CN112340058B - Test platform for carrier-based helicopter landing auxiliary equipment and operation method thereof - Google Patents
Test platform for carrier-based helicopter landing auxiliary equipment and operation method thereof Download PDFInfo
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- CN112340058B CN112340058B CN202011223842.5A CN202011223842A CN112340058B CN 112340058 B CN112340058 B CN 112340058B CN 202011223842 A CN202011223842 A CN 202011223842A CN 112340058 B CN112340058 B CN 112340058B
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- 238000012360 testing method Methods 0.000 title claims abstract description 86
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000004088 simulation Methods 0.000 claims description 35
- 229910000831 Steel Inorganic materials 0.000 claims description 29
- 239000010959 steel Substances 0.000 claims description 29
- 230000005540 biological transmission Effects 0.000 claims description 24
- 239000000523 sample Substances 0.000 claims description 22
- 210000000078 claw Anatomy 0.000 claims description 13
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 238000013016 damping Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 abstract description 2
- 238000011056 performance test Methods 0.000 abstract description 2
- 238000012544 monitoring process Methods 0.000 description 6
- 238000013459 approach Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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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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- 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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to the technical field of mechanical equipment performance test, in particular to a test platform of carrier-based helicopter landing auxiliary equipment and an operation method thereof.A double-cylinder parallel hydraulic cylinder drives the carrier-based helicopter landing auxiliary equipment to simulate the action of the carrier-based helicopter landing auxiliary equipment approaching to a helicopter; the whole process of the invention is automatically controlled, so that the operation of the test process is simpler, and manpower and material resources are saved.
Description
Technical Field
The invention relates to the technical field of mechanical equipment performance testing, in particular to a test platform of carrier-based helicopter landing auxiliary equipment and an operation method thereof.
Background
At present, with the research and development of helicopter technology, the application of helicopters in offshore operation is increasingly wide, and various devices for ensuring the rising and falling safety of helicopters appear, wherein one of the devices is carrier-based helicopter landing auxiliary equipment. The carrier-based helicopter landing auxiliary equipment can be moved to a place adjacent to the landing of the helicopter, and the mechanical gripper on the carrier-based helicopter landing auxiliary equipment can grasp the probe rod extending out of the helicopter to fix the helicopter on a ship. However, the inspection of the quality and the performance of the carrier-based helicopter landing auxiliary equipment also depends on simple mechanical equipment and a large amount of manpower, so that the operation is complicated, time and labor are wasted, the working environment of the carrier-based helicopter landing auxiliary equipment on a ship is simulated only by a hoisting method, and the efficiency is not high and the safety is not high. When the simulation helicopter probe approaches the carrier-based helicopter landing auxiliary equipment, the simulation probe needs to be manually sent into a capture area of the carrier-based helicopter landing auxiliary equipment, and great labor is consumed.
Disclosure of Invention
The invention aims to solve the problem that the prior art can not efficiently, time-saving, safely and accurately test the quality and performance of carrier-based helicopter landing auxiliary equipment.
In order to achieve the technical problem, the invention provides the following technical scheme:
a test platform for carrier-based helicopter landing auxiliary equipment comprises: the device comprises landing auxiliary equipment, a simulation platform, a test platform base, a double-cylinder parallel hydraulic cylinder, a transmission assembly, a beam assembly, a support, a single-rod hydraulic cylinder, a track and a capturing mechanical claw; the device comprises a track, landing auxiliary equipment, a capturing mechanical claw, a double-cylinder parallel hydraulic cylinder, a support and a transmission assembly, wherein the track is arranged in a test platform base, the landing auxiliary equipment is arranged on the surface of the track and is connected with the transmission assembly, the landing auxiliary equipment is provided with the capturing mechanical claw, the double-cylinder parallel hydraulic cylinder is connected with the transmission assembly and is arranged in the test platform base, and the support is arranged on the left side and the right side of the test platform base; the single-rod hydraulic cylinder is installed at the top end of the support, the beam assembly is installed on the support and connected with the single-rod hydraulic cylinder, and the testing platform base is installed on the simulation platform.
