjusted through balancing weights of different weights or different amounts, the equivalent mass required by the landing gear test is met, when the total mass of the hanging basket frame body, the landing gear and the balancing weight needs to be adjusted, the balancing weight is placed in the hanging basket frame body and between two stable clamping blocks, then, an electric telescopic rod is opened, the two stable clamping blocks which are distributed relatively are close to each other and are used for fixing and clamping the balancing weight, and when the obstacle crossing impact test can be avoided, the balancing weight swings and impacts at will, the hanging basket frame body is damaged, and the normal running of the test is affected.
Furthermore, each stable clamping block is formed by arranging a plurality of sub clamping blocks from top to bottom in sequence, each sub clamping block is provided with an inverted T-shaped splicing chute at the upper end, each sub clamping block is provided with an inverted T-shaped splicing slide bar at the lower end, two adjacent sub clamping blocks are connected through the corresponding splicing chute and the inverted T-shaped splicing slide bar, and the lower end of the sub clamping block at the bottommost end is of a planar structure and is in sliding connection with the horizontal sliding groove.
Description: when adjusting hanging basket frame main part, undercarriage and balancing weight whole total mass according to experimental demand, arrange the stack in proper order in hanging basket frame main part from bottom to top with several balancing weight and be located between two stable grip blocks, when the height of stable grip block is adjusted according to the stack height of balancing weight to the needs, can place a sub grip block again in sub grip block upper end of bottommost, make the slip of pegging graft that falls T type of newly placed sub grip block bottom and the grafting spout sliding connection that the sub grip block of bottom corresponds, repeat above-mentioned step of placing, until the balancing weight quantity of placing reaches the requirement, then, start each electric telescopic handle, make two electric telescopic handle of relative distribution be close to each other, and each sub grip block of relative distribution is also synchronous be close to each other, thereby carry out the centre gripping fixed to the balancing weight, can satisfy the purpose of adjusting hanging basket frame main part, undercarriage and balancing weight whole total mass, improve equipment's suitability.
Still further, two the opposite sides of vertical installation strip all are equipped with a plurality of from top to bottom evenly distributed's first connecting socket, a plurality of first connecting socket and a plurality of sub-grip block one-to-one, and be equipped with the second on every sub-grip block lateral wall with the lateral wall of the opposite side of first connecting socket and connect the socket, electric telescopic handle has a plurality ofly, and a plurality of electric telescopic handle locate in proper order between the first connecting socket and the second connecting socket of relative distribution.
Description: along with the increase of the stacking height of each sub-clamping block, in order to improve the clamping force, through setting up the electric telescopic rod corresponding to each sub-clamping block on the vertical installation strip, each sub-clamping block can be supported and pushed, and the integral mechanical strength and the clamping force of the stable clamping block are improved.
Furthermore, an anti-slip pad is arranged on the inner wall of the plug-in sliding groove.
Description: through set up the slipmat at the inner wall of grafting spout, increase the frictional force between reverse T type grafting draw runner and the grafting spout, it is more firm to make the connection between two adjacent sub-grip blocks, has further improved holistic mechanical strength and the clamping force of stable grip block.
The invention also discloses a landing gear running obstacle crossing impact test method of the carrier-based aircraft, which is based on the landing gear running obstacle crossing impact test equipment of the carrier-based aircraft, and comprises the following steps:
s1, release of landing gear
Opening external driving equipment, enabling the hanging basket assembly to slide downwards along the inner wall of the guide frame through releasing the length of the steel wire rope, and enabling the landing gear to synchronously move downwards without clamping;
s2, preparation before obstacle surmounting impact test
Checking the buffer and the tire filling pressure of the landing gear, after the buffer and the tire filling pressure of the landing gear meet the test requirements, charging the inside of the emission installation main body through the air gun emission element, setting a charging target value according to the current test speed requirements, and closing the air gun emission element after the air pressure in the emission installation main body reaches the air pressure value corresponding to the required speed;
s3, adjusting the height of the obstacle module
Pushing the mounting bracket to slide in the sliding groove to adjust the position of the landing gear, driving the horizontal mounting plate and the barrier module to synchronously move upwards through the micro hydraulic cylinder, simultaneously synchronously extending each auxiliary telescopic rod and supporting the horizontal mounting plate and the barrier module, and synchronously sliding the first sliding bar in the vertical sliding groove until the barrier module moves out of the mounting notch;
s4, performing obstacle surmounting impact test
Clicking a launching button of an air cannon launching element to enable high-pressure air in a launching installation main body to push a high-speed sliding table to slide towards one side close to the landing gear on an installation chassis, enabling an obstacle module to slide synchronously, and impacting a landing gear wheel at a preset speed, so that landing gear obstacle crossing performance data are obtained, and obstacle crossing impact tests are completed.
