CN116968938B - Device and method for sliding cable-passing impact test of landing gear of carrier-based aircraft - Google Patents
Device and method for sliding cable-passing impact test of landing gear of carrier-based aircraft Download PDFInfo
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- CN116968938B CN116968938B CN202311240263.5A CN202311240263A CN116968938B CN 116968938 B CN116968938 B CN 116968938B CN 202311240263 A CN202311240263 A CN 202311240263A CN 116968938 B CN116968938 B CN 116968938B
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- 238000009863 impact test Methods 0.000 title claims abstract description 23
- 238000012360 testing method Methods 0.000 claims abstract description 37
- 230000005540 biological transmission Effects 0.000 claims abstract description 26
- 230000000903 blocking effect Effects 0.000 claims abstract description 11
- 229910000831 Steel Inorganic materials 0.000 claims description 18
- 239000010959 steel Substances 0.000 claims description 18
- 238000009434 installation Methods 0.000 claims description 9
- 230000001360 synchronised effect Effects 0.000 claims description 9
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 238000007789 sealing Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
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- 229910000984 420 stainless steel Inorganic materials 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0075—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by means of external apparatus, e.g. test benches or portable test 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
Abstract
The invention discloses a device and a method for a carrier-based aircraft landing gear sliding cable-passing impact test, which belong to the technical field of aircraft tests, wherein the test device comprises a device bracket, a vertical loading assembly arranged at the upper end inside the device bracket, a test piece arranged at the lower bottom surface of the vertical loading assembly, a transmission assembly arranged at the inner bottom of the device bracket and a blocking cable simulator arranged on the transmission assembly; the test equipment truly simulates the sliding cable passing process of the front landing gear of the carrier-based aircraft under the test environment, measures the dynamic load response of key structural members when the front landing gear of the carrier-based aircraft slides over the cable, and provides a reliable theoretical basis for researching and verifying the sliding cable passing capability of the landing gear.
Description
Technical Field
The invention relates to the technical field of aircraft tests, in particular to a device and a method for a carrier-based aircraft landing gear sliding cable-passing impact test.
Background
The carrier-based aircraft landing generally comprises several processes of approach, rope blocking, main landing, front landing, running, deceleration and the like. Each 14 m interval on the aircraft carrier surface can be provided with a total of 4 blocking ropes, and a first blocking rope is arranged at a position 40-50 m away from the tail end of the deck under the common condition, and the blocking ropes are supported by bow springs to be 30-50 cm higher than the flight deck. After carrier aircraft landing, the 2 nd or 3 rd arresting rope is generally hung by the arresting hook, and then the 1 st or 2 nd arresting rope which is remained in the advancing direction is quickly slipped.
In the process of reducing and sliding the carrier-based aircraft to pass the cable, different impact resistances caused by the supporting height and the tension of the blocking rope can cause the damage of the landing gear structure and even the condition that the cable cannot pass; in particular for small carrier-borne aircraft, such as carrier-borne coaches and unmanned aerial vehicles, the risk of landing gear structural damage and inability to pass cables, which are often caused by smaller wheel sizes and limited body structural space, can increase significantly.
Therefore, in order to ensure the service safety and operational performance of the carrier-based aircraft, the sliding cable passing capability of the landing gear of the carrier-based aircraft needs to be checked in a laboratory environment, the influences of the sliding cable passing capability and the sliding cable passing load of the landing gear of the carrier-based aircraft on the engine body structure need to be studied at different sliding speeds and supporting heights, the sliding cable passing capability of the landing gear is checked and verified, and test basis is provided for the service life estimation and performance design of the landing gear in the development stage of the carrier-based aircraft.
However, at present, research on equipment and a method for testing landing gear sliding over cable impact based on a high-acceleration steel belt in a laboratory environment is still blank, and research on equipment and a method for testing landing gear sliding over cable based on the high-acceleration steel belt in the laboratory environment is very important and urgent.
Disclosure of Invention
Aiming at the technical problems, the invention provides equipment and a method for a landing gear sliding cable-passing impact test of a carrier-based aircraft.