Further, the transmission assembly includes: the device comprises a steel wire rope, a fixed pulley, a bottom layer sliding block, a tensioning wheel and a tensioning hydraulic cylinder; the fixed pulley, the steel wire rope and the tensioning hydraulic cylinder are all fixed in the testing platform base through threaded connection, the number of the steel wire ropes is at least 2, the number of the fixed pulleys is at least 8, one end of each steel wire rope is connected with the bottom sliding block, the other end of each steel wire rope is connected with two ends of the double-cylinder parallel hydraulic cylinder, the steel wire rope abuts against the fixed pulleys, the steel wire ropes abut against the fixed pulleys and the tensioning wheels, and the steel wire ropes and the tensioning wheels are arranged at the end portions of the tensioning hydraulic cylinder.
Furthermore, the beam assembly comprises a beam, a beam sliding block, a beam trolley, a double-rod hydraulic cylinder, a simulation probe rod, a beam magnetostrictive displacement sensor and a pull pressure sensor; at least 4 beam sliding blocks are welded at two ends of the beam, a double-rod hydraulic cylinder is mounted on the beam, two ends of a piston rod of the double-rod hydraulic cylinder are connected with the beam, and a cylinder barrel of the double-rod hydraulic cylinder is connected with the beam trolley; the beam trolley is connected with a magnetic ring of a beam magnetostrictive displacement sensor arranged on the beam; the lower end of the beam trolley is at least provided with four pull pressure sensors, and the lower parts of the pull pressure sensors are provided with simulation probe rods.
Furthermore, the double-cylinder parallel hydraulic cylinder is mainly formed by connecting a coarse hydraulic cylinder and a fine hydraulic cylinder in parallel.
An operation method of a test platform of carrier-based helicopter landing auxiliary equipment comprises the following steps: the method comprises the following steps:
s1, hoisting the landing auxiliary equipment on a test platform base of the test equipment and connecting the landing auxiliary equipment with the transmission assembly through the bottom layer sliding block;
s2, connecting two ends of a steel wire rope in a test platform base of the test equipment to two ends of a bottom sliding block of the landing auxiliary equipment respectively, and then using a tensioning hydraulic cylinder and a tensioning steel wire rope;
s3, driving the transmission assembly to further drive the landing auxiliary equipment to move along the rail through the double-cylinder parallel hydraulic cylinder to complete the test of capturing the simulation probe rod;
s4, detecting the stress of the simulation probe rod through a tension pressure sensor arranged on the beam assembly to finish the detection of the straightening force;
s5, applying resistance to the mechanical catching claw through the simulation probe rod by the double-rod hydraulic cylinder to finish the simulation damping force test;
s6, applying transverse, longitudinal and vertical forces to a capturing mechanical claw of the landing auxiliary equipment through a double-cylinder parallel hydraulic cylinder, a single-rod hydraulic cylinder and a double-rod hydraulic cylinder to finish a loading force test;
s7, the steps S3 to S6 are carried out, so that the simulation platform simulates sea conditions of all levels;
s8, after the test is finished, the landing auxiliary equipment retracts to the initial position under the traction of the transmission assembly;
s9, connecting the test platform with a steel wire rope of the landing auxiliary equipment;
and S10, hoisting the landing aid in the test away from the test equipment.
Compared with the prior art, the test platform for the carrier-based helicopter landing auxiliary equipment and the operation method thereof have the advantages that:
1. the invention provides a test platform of carrier-based helicopter landing auxiliary equipment and an operation method thereof, which can simulate the movement of a ship deck in severe sea conditions of more than 4-level or even 6-level, and improve the accuracy of the simulation of the working condition of the carrier-based helicopter landing auxiliary equipment.