Compared with the prior art, the invention has the beneficial effects that:
according to the landing gear sliding obstacle crossing impact test equipment for the carrier-based aircraft, the sliding obstacle crossing process of the carrier-based aircraft is simulated in a laboratory, a verification way is provided for checking the structural strength and rigidity of the landing gear of the carrier-based aircraft and verifying the landing gear sliding obstacle crossing performance, and the technical risk of real aircraft landing adaptation test flight verification is reduced; the landing gear obstacle crossing performance under different sliding speeds can be obtained by adjusting the inflation pressure of the air cannon launching element, the landing gear obstacle crossing performance under different heights can be obtained by adjusting the height of the obstacle module through the miniature hydraulic cylinder, more parameter characteristics are provided for obstacle crossing impact tests, the accuracy of test results is improved, and corresponding basis is provided for evaluating and judging the impact of the carrier aircraft landing gear performance design, life prediction and sliding obstacle crossing load on the carrier aircraft body structure.
Drawings
FIG. 1 is a flow chart of a test method of the present invention;
FIG. 2 is a schematic view of the overall structure of the test apparatus of the present invention;
FIG. 3 is a schematic view of the installation of the barrier simulation element of the present invention within a mounting recess;
FIG. 4 is a schematic view of the structure of the barrier module of the present invention;
FIG. 5 is a schematic view of a portion of the connection of the high speed slipway of the present invention to the mounting chassis;
FIG. 6 is a top view of the high speed slipway of the present invention;
FIG. 7 is a schematic view of a connection structure of a first slider and a vertical slider groove according to the present invention;
FIG. 8 is a schematic structural view of a stabilization clip assembly of the present invention;
the device comprises a 1-mounting chassis, a 10-mounting bracket, a 11-sliding groove, a 12-guiding bracket, a 13-sliding clamping groove, a 2-hanging basket assembly, a 20-hanging basket frame body, a 21-balancing weight, a 3-landing gear, a 4-obstacle crossing impact test assembly, a 40-emission mounting body, a 400-through sliding opening, a 41-air cannon emission element, a 42-high-speed sliding table, a 420-mounting notch, a 421-vertical sliding groove, a 422-second sliding bar, a 423-strip-shaped metal plate, a 43-obstacle simulation element, 4300-first sliding bar, 4301-connecting grooves, 4302-electromagnetic suction cups, 430-horizontal mounting plates, 431-miniature hydraulic cylinders, 432-auxiliary telescopic rods, 433-obstacle modules, 434-connecting convex edges, 435-compacting frames, 44-sealing sliding blocks, 5-stable clamping assemblies, 50-horizontal sliding grooves, 51-vertical mounting bars, 510-first connecting sockets, 511-second connecting sockets, 52-stable clamping blocks, 521-sub-clamping blocks, 522-plug-in sliding grooves, 523-inverted T-shaped electric sliding bars and 53-plug-in telescopic rods.
Detailed Description
The present invention will be described in detail with reference to examples.
Example 1: as shown in fig. 2, the landing gear running obstacle crossing impact test equipment of the carrier-based aircraft comprises a mounting chassis 1, a hanging basket assembly 2, a landing gear 3 and an obstacle crossing impact test assembly 4, wherein the upper end of the mounting chassis 1 is provided with a mounting bracket 10, the hanging basket assembly 2 is arranged on the mounting bracket 10, the landing gear 3 is connected with the hanging basket assembly 2, and the obstacle crossing impact test assembly 4 is arranged on the bottom surface of the mounting chassis 1;
the installation chassis 1 is provided with a sliding groove 11 along the width direction, the bottom end of the vertical section of the installation bracket 10 is in sliding connection with the sliding groove 11, the lower side of the horizontal section of the installation bracket 10 is provided with a guide frame 12, the hanging basket assembly 2 can slide up and down along the inner wall of the guide frame 12 through external driving equipment, and the landing gear 3 is connected with the bottom end of the hanging basket assembly 2;