The technical scheme of the invention is as follows: the utility model provides a carrier-borne aircraft undercarriage slides cable impact test equipment, includes equipment support, sets up the vertical loading subassembly of the inside upper end of equipment support, sets up the test piece of bottom surface under the vertical loading subassembly, sets up the transmission subassembly of bottom in the equipment support and sets up the blocking rope simulator on the transmission subassembly; the equipment bracket comprises a supporting table and a guide frame arranged on one side of the upper end surface of the supporting table;
the vertical loading assembly comprises a hanging basket, a loading frame and a loading motor, wherein the hanging basket is in sliding clamping connection with the inside of the guide frame, the loading frame is arranged on the upper end face of the hanging basket, and the loading motor is arranged on the upper end face of the guide frame; the hanging basket is internally filled with a balancing weight; the output shaft of the loading motor is provided with a pushing screw rod penetrating through the guide frame and in threaded connection with the loading frame;
the test piece comprises an aircraft tire movably hinged to the lower bottom surface of the hanging basket through a landing gear, and support rods with two ends movably hinged to the side wall of the landing gear and the lower bottom surface of the hanging basket respectively; a hinge point force sensor is arranged at the joint of the support rod and the hanging basket;
the transmission assembly comprises two rotating shafts which are arranged on the upper end surface of the supporting table in parallel and far away from one side of the supporting rod, and a transmission motor which is arranged on the upper end surface of the supporting table and provides power for one of the rotating shafts; two ends of the two rotating shafts are rotatably clamped with a bearing seat which is fixedly connected with the supporting table respectively; the two ends of the two rotating shafts are respectively sleeved with a connecting fluted disc positioned at the inner side of the bearing seat at the corresponding position, and the two connecting fluted discs positioned at the same side on the two rotating shafts are connected through a steel belt;
the arresting cable simulators are provided with a plurality of arresting cable simulators, each arresting cable simulators are distributed between two steel belts at equal intervals, and each arresting cable simulators is movably clamped with the two steel belts through a locating rod.
Further, a filling channel is arranged on the side wall of the hanging basket, and a counterweight box is arranged on the guide frame at the position corresponding to the filling channel;
description: through counter weight box to hanging flower basket inside packing balancing weight, be favorable to improving the high efficiency and the convenience when balancing weight fills.
Further, the middle parts of the two rotating shafts are respectively sleeved with a synchronous gear, and the two synchronous gears are connected through a synchronous chain;
description: through set up synchronous gear on two rotation axis, utilize synchronous chain to connect two synchronous gears, guaranteed that the rotational speed of two rotation axes is unanimous to stability when having improved the stopper rope simulant and removed.
Further, annular guide rails positioned at the outer sides of the connecting fluted disc are sleeved at two ends of the two rotating shafts, and the two annular guide rails are fixedly connected with bearing seats at corresponding positions respectively; the two annular guide rails are provided with sliding grooves, and two ends of each arresting rope simulator are provided with sliding blocks which are in sliding clamping connection with the sliding grooves;
description: the two annular guide rails are utilized to guide the movement of the arresting rope simulators, so that the arresting rope simulators are prevented from falling off and shifting when the landing gear impacts the arresting rope simulators, and the reliability of the equipment is improved.
Furthermore, an adjusting frame is arranged on the arresting cable simulator, two ends of the adjusting frame are rotatably clamped with adjusting screws, and mounting blocks which are slidably clamped with the inner wall of the adjusting frame are connected to the two adjusting screws in a threaded manner; two ends of the arresting rope simulant are respectively connected with the two mounting blocks in a one-to-one correspondence manner;
description: the height of the installation blocks at the corresponding positions can be adjusted by utilizing the adjusting screws at the two ends of the adjusting frame, so that the height of the arresting cable simulators can be adjusted, and the influence of the arresting cable simulators with different heights on the landing gear sliding cable passing performance can be conveniently studied.
Further, tensioning inhaul cables penetrating through the mounting blocks are arranged at two ends of the arresting cable simulant, and the mounting blocks are connected with reels used for winding the tensioning inhaul cables at corresponding positions in a threaded manner;
description: through rotatory spool, utilize two tensioning guys to stretch the rope simulator to can adjust the rigidity of rope simulator, improve test data acquisition's reliability.