2. The invention provides a test platform of carrier-based helicopter landing auxiliary equipment and an operation method thereof, which adopt automatic control on the test process of the performance and the quality of the carrier-based helicopter landing auxiliary equipment, only one operator is needed to complete the test of the performance and the quality of the carrier-based helicopter landing auxiliary equipment, thereby greatly reducing the operation difficulty in the test process, saving manpower and material resources and improving the test efficiency.
3. The invention provides a test platform of carrier-based helicopter landing auxiliary equipment and an operation method thereof, wherein personnel do not need to approach the test equipment in the test process, and the danger to related personnel caused by the accident that the carrier-based helicopter landing auxiliary equipment is in failure, collides with the test equipment and the like in the test process is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic diagram of the overall structure of the platform of the present invention;
FIG. 2 is a schematic diagram of the platform structure of the present invention;
FIG. 3 is a schematic view of the transmission assembly of FIG. 1 of the present invention;
fig. 4 is a schematic view of the landing aid of fig. 1 of the present invention;
FIG. 5 is a schematic representation of the present invention for the connection of the steel cords of FIG. 1;
FIG. 6 is a schematic illustration of the parallel double-bar hydraulic cylinder of FIG. 1 according to the present invention;
fig. 7 is a schematic view of the cross-beam assembly of fig. 1 in accordance with the present invention.
Reference numerals: 1-a beam assembly; 2-landing aid; 3-a simulation platform; 4-single-rod hydraulic cylinder; 5-a support; 6-double-rod hydraulic cylinder; 7-a beam trolley; 8-a cross beam; 9-simulating a probe rod; 10-a transmission assembly; 11-double cylinders parallel hydraulic cylinder; 12-a steel wire rope; 13-a tensioning wheel; 14-tensioning hydraulic cylinders; 15-a fixed pulley; 16 a test platform base; 17-a catch gripper; 18-a bottom layer slider; 19-coarse hydraulic cylinder; 20-fine hydraulic cylinder; 21-a beam slide block; 22-a beam magnetostrictive displacement sensor; 23-a pull pressure sensor; 24-track.
Detailed Description
The technical solution of the present invention will be clearly and completely described by the following embodiments. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. 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.
As shown in fig. 1 to 7, the test platform for the carrier-based helicopter landing aid comprises: the device comprises landing auxiliary equipment 2, a simulation platform 3, a test platform base 16, a double-cylinder parallel hydraulic cylinder 11, a transmission assembly 10, a beam assembly 1, a support 5, a single-rod hydraulic cylinder 4, a track 24 and a capturing mechanical claw 17; the track 24 is installed in the test platform base 16, the landing aid 2 is installed on the surface of the track 24 and connected with the transmission assembly 10, the landing aid 2 is provided with a capturing mechanical claw 17, the double-cylinder parallel hydraulic cylinder 11 is connected with the transmission assembly 10 and is arranged in the test platform base 16, and the supports 5 are arranged on the left side and the right side of the test platform base 16; the single-rod hydraulic cylinder 4 is installed at the top end of the support 5, the beam assembly 1 is installed on the support 5 and connected with the single-rod hydraulic cylinder 4, and the test platform base 16 is installed on the simulation platform 3.
Preferably, the transmission assembly 10 includes: a steel wire rope 12, a fixed pulley 15, a bottom layer sliding block 18, a tensioning wheel 13 and a tensioning hydraulic cylinder 14; the fixed pulleys 15, the steel wire ropes 12 and the tensioning hydraulic cylinders 14 are all fixed in the testing platform base 16 through threaded connection, the number of the steel wire ropes 12 is at least 2, the number of the fixed pulleys 15 is at least 8, one ends of the steel wire ropes 12 are connected with the bottom layer sliding block 18, the other ends of the steel wire ropes are connected with two ends of the double-cylinder parallel hydraulic cylinder 11, the steel wire ropes 12 abut against the fixed pulleys 15 and the tensioning wheels 13, and the steel wire ropes 12 and the tensioning wheels 13 are arranged at the end portions of the tensioning hydraulic cylinders 14.