the obstacle surmounting impact test assembly 4 comprises an emission installation main body 40 arranged on the installation chassis 1, an air cannon emission element 41 arranged on the emission installation main body 40 and at one side far away from the landing gear 3, a high-speed sliding table 42 arranged on the emission installation main body 40 and at one side close to the air cannon emission element 41, and an obstacle simulation element 43 arranged on the high-speed sliding table 42;
a through sliding opening 400 is formed in the launching installation main body 40 and at one side close to the landing gear 3, one end of the high-speed sliding table 42 extends into the launching installation main body 40 through the through sliding opening 400, the other end of the high-speed sliding table 42 is positioned outside the launching installation main body 40, a sealing sliding block 44 is arranged at one end of the high-speed sliding table 42 positioned in the launching installation main body 40, the sealing sliding block 44 can slide towards one side close to the landing gear 3 along the launching installation main body 40 under the driving of the air gun launching element 41, and an installation notch 420 is formed in the high-speed sliding table 42;
as shown in fig. 3, the obstacle simulation element 43 includes a horizontal mounting plate 430 having first sliding strips 4300 on both left and right sides and located in the mounting recess 420, a micro hydraulic cylinder 431 disposed at the bottom center of the horizontal mounting plate 430, 4 auxiliary telescopic rods 432 disposed at the bottom of the horizontal mounting plate 430 and uniformly distributed along the circumferential direction of the horizontal mounting plate 430, and an obstacle module 433 disposed at the upper portion of the horizontal mounting plate 430, wherein vertical sliding grooves 421 are disposed on both left and right sides of the mounting recess 420, and the first sliding strips 4300 are correspondingly slidably connected with the vertical sliding grooves 421;
as shown in fig. 4 and 6, 3 mounting recesses 420 are provided, 3 mounting recesses 420 are distributed along the width direction of the mounting chassis 1, each mounting recess 420 is internally provided with a horizontal mounting plate 430, corresponding barrier modules 433 on each horizontal mounting plate 430 are respectively used for simulating various barriers on the deck of the aircraft carrier, the periphery of each barrier module 433 is provided with a connecting convex edge 434, the connecting convex edges 434 are connected with the horizontal mounting plates 430 through 4 fastening bolts, a pressing frame 435 is arranged at the connecting part, and the shape of the pressing frame 435 is matched with the shape of the outer edge of each barrier module 433; wherein, the barriers installed in the 3 installation notches 420 are a lamp cover, a camera cover and a blocking rope, respectively;
as shown in fig. 7, the left and right sides of the vertical sliding groove 421 are respectively provided with a strip-shaped metal plate 423, the left and right sides of the first sliding bar 4300 are respectively provided with a connecting groove 4301, each connecting groove 4301 is movably connected with an electromagnetic chuck 4302, and the electromagnetic chuck 4302 is flush with the side wall of the first sliding bar 4300;
as shown in fig. 8, the basket assembly 2 comprises a basket body 20 with left and right sides slidably connected with the side walls of the guide frame 12 and upper ends slidably connected with external driving equipment through steel wires, and a balancing weight 21 placed in the basket body 20, the landing gear 3 is connected with the bottom end of the basket body 20, a stable clamping assembly 5 is arranged in the basket body 20, the stable clamping assembly 5 comprises a horizontal sliding groove 50 arranged at the bottom end inside the basket body 20, vertical mounting bars 51 symmetrically distributed at the left and right sides inside the basket body 20, two stable clamping blocks 52 arranged between the two vertical mounting bars 51 and with the bottom ends slidably connected with the horizontal sliding groove 50, and an electric telescopic rod 53 arranged between the vertical mounting bars 51 and the corresponding stable clamping blocks 52;
the air cannon launching element 41 adopts the existing air cannon or air compressor, and the micro hydraulic cylinder 431, the electromagnetic chuck 4302, the electric telescopic rod 53 and the stable clamping block 52 all adopt the prior art.