Further, limiting components for fixing the hanging basket are arranged on two sides of the guide frame; the limiting assembly comprises an installation box arranged on the side wall of the guide frame, an electric push rod arranged in the installation box and a limiting stay rod rotationally clamped on the guide frame; a through groove is arranged on the side wall of the guide frame and corresponds to the mounting box in position; the two limiting support rods are rotatably clamped in the through grooves, clamping grooves are formed in one ends, close to the mounting boxes, of the two limiting support rods, and the output ends of the electric push rods are respectively and slidably clamped with the clamping grooves on the two limiting support rods; the upper end face of one of the limit supporting rods is provided with a pressure sensor;
the upper end surface of the hanging basket is rotationally clamped with a force unloading ring, the force unloading ring is hollow, and a plurality of notches are distributed on the inner wall of the force unloading ring at equal intervals; a gear ring is sleeved outside the force unloading ring; the upper end face of the hanging basket is provided with a micro motor, and the output shaft of the micro motor is provided with a pinion which is meshed with the gear ring; the loading frame is rotationally clamped on the unloading ring, and a positioning block which can be in sliding clamping connection with the notch is arranged on the loading frame;
description: when the device is used, the electric push rod is utilized to push the two limit supporting rods to extend out in a rotary mode in the through groove, the hanging basket is limited and supported, then the miniature motor drives the pinion to rotate, the force unloading ring is enabled to rotate on the upper end face of the hanging basket by utilizing the meshing effect of the pinion and the gear ring, the positioning block on the loading frame is located at the notch position, the hanging basket is not subjected to the tensile force of the loading frame, and the pressure sensor is utilized to sense the pressure of the hanging basket, so that the device meets the test requirement.
Further, sliding rails are arranged on two inner walls of the guide frame, which are symmetrical inside the guide frame; the outer wall of the hanging basket is provided with a sliding sleeve which is in sliding joint with the sliding rail at the corresponding position, and a roller which is in abutting joint with the sliding rail at the corresponding position is rotationally clamped in the sliding sleeve;
description: utilize sliding sleeve and slide rail to carry out movable joint with hanging flower basket and leading truck, be favorable to improving the stability of hanging flower basket when the leading truck is inside to accuracy when vertical load applys has been improved.
Further, a sealing shell is arranged between the two annular guide rails;
description: when the landing gear runs at high speed and passes through the arresting rope simulant, the arresting rope simulant accidentally drops to cause dangerous accidents through the arrangement of the sealing shell, so that the safety of equipment is improved.
The invention also provides a carrier-based aircraft landing gear sliding cable-passing impact test method, which comprises the following steps:
s1, connecting a power supply:
the loading motor and the transmission motor are respectively connected with an external power supply;
s2, equipment adjustment:
the balancing weight is filled into the hanging basket, so that the quality of the hanging basket meets the test requirement;
s3, running equipment:
starting a transmission motor, and driving one of the rotating shafts to rotate on the bearing seat by using the transmission motor, wherein the two rotating shafts are provided with a connecting fluted disc and a steel belt connected with the connecting fluted disc, so that the two rotating shafts synchronously rotate; in the rotation process of the two steel belts, each arresting rope simulator is driven to move by the locating rod;
s4, applying a vertical load:
starting a loading motor, driving a pushing screw rod to rotate by using the loading motor, enabling a hanging basket to slide downwards along a guide frame by using the threaded connection effect of the pushing screw rod and a loading frame, pushing a test piece to move downwards in the moving process of the hanging basket, and finally enabling a landing gear to reach a set compression amount;
s5, testing dynamic load response:
when the aircraft tire impacts the arresting rope simulator, the supporting rod is stressed to trigger the hinge point force sensor, and the hinge point force sensor is used for sensing the dynamic load response of the landing gear.
Compared with the prior art, the invention has the beneficial effects that:
the test equipment provided by the invention can simulate the sliding cable passing process of the carrier-based aircraft on the carrier surface, measure the dynamic load response of the landing gear system, check the rigidity and strength of the landing gear structure and verify the sliding cable passing capability of the landing gear;
secondly, the test equipment can measure the load of the landing gear mounting hinge point of the carrier-based aircraft in the process of sliding the carrier-based aircraft over the cable, and provides test basis for the design of the mounting connection structure between the landing gear and the aircraft;
thirdly, the rigidity requirements of different arresting cable simulators can be met by adjusting the installation rigidity of the arresting cable simulators; meanwhile, the invention can study the influence of different running speeds of the landing gear and the installation heights of different blocking rope simulators on the performance of the landing gear running through the cable.