Preferably, the beam assembly 1 includes: the device comprises a beam 8, a beam slider 21, a beam trolley 7, a double-rod hydraulic cylinder 6, a simulation probe rod 9, a beam magnetostrictive displacement sensor 22 and a pull pressure sensor 23; two ends of the beam 8 are welded with at least 4 beam sliding blocks 21, a double-rod hydraulic cylinder 6 is mounted on the beam 8, two ends of a piston rod of the double-rod hydraulic cylinder 6 are connected with the beam 8, and a cylinder barrel of the double-rod hydraulic cylinder 6 is connected with the beam trolley 7; the beam trolley 7 is connected with a magnetic ring of a beam magnetostrictive displacement sensor 22 arranged on the beam 8; the lower end of the beam trolley 7 is at least provided with four pull pressure sensors 23, and the lower parts of the pull pressure sensors 23 are provided with simulation feeler levers 9.
Preferably, the double-cylinder parallel hydraulic cylinder 11 is mainly composed of a coarse hydraulic cylinder 19 and a fine hydraulic cylinder 20 which are connected in parallel.
An operation method of a test platform of carrier-based helicopter landing auxiliary equipment comprises the following steps: the method comprises the following steps:
s1, hoisting the landing auxiliary equipment 2 on a test platform base 16 of the test equipment and connecting the landing auxiliary equipment with the transmission assembly 10 through a bottom layer slide block 18;
s2, respectively connecting two ends of a steel wire rope 12 in a test platform base 16 of the test equipment to two ends of a bottom sliding block 18 of the landing auxiliary equipment 2, and then tensioning a hydraulic cylinder 14 and the steel wire rope 12;
s3, driving the transmission assembly 10 to further drive the landing aid 2 to move along the rail 24 through the double-cylinder parallel hydraulic cylinder 11, and completing the test of capturing the simulation probe 9;
s4, detecting the stress of the simulation probe rod 9 through the tension and pressure sensor 23 arranged on the beam assembly 1 to finish the detection of the straightening force;
s5, applying resistance to the mechanical catching claw 17 through the simulation probe rod 9 by the double-rod hydraulic cylinder 11 to finish a simulation damping force test;
s6, transverse, longitudinal and vertical forces are applied to the capturing mechanical claw 17 of the ship auxiliary equipment 2 through the double-cylinder parallel hydraulic cylinder 11, the single-rod hydraulic cylinder 4 and the double-rod hydraulic cylinder 6, and a loading force test is completed;
s7, the steps S3 to S6 are carried out, so that the simulation platform 3 simulates sea conditions of all levels;
s8, after the test is finished, the landing aid 2 retracts to the initial position under the traction of the transmission assembly 10;
s9, connecting the test releasing platform with the steel wire rope 12 of the landing auxiliary equipment 2;
and S10, hoisting the landing aid 2 of the test away from the test equipment.
According to the embodiment of the invention, after the landing auxiliary equipment 2 is produced according to a specified production program, the landing auxiliary equipment 2 is hoisted on a test platform base 16 of the equipment, a capture area of the landing auxiliary equipment 2 faces a simulation probe 9, two ends of a steel wire rope 12 of the equipment are respectively connected to two ends of a sliding block 22 on the landing auxiliary equipment and the steel wire rope 12 is tensioned, various parameters of a test platform in the equipment are set on the control and monitoring equipment, a quick approach command is sent to the platform on the control and monitoring equipment, the platform rapidly pulls the landing auxiliary equipment 2 to approach the simulation probe 9 according to the command, the simulation probe 9 enters the capture area of the landing auxiliary equipment 2, the landing auxiliary equipment 2 captures the simulation probe 9, a performance test command is sent to the platform on the control and monitoring equipment, and the platform applies a transverse direction to a capture paw 17 on the landing auxiliary equipment 2 according to the command, And longitudinal and vertical forces are recorded in the control and monitoring equipment, various performances of the landing aid 2 of the test are displayed in the control and monitoring equipment, the performances and the quality of the landing aid 2 of the test are compared with various performance standards, whether the performances and the quality of the landing aid 2 of the test meet the requirements or not is analyzed, after performance judgment is completed, a test completion command is sent out on the control and monitoring equipment, and the landing aid 2 returns to an initial position, so that the equipment test is completed.