Example 2: the embodiment discloses a carrier-based aircraft landing gear running obstacle-crossing impact test method, which is based on the carrier-based aircraft landing gear running obstacle-crossing impact test equipment of embodiment 1, and as shown in fig. 1, and comprises the following steps:
s1 release of landing gear 3
Opening external driving equipment, enabling the basket frame main body 20 to slide downwards along the inner wall of the guide frame 12 through releasing the length of the steel wire rope without blocking, simultaneously enabling the landing gear 3 to synchronously move downwards, placing the balancing weight 21 in the basket frame main body 20 and between the two stable clamping blocks 52 when the total mass of the basket frame main body 20, the landing gear 3 and the balancing weight 21 needs to be regulated, then opening the electric telescopic rod 53, enabling the two relatively distributed stable clamping blocks 52 to be close to each other and fixedly clamping the balancing weight 21, and avoiding random swing and impact of the balancing weight 21 on the basket frame main body 20 when an obstacle crossing impact test is carried out;
s2, preparation before obstacle surmounting impact test
Checking the buffer and tyre filling pressure of the landing gear 3, after the buffer and tyre filling pressure of the landing gear 3 meet the test requirements, charging the inside of the emission installation main body 40 by the air gun emission element 41 to store energy, setting a charging target value according to the current test speed requirements, and closing the air gun emission element 41 after the air pressure in the inside of the emission installation main body 40 reaches the air pressure value corresponding to the required speed;
s3, adjusting the height of the obstacle module 433
Pushing the mounting bracket 10 to slide in the sliding groove 11, adjusting the position of the landing gear 3 on the width of the mounting chassis 1, enabling the landing gear 3 to be positioned at the right upper end corresponding to the barrier module 433, driving the horizontal mounting plate 430 and the barrier module 433 to synchronously move upwards through the corresponding micro hydraulic cylinder 431, simultaneously enabling each auxiliary telescopic rod 432 to synchronously extend and support the horizontal mounting plate 430 and the barrier module 433, at the moment, enabling the first sliding strip 4300 to synchronously slide in the vertical sliding groove 421 until the barrier module 433 is moved out of the mounting notch 420, enabling the horizontal mounting plate 430 to stop sliding after the micro hydraulic cylinder 431 is closed, enabling the electromagnetic chuck 4302 to be electrified, and enabling the first sliding strip 4300 to be fixedly adsorbed with the strip-shaped metal plate 423 under the action of electromagnetic attraction force;
s4, performing obstacle surmounting impact test
Clicking the firing button of the air cannon firing element 41 causes the high-pressure air in the firing installation main body 40 to push the high-speed sliding table 42 to slide on the installation chassis 1 towards the side close to the landing gear 3, and the barrier module 433 slides synchronously to strike the landing gear 3 wheels at a preset speed, thereby obtaining the barrier-crossing performance data of the landing gear 3 and completing the barrier-crossing impact test.
Example 3: this embodiment differs from embodiment 1 in that:
as shown in fig. 5, two sliding clamping grooves 13 are arranged on the installation chassis 1 along the horizontal direction, the two sliding clamping grooves 13 are distributed in parallel along the width direction of the installation chassis 1, second sliding strips 422 which are in one-to-one correspondence with the sliding clamping grooves 13 and are in sliding connection with the sliding clamping grooves 13 are arranged at the bottom end of the high-speed sliding table 42, and lubricating oil is filled between the sliding clamping grooves 13 and the second sliding strips 422.
Example 4: the present embodiment describes a landing gear running obstacle surmounting impact test method for a carrier-based aircraft based on embodiment 3, which is different from embodiment 2 in that:
when the high-speed sliding table 42 is pushed by the high-pressure air emitted by the air cannon emitting element 41 to sideslip close to the landing gear 3, the bottom end of the high-speed sliding table 42 can be supported and limited by the sliding connection between the second sliding bar 422 at the bottom end of the high-speed sliding table 42 and the sliding clamping groove 13 on the installation chassis 1, so that the high-speed sliding table 42 is compactly connected with the installation chassis 1.
Example 5: this embodiment differs from embodiment 3 in that:
as shown in fig. 8, each stable clamping block 52 is formed by sequentially arranging 3 sub-clamping blocks 521 from top to bottom, the upper end of each sub-clamping block 521 is provided with an inverted-T-shaped insertion sliding chute 522 with an inverted-T-shaped cross section, the lower end of each sub-clamping block 521 is provided with an inverted-T-shaped insertion sliding bar 523, two adjacent sub-clamping blocks 521 are connected through corresponding insertion sliding chutes 522 and inverted-T-shaped insertion sliding bars 523, and the lower end of the sub-clamping block 521 at the bottommost end is in a planar structure and is in sliding connection with the horizontal sliding chute 50;
the opposite sides of the two vertical installation bars 51 are respectively provided with 3 first connection sockets 510,3 which are uniformly distributed from top to bottom, the first connection sockets 510 are in one-to-one correspondence with the 3 sub clamping blocks 521, the side wall of each sub clamping block 521 on the side opposite to the first connection socket 510 is provided with a second connection socket 511, the number of the electric telescopic rods 53 is 3, and the 3 electric telescopic rods 53 are sequentially arranged between the first connection sockets 510 and the second connection sockets 511 which are relatively distributed;
the inner wall of the inserting chute 522 is provided with an anti-slip pad; wherein, the anti-skid pad adopts the prior art.