Drawings
FIG. 1 is a flow chart of a method of a slide-over cable impact test for a carrier aircraft landing gear according to embodiment 2 of the present invention;
FIG. 2 is a longitudinal cross sectional view of the carrier aircraft landing gear of the present invention sliding through cable impact test apparatus;
FIG. 3 is a front view of the carrier aircraft landing gear of the present invention sliding through cable impact test apparatus;
FIG. 4 is a schematic illustration of the attachment of a basket to a guide frame of the present invention;
FIG. 5 is a schematic illustration of the connection of the spacing assembly of the present invention to the guide frame;
FIG. 6 is a schematic illustration of the attachment of the loading bay to the basket of the present invention;
FIG. 7 is a schematic illustration of the attachment of the loading frame to the force-releasing ring of the present invention;
FIG. 8 is a schematic view of the connection of the annular rail to the spindle of the present invention;
FIG. 9 is a schematic illustration of the attachment of a stopper rope mimetic to a circular rail of the present invention;
FIG. 10 is a schematic illustration of the connection of the seal housing to the annular rail of the present invention;
FIG. 11 is a schematic illustration of the connection of the tension cable to the mounting block of the present invention;
the device comprises a 1-device bracket, a 10-supporting table, a 11-guide frame, a 12-sliding rail, a 2-vertical loading component, a 20-hanging basket, a 200-loading channel, a 201-sliding sleeve, a 21-loading frame, a 210-positioning block, a 22-loading motor, a 220-pushing screw rod, a 23-balancing weight, a 24-balancing weight box, a 25-limiting component, a 250-mounting box, a 251-electric push rod, a 252-limiting support rod, a 2520-clamping groove, a 26-unloading ring, a 260-notch, a 261-gear ring, a 27-micro motor, a 270-pinion, a 3-test piece, a 30-landing gear, a 31-aircraft tire, a 32-supporting rod, a 4-transmission component, a 40-rotating shaft, a 400-bearing seat, a 41-transmission motor, a 42-connecting fluted disc, a 420-steel belt, a 43-synchronous gear, a 430-synchronous chain, a 5-blocking cable simulator, a 50-positioning rod, a 51-annular guide rail, a 510-sliding groove, a 52-sliding block, a 53-adjusting frame, a 530-adjusting screw rod, a 531-mounting block, a 532-tensioning cable, 533-and a 54-sealing shell.
Detailed Description
Example 1: the equipment for the cable-through impact test of the landing gear sliding of the carrier-based aircraft as shown in fig. 2 comprises an equipment bracket 1, a vertical loading assembly 2 arranged at the upper end inside the equipment bracket 1, a test piece 3 arranged at the lower bottom surface of the vertical loading assembly 2, a transmission assembly 4 arranged at the inner bottom of the equipment bracket 1 and a blocking cable simulator 5 arranged on the transmission assembly 4; the equipment bracket 1 comprises a supporting table 10 and a guide frame 11 arranged on one side of the upper end surface of the supporting table 10;
as shown in fig. 2, the vertical loading assembly 2 comprises a hanging basket 20, a loading frame 21 and a loading motor 22, wherein the hanging basket 20 is in sliding clamping connection with the inside of the guide frame 11, the loading frame 21 is arranged on the upper end surface of the hanging basket 20, and the loading motor 22 is arranged on the upper end surface of the guide frame 11; the output shaft of the loading motor 22 is provided with a pushing screw 220 penetrating through the guide frame 11 and in threaded connection with the loading frame 21; the hanging basket 20 is internally filled with a balancing weight 23;
as shown in fig. 2, the test piece 3 comprises an aircraft tire 31 movably hinged to the lower bottom surface of the basket 20 through a landing gear 30 and a supporting rod 32 with two ends movably hinged to the side wall of the landing gear 30 and the lower bottom surface of the basket 20 respectively; a hinge point force sensor is arranged at the joint of the support rod 32 and the hanging basket 20;
as shown in fig. 2, 8 and 9, the transmission assembly 4 includes two rotating shafts 40 arranged in parallel on the upper end surface of the support table 10 and far from the side of the support bar 32, and a transmission motor 41 arranged on the upper end surface of the support table 10 and providing power to one of the rotating shafts 40; two ends of the two rotating shafts 40 are rotatably clamped with a bearing seat 400 fixedly connected with the supporting table 10 respectively; the two ends of the two rotating shafts 40 are respectively sleeved with a connecting fluted disc 42 positioned at the inner side of the bearing seat 400 at the corresponding position, and the two connecting fluted discs 42 positioned at the same side on the two rotating shafts 40 are connected through a steel belt 420;
as shown in fig. 2 and 8, 5 arresting cable simulators 5 are provided, and each arresting cable simulators 5 is equidistantly distributed between two steel belts 420, and each arresting cable simulators 5 is movably clamped with the two steel belts 420 through a positioning rod 50.