The above-mentioned embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.
Claims (4)
1. The utility model provides a test platform of carrier-based helicopter auxiliary assembly that boards a ship which characterized in that includes: the device comprises landing auxiliary equipment (2), a simulation platform (3), a test platform base (16), a double-cylinder parallel hydraulic cylinder (11), a transmission assembly (10), a beam assembly (1), a support (5), a single-rod hydraulic cylinder (4), a track (24) and a capturing mechanical claw (17); the track (24) is installed in the testing platform base (16), the landing auxiliary equipment (2) is installed on the surface of the track (24) and connected with the transmission assembly (10), the landing auxiliary equipment (2) is provided with a capturing mechanical claw (17), the double-cylinder parallel hydraulic cylinders (11) are connected with the transmission assembly (10) and are all arranged in the testing platform base (16), and the supports (5) are arranged on the left side and the right side of the testing platform base (16); the single-rod hydraulic cylinder (4) is installed at the top end of the support (5), the beam assembly (1) is installed on the support (5) and connected with the single-rod hydraulic cylinder (4), and the testing platform base (16) is installed on the simulation platform (3);
the beam assembly (1) comprises a beam (8), a beam sliding block (21), a beam trolley (7), a double-rod hydraulic cylinder (6), a simulation probe rod (9), a beam magnetostrictive displacement sensor (22) and a pull pressure sensor (23); at least 4 beam sliding blocks (21) are welded at two ends of the beam (8), a double-rod hydraulic cylinder (6) is mounted on the beam (8), two ends of a piston rod of the double-rod hydraulic cylinder (6) are connected with the beam (8), and a cylinder barrel of the double-rod hydraulic cylinder (6) is connected with the beam trolley (7); the beam trolley (7) is connected with a magnetic ring of a beam magnetostrictive displacement sensor (22) arranged on a beam (8), at least four pull pressure sensors (23) are arranged at the lower end of the beam trolley (7), and a simulation probe rod (9) is arranged at the lower part of each pull pressure sensor (23).
2. The test platform for the carrier-based helicopter landing auxiliary equipment according to claim 1, characterized in that: the transmission assembly (10) comprises: the device comprises a steel wire rope (12), a fixed pulley (15), a bottom layer sliding block (18), a tensioning wheel (13) and a tensioning hydraulic cylinder (14); fixed pulley (15), wire rope (12), tensioning pneumatic cylinder (14) pass through threaded connection all fixed with test platform base (16) in, wire rope (12) are 2 at least, and fixed pulley (15) are 8 at least, and wire rope (12) one end links to each other with bottom slider (18), and the other end is connected with double-cylinder parallel hydraulic cylinder (11) both ends, and wire rope (12) conflict fixed pulley (15), wire rope (12) conflict fixed pulley (15) and take-up pulley (13), wire rope (12) and take-up pulley (13) set up with tensioning pneumatic cylinder (14) tip.
3. The test platform for the carrier-based helicopter landing auxiliary equipment according to claim 1, characterized in that: the double-cylinder parallel hydraulic cylinder (11) is mainly formed by connecting a coarse hydraulic cylinder (19) and a fine hydraulic cylinder (20) in parallel.