Example 6: the present embodiment describes a landing gear running obstacle surmounting impact test method for a carrier-based aircraft based on embodiment 5, which is different from embodiment 4 in that:
when the overall total mass of the basket body 20, the landing gear 3 and the balancing weights 21 is required to be adjusted according to test requirements, a plurality of balancing weights 21 are sequentially arranged and piled in the basket body 20 from bottom to top and positioned between the two stable clamping blocks 52, when the height of the stable clamping blocks 52 is required to be adjusted according to the piling height of the balancing weights 21, one sub clamping block 521 can be replaced at the upper end of the bottommost sub clamping block 521, the inverted T-shaped splicing sliding bar 523 at the bottom end of the newly placed sub clamping block 521 is in sliding connection with the splicing sliding groove 522 corresponding to the sub clamping block 521 at the bottom end, the placing steps are repeated until the number of the placed balancing weights 21 reaches the requirement, then, each electric telescopic rod 53 is started, the two electric telescopic rods 53 which are distributed oppositely are mutually close, and the sub clamping blocks 521 which are distributed oppositely are mutually close synchronously, so that the balancing weights 21 are clamped and fixed;
as the stacking height of each sub-clamping block 521 increases, in order to increase the clamping force, each sub-clamping block 521 can be supported and pushed by providing the electric telescopic rods 53 corresponding to each sub-clamping block 521 one by one on the vertical mounting bar 51;
by providing a slip pad on the inner wall of the mating chute 522, the friction between the inverted-T mating slide 523 and the mating chute 522 is increased.
Example 7: this embodiment differs from embodiment 1 in that:
the number of the mounting notches 420 is 4, the 4 mounting notches 420 are distributed along the width direction of the mounting chassis 1, each mounting notch 420 is internally provided with a horizontal mounting plate 430, and the corresponding barrier module 433 on each horizontal mounting plate 430 is used for simulating various barriers on the deck of the aircraft carrier.
Example 8: this embodiment differs from embodiment 3 in that:
the installation chassis 1 is provided with three sliding clamping grooves 13 along the horizontal direction, the three sliding clamping grooves 13 are distributed in parallel along the width direction of the installation chassis 1, the bottom end of the high-speed sliding table 42 is provided with second sliding strips 422 which are in one-to-one correspondence with the sliding clamping grooves 13 and are in sliding connection, and lubricating oil is filled between the sliding clamping grooves 13 and the second sliding strips 422.
Example 9: this embodiment differs from embodiment 5 in that:
each stable clamping block 52 is composed of 4 sub-clamping blocks 521 which are sequentially arranged from top to bottom.
Claims (7)
1. The landing gear running obstacle crossing impact test equipment for the carrier-based aircraft is characterized by comprising a mounting chassis (1) with a mounting bracket (10) at the upper end, a hanging basket assembly (2) arranged on the mounting bracket (10), a landing gear (3) connected with the hanging basket assembly (2) and an obstacle crossing impact test assembly (4) arranged on the bottom surface of the mounting chassis (1);
a first sliding groove (11) is formed in the mounting chassis (1) along the width direction of the mounting chassis, the bottom end of the vertical section of the mounting bracket (10) is in sliding connection with the first sliding groove (11), a guide frame (12) is arranged on the lower side of the horizontal section of the mounting bracket (10), the hanging basket assembly (2) can slide up and down along the inner wall of the guide frame (12) through external driving equipment, the landing gear (3) is connected with the bottom end of the hanging basket assembly (2), and the horizontal section of the mounting bracket (10) is vertically connected with the upper end of the vertical section;
the obstacle crossing impact test assembly (4) comprises an emission installation main body (40) arranged on the installation chassis (1) along the length direction, an air cannon emission element (41) arranged on the emission installation main body (40) and far away from the landing gear (3), a high-speed sliding table (42) arranged on the emission installation main body (40) and near the landing gear (3), and an obstacle simulation element (43) arranged on the high-speed sliding table (42);
a through sliding opening (400) is formed in one side, close to the landing gear (3), of the launching installation main body (40), one end of the high-speed sliding table (42) passes through the through sliding opening (400) and extends into the launching installation main body (40), the other end of the high-speed sliding table (42) is positioned outside the launching installation main body (40), a sealing sliding block (44) is arranged at one end, positioned in the launching installation main body (40), of the high-speed sliding table (42), and the sealing sliding block (44) slides to one side, close to the landing gear (3), along the launching installation main body (40) through driving of the air cannon launching element (41), and an installation notch (420) is formed in the high-speed sliding table (42);
the obstacle simulation element (43) comprises a horizontal installation plate (430) which is provided with a first sliding bar (4300) at the left side and the right side and is positioned in the installation notch (420), a micro hydraulic cylinder (431) which is arranged at the center of the bottom of the horizontal installation plate (430), a plurality of auxiliary telescopic rods (432) which are arranged at the bottom of the horizontal installation plate (430) and are uniformly distributed along the circumferential direction of the horizontal installation plate (430), and an obstacle module (433) which is arranged at the upper part of the horizontal installation plate (430), wherein the left side and the right side of the installation notch (420) are respectively provided with a second sliding groove (421), and the first sliding bar (4300) is correspondingly and slidably connected with the second sliding grooves (421);
the plurality of mounting notches (420) are arranged, the plurality of mounting notches (420) are distributed along the width direction of the mounting chassis (1), each mounting notch (420) is internally provided with a horizontal mounting plate (430), the periphery of each barrier module (433) is provided with a connecting convex edge (434), the connecting convex edges (434) are connected with the horizontal mounting plates (430) through a plurality of fastening bolts, the connecting positions are provided with a pressing frame (435), and the shape of the pressing frame (435) is matched with the shape of the outer edge of the barrier module (433);
the second sliding groove (421) both sides all are equipped with bar metal sheet (423), first sliding strip (4300) both sides all are equipped with coupling groove (4301), and every swing joint has electromagnetic chuck (4302) in coupling groove (4301), electromagnetic chuck (4302) flushes with first sliding strip (4300) lateral wall.