Example 2: the embodiment describes a method for performing a carrier aircraft landing gear sliding cable impact test by using the test device of embodiment 1, as shown in fig. 1, including the following steps:
s1, connecting a power supply:
the loading motor 22 and the transmission motor 41 are respectively connected with an external power supply;
s2, equipment adjustment:
the weight block 23 is filled into the hanging basket 20, so that the quality of the hanging basket 20 meets the test requirement;
s3, running equipment:
starting a transmission motor 41, and driving one of the rotating shafts 40 to rotate on the bearing seat 400 by using the transmission motor 41, wherein the two rotating shafts 40 are synchronously rotated due to the fact that the connecting fluted disc 42 and the steel belt 420 connected with the connecting fluted disc 42 are arranged on the two rotating shafts 40; during the rotation process of the two steel belts 420, the positioning rods 50 drive each arresting rope simulator 5 to move;
s4, applying a vertical load:
starting a loading motor 22, driving a pushing screw 220 to rotate by using the loading motor 22, enabling a hanging basket 20 to slide downwards along a guide frame 11 by using the threaded connection effect of the pushing screw 220 and a loading frame 21, pushing a test piece 3 to move downwards in the moving process of the hanging basket 20, and finally enabling a landing gear 30 to reach a set compression amount;
s5, testing dynamic load response:
when the aircraft tire 31 impacts the stopper rope simulator 5, the support rod 32 is stressed to trigger a hinge point force sensor, and the hinge point force sensor is used for sensing the dynamic load response of the landing gear 30.
Example 3: this embodiment differs from embodiment 1 in that:
as shown in fig. 3 and 4, a loading channel 200 is arranged on the side wall of the hanging basket 20, and a counterweight box 24 is arranged on the guide frame 11 corresponding to the position of the loading channel 200;
as shown in fig. 4, sliding rails 12 are arranged on two inner walls of the guide frame 11, which are symmetrical inside; the outer wall of the hanging basket 20 is provided with a sliding sleeve 201 which is in sliding joint with the sliding rail 12 at the corresponding position, and a roller which is in abutting joint with the sliding rail 12 at the corresponding position is rotationally clamped in the sliding sleeve 201.
Example 4: the present example describes a method for performing a carrier aircraft landing gear slip-over cable impact test using the test apparatus of example 3, differing from example 2 in that:
in step S2, the counterweight 23 is filled into the basket 20 through the counterweight box 24;
in step S4, the sliding sleeve 201 on the side wall of the basket 20 slides down along the sliding rail 12 on the inner wall of the guiding frame 11 by the threaded connection action of the pushing screw 220 and the loading frame 21, and the roller abuts against the sliding rail 12 and rotates.
Example 5: this embodiment differs from embodiment 3 in that:
as shown in fig. 9, the middle parts of the two rotating shafts 40 are respectively sleeved with a synchronizing gear 43, and the two synchronizing gears 43 are connected through a synchronizing chain 430.
Example 6: the present example describes a method for performing a carrier aircraft landing gear slip-over cable impact test using the test apparatus of example 5, differing from example 4 in that:
in step S3, the transmission motor 41 is turned on, and one of the rotation shafts 40 is driven to rotate on the bearing block 400 by the transmission motor 41, and the two rotation shafts 40 are synchronously rotated due to the synchronization gears 43 arranged on the two rotation shafts 40 and the synchronization chain 430 connecting the two synchronization gears 43.