4. An operation method of a test platform of carrier-based helicopter landing auxiliary equipment comprises the following steps: the method comprises the following steps:
s1, hoisting the landing auxiliary equipment (2) on a test platform base (16) of the test platform and connecting the landing auxiliary equipment with the transmission assembly (10) through a bottom layer sliding block (18);
s2, connecting two ends of a steel wire rope (12) in a test platform base (16) of the test platform to two ends of a bottom layer sliding block (18) of the landing auxiliary equipment (2) respectively, and then tensioning the steel wire rope (12) by using a tensioning hydraulic cylinder (14);
s3, driving the transmission assembly (10) through the double-cylinder parallel hydraulic cylinder (11) to further drive the landing auxiliary equipment (2) to move along the track (24), and completing the test of capturing the simulation probe rod (9);
s4, detecting the stress of the simulation probe rod (9) through a tension pressure sensor (23) arranged on the beam assembly (1) to finish the detection of the straightening force;
s5, applying resistance to the mechanical catching claw (17) through the simulation probe rod (9) by the double-rod hydraulic cylinder (6) to finish the simulation damping force test;
s6, transverse, longitudinal and vertical forces are applied to a capturing mechanical claw (17) of the ship auxiliary equipment (2) through a double-cylinder parallel hydraulic cylinder (11), a single-rod hydraulic cylinder (4) and a double-rod hydraulic cylinder (6), and a loading force test is completed;
s7, the steps S3 to S6 are carried out, so that the simulation platform (3) simulates sea conditions of all levels;
s8, after the test is finished, the landing auxiliary equipment (2) retracts to the initial position under the traction of the transmission assembly (10);
s9, connecting the release test platform with a steel wire rope (12) of the landing auxiliary equipment (2);
and S10, hoisting the landing auxiliary equipment (2) of the test away from the test platform.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011223842.5A CN112340058B (en) | 2020-11-05 | 2020-11-05 | Test platform for carrier-based helicopter landing auxiliary equipment and operation method thereof |
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| CN202011223842.5A CN112340058B (en) | 2020-11-05 | 2020-11-05 | Test platform for carrier-based helicopter landing auxiliary equipment and operation method thereof |
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| CN112340058B true CN112340058B (en) | 2022-05-06 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113665831B (en) * | 2021-06-24 | 2022-12-27 | 中国舰船研究设计中心 | Shipborne unmanned aerial vehicle recovery docking window motion simulation device and method |
| CN114455090B (en) * | 2022-01-27 | 2023-06-16 | 燕山大学 | Transmission system suitable for ship-borne helicopter landing assisting device |
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| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN109094817A (en) * | 2018-08-29 | 2018-12-28 | 哈尔滨工业大学 | The adaptive undercarriage of carrier-based helicopter warship simulation system |
| CN109850177A (en) * | 2018-11-29 | 2019-06-07 | 中国船舶工业***工程研究院 | A method of being quickly tethered at operation on the sea helicopter |
| CN209258417U (en) * | 2018-12-03 | 2019-08-16 | 南京航空航天大学 | A kind of helicopter landing gear falls shake comprehensive experimental device |
| CN110816865A (en) * | 2019-10-21 | 2020-02-21 | 燕山大学 | Compensation type four-degree-of-freedom ship-based take-off and landing platform |
-
2020
- 2020-11-05 CN CN202011223842.5A patent/CN112340058B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101513936A (en) * | 2009-03-31 | 2009-08-26 | 王力丰 | Taking off device and taking off method for carrier-based aircraft |
| CN109094817A (en) * | 2018-08-29 | 2018-12-28 | 哈尔滨工业大学 | The adaptive undercarriage of carrier-based helicopter warship simulation system |
| CN109850177A (en) * | 2018-11-29 | 2019-06-07 | 中国船舶工业***工程研究院 | A method of being quickly tethered at operation on the sea helicopter |
| CN209258417U (en) * | 2018-12-03 | 2019-08-16 | 南京航空航天大学 | A kind of helicopter landing gear falls shake comprehensive experimental device |
| CN110816865A (en) * | 2019-10-21 | 2020-02-21 | 燕山大学 | Compensation type four-degree-of-freedom ship-based take-off and landing platform |
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