2. The landing gear running obstacle surmounting impact test device for the carrier-based aircraft according to claim 1, wherein a plurality of sliding clamping grooves (13) are formed in the mounting chassis (1) along the horizontal direction, the sliding clamping grooves (13) are distributed in parallel along the width direction of the mounting chassis (1), second sliding strips (422) which are in one-to-one correspondence with the sliding clamping grooves (13) and are in sliding connection are arranged at the bottom end of the high-speed sliding table (42), and lubricating oil is filled between the sliding clamping grooves (13) and the second sliding strips (422).
3. The landing gear running obstacle surmounting impact test device for the carrier-based aircraft according to claim 1, wherein the hanging basket assembly (2) comprises a hanging basket frame body (20) which is connected with the side wall of the guide frame (12) on the left side and the right side in a sliding manner, a balancing weight (21) which is arranged in the hanging basket frame body (20) and is connected with the bottom end of the hanging basket frame body (20), a stable clamping assembly (5) is arranged in the hanging basket frame body (20), the stable clamping assembly (5) comprises a horizontal sliding groove (50) which is arranged at the bottom end inside the hanging basket frame body (20), vertical mounting strips (51) which are symmetrically distributed at the left side and the right side inside the hanging basket frame body (20), two stable clamping blocks (52) which are arranged between the two vertical mounting strips (51) and are connected with the horizontal sliding groove (50) in a sliding manner, and an electric telescopic rod (53) which is arranged between the vertical mounting strips (51) and the corresponding stable clamping blocks (52).
4. A carrier-based aircraft landing gear running obstacle crossing impact test device according to claim 3, wherein each stable clamping block (52) is formed by sequentially arranging a plurality of sub-clamping blocks (521) from top to bottom, the upper end of each sub-clamping block (521) is provided with an inverted-T-shaped splicing chute (522) with the cross section, the lower end of each sub-clamping block (521) is provided with an inverted-T-shaped splicing slide bar (523), and two adjacent sub-clamping blocks (521) are connected with each other through the corresponding splicing chute (522) and the inverted-T-shaped splicing slide bar (523), and the lower end of the sub-clamping block (521) at the bottommost end is of a planar structure and is in sliding connection with the horizontal sliding chute (50).
5. The landing gear running obstacle surmounting impact test device for the carrier aircraft according to claim 4, wherein a plurality of first connecting jacks (510) which are uniformly distributed from top to bottom are arranged on opposite sides of the two vertical mounting strips (51), the plurality of first connecting jacks (510) are in one-to-one correspondence with the plurality of sub clamping blocks (521), a second connecting jack (511) is arranged on a side wall of each sub clamping block (521) opposite to the side wall of the first connecting jack (510), a plurality of electric telescopic rods (53) are arranged, and the plurality of electric telescopic rods (53) are sequentially arranged between the first connecting jacks (510) and the second connecting jacks (511) which are oppositely distributed.
6. The landing gear running obstacle crossing impact test equipment for the carrier-based aircraft according to claim 4, wherein an anti-slip pad is arranged on the inner wall of the plugging sliding groove (522).