Example 7: this embodiment differs from embodiment 5 in that:
as shown in fig. 8, 9, 10 and 11, annular guide rails 51 positioned outside the connecting fluted disc 42 are sleeved at two ends of the two rotating shafts 40, and the two annular guide rails 51 are fixedly connected with bearing seats 400 at corresponding positions respectively; the two annular guide rails 51 are provided with sliding grooves 510, and two ends of each arresting cable simulator 5 are provided with sliding blocks 52 which are in sliding clamping connection with the sliding grooves 510; an adjusting frame 53 is arranged on the arresting cable simulator 5, two ends of the adjusting frame 53 are rotatably clamped with adjusting screws 530, and two adjusting screws 530 are in threaded connection with an installing block 531 which is in sliding clamping connection with the inner wall of the adjusting frame 53; two ends of the arresting rope simulant 5 are respectively connected with the two mounting blocks 531 in a one-to-one correspondence manner; both ends of the arresting cable simulator 5 are provided with tensioning cables 532 penetrating through the mounting blocks 531, and the mounting blocks 531 are connected with a scroll 533 for winding the tensioning cables 532 at corresponding positions in a threaded manner; a seal housing 54 is provided between the annular rails 51.
Example 8: the present example describes a method for performing a carrier aircraft landing gear slip-over cable impact test using the test apparatus of example 7, differing from example 6 in that:
in step S3, the height of the installing block 531 at the corresponding position is adjusted by using the adjusting screws 530 at the two ends of the adjusting frame 53, so as to adjust the height of the stopper rope simulator 5; by rotating the spool 533, the stopper-rope simulator 5 is stretched by the two tension cables 532, and the rigidity of the stopper-rope simulator 5 is adjusted; in the process that the arresting cable simulator 5 and the adjusting frame 53 move along with the steel belt 420, the sliding block 52 on the lower bottom surface of the adjusting frame 53 slides in the sliding groove 510 on the annular guide rail 51.
Example 9: this embodiment differs from embodiment 7 in that:
as shown in fig. 5, 6 and 7, limiting components 25 for fixing the hanging basket 20 are arranged on two sides of the guide frame 11; the limiting assembly 25 comprises an installation box 250 arranged on the side wall of the guide frame 11, an electric push rod 251 arranged inside the installation box 250 and a limiting stay rod 252 rotatably clamped on the guide frame 11; a through groove is arranged on the side wall of the guide frame 11 and corresponds to the mounting box 250 in position; the two limit stay bars 252 are arranged, the two limit stay bars 252 are rotationally clamped in the through grooves, clamping grooves 2520 are formed in one ends, close to the mounting boxes 250, of the two limit stay bars 252, and the output ends of the electric push rods 251 are respectively in sliding clamping connection with the clamping grooves 2520 on the two limit stay bars 252; the upper end surface of one of the limit stay bars 252 is provided with a pressure sensor; the upper end surface of the hanging basket 20 is rotationally clamped with a force unloading ring 26, the force unloading ring 26 is hollow, and a plurality of notches 260 are distributed on the inner wall at equal intervals; a gear ring 261 is sleeved outside the force unloading ring 26; the upper end surface of the hanging basket 20 is provided with a micro motor 27, and the output shaft of the micro motor 27 is provided with a pinion 270 which is meshed and connected with a gear ring 261; the loading frame 21 is rotatably clamped on the unloading ring 26, and the loading frame 21 is provided with a positioning block 210 which can be slidably clamped with the notch 260.
Example 10: the present example describes a method for performing a carrier aircraft landing gear slip-over cable impact test using the test apparatus of example 9, differing from example 8 in that:
in step S2, the electric push rod 251 is utilized to push the two limit stay bars 252 to rotate and extend out of the through groove to limit and support the hanging basket 20, then the micro motor 27 is utilized to drive the pinion 270 to rotate, the meshing effect of the pinion 270 and the gear ring 261 is utilized to enable the force unloading ring 26 to rotate on the upper end face of the hanging basket 20, at this time, the positioning block 210 on the loading frame 21 is positioned at the notch 260, the hanging basket 20 is not under the tension of the loading frame 21, and the balancing weight 23 is filled into the hanging basket 20 through the balancing weight box 24; the pressure of the basket 20 is sensed by the pressure sensor so that it meets the test requirements.
It should be noted that, the loading motor 22, the electric push rod 251, the micro motor 27, the transmission motor 41, the pressure sensor and the hinge point sensor used in the present invention all adopt the prior art, and are not limited herein, and the corresponding products can be selected according to actual needs.
Claims (7)
1. The carrier-based aircraft landing gear sliding cable impact test device is characterized by comprising a device bracket (1), a vertical loading assembly (2) arranged at the upper end inside the device bracket (1), a test piece (3) arranged at the lower bottom surface of the vertical loading assembly (2), a transmission assembly (4) arranged at the inner bottom of the device bracket (1) and a blocking cable simulator (5) arranged on the transmission assembly (4); the equipment bracket (1) comprises a supporting table (10) and a guide frame (11) arranged on one side of the upper end face of the supporting table (10);
the vertical loading assembly (2) comprises a hanging basket (20) which is in sliding clamping connection with the inside of the guide frame (11), a loading frame (21) which is arranged on the upper end surface of the hanging basket (20) and a loading motor (22) which is arranged on the upper end surface of the guide frame (11); the hanging basket (20) is internally filled with a balancing weight (23); an output shaft of the loading motor (22) is provided with a pushing screw rod (220) penetrating through the guide frame (11) and in threaded connection with the loading frame (21);
the test piece (3) comprises an aircraft tire (31) movably hinged to the lower bottom surface of the hanging basket (20) through a landing gear (30) and a supporting rod (32) with two ends respectively movably hinged to the side wall of the landing gear (30) and the lower bottom surface of the hanging basket (20); a hinge point force sensor is arranged at the joint of the supporting rod (32) and the hanging basket (20);
the transmission assembly (4) comprises two rotating shafts (40) which are arranged on the upper end face of the supporting table (10) in parallel and far away from one side of the supporting rod (32), and a transmission motor (41) which is arranged on the upper end face of the supporting table (10) and provides power for one rotating shaft (40); two ends of the two rotating shafts (40) are rotatably clamped with a bearing seat (400) which is fixedly connected with the supporting table (10) respectively; the two ends of the two rotating shafts (40) are respectively sleeved with a connecting fluted disc (42) positioned at the inner side of the bearing seat (400) at the corresponding position, and the two connecting fluted discs (42) positioned at the same side on the two rotating shafts (40) are connected through a steel belt (420);
the plurality of the arresting cable simulators (5) are arranged, each arresting cable simulators (5) are equidistantly distributed between the two steel belts (420), and each arresting cable simulators (5) are movably clamped with the two steel belts (420) through positioning rods (50);
annular guide rails (51) positioned at the outer sides of the connecting fluted discs (42) are sleeved at the two ends of the two rotating shafts (40), and the two annular guide rails (51) are fixedly connected with bearing seats (400) at corresponding positions respectively; a sliding groove (510) is formed in each of the two annular guide rails (51), and sliding blocks (52) which are in sliding clamping connection with the sliding grooves (510) are arranged at two ends of each blocking rope simulator (5);
an adjusting frame (53) is arranged on the arresting cable simulator (5), adjusting screws (530) are rotatably clamped at two ends of the adjusting frame (53), and mounting blocks (531) which are slidably clamped with the inner walls of the adjusting frame (53) are connected to the two adjusting screws (530) in a threaded manner; two ends of the arresting rope simulant (5) are respectively connected with the two mounting blocks (531) in one-to-one correspondence;
both ends of the arresting cable analog (5) are provided with tensioning cables (532) penetrating through the mounting blocks (531), and the mounting blocks (531) are connected with reels (533) for winding the tensioning cables (532) at corresponding positions in a threaded manner.
2. The equipment for the impact test of the sliding cable of the landing gear of the carrier aircraft according to claim 1, wherein a loading channel (200) is arranged on the side wall of the hanging basket (20), and a counterweight box (24) is arranged on the guide frame (11) corresponding to the loading channel (200).