7. A method for a landing gear running obstacle crossing impact test of a carrier-based aircraft, based on the landing gear running obstacle crossing impact test equipment of any one of claims 1-6, comprising the following steps:
s1 release of landing gear (3)
Opening external driving equipment and enabling the hanging basket assembly (2) to slide downwards along the inner wall of the guide frame (12) through releasing the length of the steel wire rope without blocking, and simultaneously enabling the landing gear (3) to synchronously move downwards;
s2, preparation before obstacle surmounting impact test
Checking the buffer and the tire filling pressure of the landing gear (3), after the buffer and the tire filling pressure of the landing gear (3) meet the test requirements, charging the inside of the emission installation main body (40) through the air gun emission element (41), setting a charging target value according to the current test speed requirements, and closing the air gun emission element (41) after the air pressure in the inside of the installation main body (40) to be emitted reaches the air pressure value corresponding to the required speed;
s3, adjusting the height of the obstacle module (433)
Pushing the mounting bracket (10) to slide in the first sliding groove (11) to adjust the position of the landing gear (3), then driving the horizontal mounting plate (430) and the barrier module (433) to synchronously move upwards through the micro hydraulic cylinder (431), simultaneously synchronously extending the auxiliary telescopic rods (432) and supporting the horizontal mounting plate (430) and the barrier module (433), and synchronously sliding the first sliding bar (4300) in the second sliding groove (421) until the barrier module (433) is moved out of the mounting notch (420);
s4, performing obstacle surmounting impact test
Clicking a launching button of an air cannon launching element (41) to enable high-pressure air in a launching installation main body (40) to push a high-speed sliding table (42) to slide towards one side close to a landing gear (3) on an installation chassis (1), enabling an obstacle module (433) to slide synchronously, and impacting a landing gear (3) wheel at a preset speed, so that landing gear (3) obstacle crossing performance data are obtained, and obstacle crossing impact tests are completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311308636.8A CN117048845B (en) | 2023-10-11 | 2023-10-11 | Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311308636.8A CN117048845B (en) | 2023-10-11 | 2023-10-11 | Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117048845A CN117048845A (en) | 2023-11-14 |
| CN117048845B true CN117048845B (en) | 2023-12-19 |
Family
ID=88661203
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311308636.8A Active CN117048845B (en) | 2023-10-11 | 2023-10-11 | Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117048845B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5817935A (en) * | 1995-11-21 | 1998-10-06 | Pirelli Coordinamento Pneuatici S.P.A. | Apparatus for testing a wheel passing over an obstacle |
| CN101532903A (en) * | 2009-04-08 | 2009-09-16 | 南京航空航天大学 | Drop test device for movable impact platform |
| JP2011232116A (en) * | 2010-04-27 | 2011-11-17 | Japan Automobile Research Inst Inc | Pre-crash testing method and pre-crash testing device |
| CN107782574A (en) * | 2017-12-02 | 2018-03-09 | 西北农林科技大学 | A kind of hillside tractor obstacle detouring test platform |
| CN107884210A (en) * | 2017-11-18 | 2018-04-06 | 哈尔滨工业大学（威海） | A kind of tire obstacle detouring mechanical response comprehensive test device |
| KR101850877B1 (en) * | 2016-10-31 | 2018-05-31 | 원상연 | Drop impact test equipment |
| CN108362638A (en) * | 2017-12-06 | 2018-08-03 | 中国飞机强度研究所 | A kind of arresting system dynamic energy absorption characteristics experimental provision and experimental method |
| CN111397921A (en) * | 2020-04-02 | 2020-07-10 | 储德姣 | Performance test detection system after automobile manufacturing, assembling and molding |
| CN115753133A (en) * | 2022-11-01 | 2023-03-07 | 吉林大学 | Obstacle crossing driving characteristic test device under high and low temperature environment of planet wheel |
| CN115808280A (en) * | 2022-11-16 | 2023-03-17 | 中国矿业大学 | Double-wheel-pair-framework multi-mode excitation equipment and method for rail vibration damping evaluation |
| CN116443266A (en) * | 2023-03-29 | 2023-07-18 | 中国飞机强度研究所 | Emergent breaking dynamic test device of undercarriage |
| CN116773229A (en) * | 2023-08-15 | 2023-09-19 | 山东金彭新能源科技有限公司 | Durable detection device of automobile shock absorber ware |
-
2023
- 2023-10-11 CN CN202311308636.8A patent/CN117048845B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5817935A (en) * | 1995-11-21 | 1998-10-06 | Pirelli Coordinamento Pneuatici S.P.A. | Apparatus for testing a wheel passing over an obstacle |
| CN101532903A (en) * | 2009-04-08 | 2009-09-16 | 南京航空航天大学 | Drop test device for movable impact platform |
| JP2011232116A (en) * | 2010-04-27 | 2011-11-17 | Japan Automobile Research Inst Inc | Pre-crash testing method and pre-crash testing device |
| KR101850877B1 (en) * | 2016-10-31 | 2018-05-31 | 원상연 | Drop impact test equipment |
| CN107884210A (en) * | 2017-11-18 | 2018-04-06 | 哈尔滨工业大学（威海） | A kind of tire obstacle detouring mechanical response comprehensive test device |
| CN107782574A (en) * | 2017-12-02 | 2018-03-09 | 西北农林科技大学 | A kind of hillside tractor obstacle detouring test platform |
| CN108362638A (en) * | 2017-12-06 | 2018-08-03 | 中国飞机强度研究所 | A kind of arresting system dynamic energy absorption characteristics experimental provision and experimental method |
| CN111397921A (en) * | 2020-04-02 | 2020-07-10 | 储德姣 | Performance test detection system after automobile manufacturing, assembling and molding |
| CN115753133A (en) * | 2022-11-01 | 2023-03-07 | 吉林大学 | Obstacle crossing driving characteristic test device under high and low temperature environment of planet wheel |
| CN115808280A (en) * | 2022-11-16 | 2023-03-17 | 中国矿业大学 | Double-wheel-pair-framework multi-mode excitation equipment and method for rail vibration damping evaluation |
| CN116443266A (en) * | 2023-03-29 | 2023-07-18 | 中国飞机强度研究所 | Emergent breaking dynamic test device of undercarriage |
| CN116773229A (en) * | 2023-08-15 | 2023-09-19 | 山东金彭新能源科技有限公司 | Durable detection device of automobile shock absorber ware |
Non-Patent Citations (2)
| Title |
|---|
| 甲板障碍对舰载机着陆性能影响仿真研究;赵碧波;吴斌;黄德东;;计算机仿真;第25卷(第12期);84-87 * |
| 舰载飞机起降装置动力学试验研究进展;胡锐 等;航空科学技术;第33卷(第1期);11-19 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117048845A (en) | 2023-11-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN117048845B (en) | Ship-borne aircraft landing gear running obstacle crossing impact test equipment and test method | |
| CN213580001U (en) | Electric motor car battery vibration detection testing machine | |
| CN103091064A (en) | Dynamic impact test equipment | |
| CN111634205B (en) | Anti-collision type new energy automobile is with filling electric pile | |
| CN112147521A (en) | Square battery charging and discharging test movement mechanism and application method | |
| CN103630380A (en) | Vehicle body strength test bogie loading device and vehicle body strength test bogie loading method | |
| CN109193459A (en) | Guide rope side incoming type releasing pulley | |
| CN113670588A (en) | Test stand for testing structural performance of stairs with different specifications | |
| CN113147861A (en) | Luggage carrying equipment with anti-collision function | |
| CN104483143A (en) | Rack for durability test of frame of forklift | |
| CN107840055B (en) | Battery ejection device | |
| CN216007973U (en) | Mechanical civil air defense stereo garage | |
| CN202414918U (en) | Device for preventing elevator from falling off | |
| CN215407722U (en) | Anti-shaking and anti-falling device of mechanical stereo garage | |
| CN214041678U (en) | Square battery charge-discharge test movement mechanism | |
| CN111366376A (en) | Downhill curve brake performance testing device for automobile | |
| CN212748581U (en) | Wear-resisting cast ball falling ball testing machine | |
| CN210121646U (en) | Riveting mechanism of solenoid valve guide cover assembly equipment | |
| CN201933962U (en) | Balancing device for sectional counterweight of industrial door | |
| CN213091139U (en) | Auto parts pressure test equipment | |
| CN111689243A (en) | Novel hacking machine | |
| CN111005606A (en) | Lifting frame of planar mobile garage and operation method thereof | |
| CN218489482U (en) | Alternating-current charging pile with strong protection performance for new energy automobile | |
| CN218702946U (en) | Electric automobile rescue storage battery car | |
| CN215284451U (en) | Heavy truck battery floor truck of side bolt formula |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Wang Binwen Inventor after: Yang Zhengquan Inventor after: Li Xiao Inventor after: Xue Yunfang Inventor after: You Zhongze Inventor after: Zhang Yu Inventor after: Yang Qiang Inventor before: Wang Binwen Inventor before: Yang Zhengquan Inventor before: Li Xiao Inventor before: Xue Yunfang Inventor before: You Zongze Inventor before: Zhang Yu Inventor before: Yang Qiang |