3. The carrier-based aircraft landing gear sliding cable impact test device according to claim 1, wherein the middle parts of the two rotating shafts (40) are respectively sleeved with a synchronous gear (43), and the two synchronous gears (43) are connected through a synchronous chain (430).
4. The equipment for the impact test of the sliding of the landing gear of the carrier aircraft through the cable according to claim 1, wherein limiting assemblies (25) for fixing the hanging basket (20) are arranged on two sides of the guide frame (11); the limiting assembly (25) comprises an installation box (250) arranged on the side wall of the guide frame (11), an electric push rod (251) arranged in the installation box (250) and a limiting stay bar (252) rotatably clamped on the guide frame (11); a through groove is formed in the side wall of the guide frame (11) at a position corresponding to the mounting box (250); the two limiting support rods (252) are rotatably clamped in the through grooves, clamping grooves (2520) are formed in one ends, close to the mounting box (250), of the two limiting support rods (252), and the output ends of the electric push rods (251) are respectively and slidably clamped with the clamping grooves (2520) on the two limiting support rods (252); the upper end surface of one limit stay bar (252) is provided with a pressure sensor;
the upper end face of the hanging basket (20) is rotationally clamped with a force unloading ring (26), the force unloading ring (26) is hollow, and a plurality of notches (260) are distributed on the inner wall of the force unloading ring at equal intervals; a gear ring (261) is sleeved outside the force unloading ring (26); the upper end face of the hanging basket (20) is provided with a micro motor (27), and the output shaft of the micro motor (27) is provided with a pinion (270) which is meshed with the gear ring (261); the loading frame (21) is rotationally clamped on the unloading ring (26), and the loading frame (21) is provided with a positioning block (210) which can be slidably clamped with the notch (260).
5. The equipment for the impact test of the landing gear sliding cable of the carrier-based aircraft according to claim 1 is characterized in that sliding rails (12) are arranged on two inner walls which are symmetrical inside the guide frame (11); the outer wall of the hanging basket (20) is provided with a sliding sleeve (201) which is in sliding joint with the sliding rail (12) at the corresponding position, and a roller which is in abutting joint with the sliding rail (12) at the corresponding position is rotationally clamped inside the sliding sleeve (201).
6. The carrier aircraft landing gear slide-over cable impact test device of claim 1, wherein a sealed enclosure (54) is provided between the two annular rails (51).
7. A method for performing a carrier aircraft landing gear slide-over cable impact test using the test apparatus of any one of claims 1-6, comprising the steps of:
s1, connecting a power supply:
the loading motor (22) and the transmission motor (41) are respectively connected with an external power supply;
s2, equipment adjustment:
the balancing weight (23) is filled into the hanging basket (20), so that the quality of the hanging basket (20) meets the test requirement;
s3, running equipment:
starting a transmission motor (41), and driving one rotating shaft (40) to rotate on a bearing seat (400) by using the transmission motor (41), wherein a connecting fluted disc (42) and a steel belt (420) connected with the connecting fluted disc (42) are arranged on both rotating shafts (40), so that the two rotating shafts (40) synchronously rotate; in the rotating process of the two steel belts (420), each arresting rope simulator (5) is driven to move by the positioning rod (50);
s4, applying a vertical load:
starting a loading motor (22), driving a pushing screw rod (220) to rotate by using the loading motor (22), enabling a hanging basket (20) to slide downwards along a guide frame (11) by using the threaded connection effect of the pushing screw rod (220) and a loading frame (21), pushing a test piece (3) to move downwards in the moving process of the hanging basket (20), and finally enabling a landing gear (30) to reach a set compression amount;
s5, testing dynamic load response:
when the aircraft tire (31) impacts the arresting rope simulator (5), the supporting rod (32) is stressed to trigger the hinge point force sensor, and the hinge point force sensor is used for sensing the dynamic load response of the landing gear (30).
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| CN117163318B (en) * | 2023-11-02 | 2024-02-02 | 中国飞机强度研究所 | Electromagnetic ejection-based aircraft landing gear running obstacle crossing impact test device and method |
| CN117622514B (en) * | 2024-01-25 | 2024-04-16 | 中国飞机强度研究所 | Device and method for simulating landing gear drop test environment of aircraft by considering high-temperature influence |
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