CN116902222B - Belt rotating device and method suitable for single-wheel double-fork landing gear drop test of airplane - Google Patents
Belt rotating device and method suitable for single-wheel double-fork landing gear drop test of airplane Download PDFInfo
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- CN116902222B CN116902222B CN202311190467.2A CN202311190467A CN116902222B CN 116902222 B CN116902222 B CN 116902222B CN 202311190467 A CN202311190467 A CN 202311190467A CN 116902222 B CN116902222 B CN 116902222B
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- 238000012360 testing method Methods 0.000 title claims abstract description 75
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- 238000006073 displacement reaction Methods 0.000 claims description 12
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- 239000007853 buffer solution Substances 0.000 description 7
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- 238000009661 fatigue test Methods 0.000 description 2
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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
Abstract
The invention discloses a rotation device and a rotation method suitable for a single-wheel double-fork landing gear drop test of an aircraft, and relates to the technical field of aviation aircraft tests. The method comprises the following steps: s1, positioning; s2, increasing the rotating speed; s3, descending contact; s4, data monitoring. The invention utilizes the transmission belt to drive the aircraft tire to rotate, can realize higher and more accurate contact speed, so that the loading of the landing test is more true and accurate, the safety of the test is improved, the rotation speed of the aircraft wheel of the landing test of the landing gear is greatly improved, the structure is reasonable and simple, and the later disassembly and inspection are convenient.
Description
Technical Field
The invention relates to the technical field of aviation aircraft tests, in particular to a rotation device and a rotation method suitable for a single-wheel double-fork landing gear drop test of an aircraft.
Background
In drop tests of aircraft landing gear, the simulation of the rotational speed of the landing gear tires generally employs friction and follow-up steering methods depending on the structural form of the landing gear. The friction type belt rotation method has the problems of insufficient belt rotation speed, large tire abrasion and the like, and meanwhile, the speed control of the tire is not accurate enough.
With the increase of carrier-based aircraft, the landing speed of the landing gear in the landing test of the landing gear is higher and higher, and the friction type belt rotation method has the defects of insufficient belt rotation speed and large tire abrasion, so that the higher test requirement cannot be met.
In the current drop test research of aviation aircraft landing gear, a plurality of students have optimized and adjusted a test device and a method for fatigue test of the landing gear, for example, patent CN216718059U discloses a landing gear fatigue test loading device, two bearing surfaces are vertically arranged on a test bed, the landing gear is arranged on the test bed in an inverted mode, a false wheel is arranged on the landing gear, and an oil injection port of the landing gear is connected with a landing gear compression amount adjusting device; patent CN112340061B discloses a loading method and loading device for landing gear hydrostatic test, which comprises a frame, a clamping assembly, a vertical loading assembly, a side loading assembly and an aeronautical loading assembly. However, through research, no one has made an optimization and improvement on the load influence relation of the landing gear drop test aiming at the rotation mode of the tire at present.
Disclosure of Invention
Aiming at the problems, the invention provides a belt rotating device and a belt rotating method suitable for a single-wheel double-fork landing gear drop test of an airplane.
The technical scheme of the invention is as follows:
the device comprises an aircraft tire, a landing gear for fixing the aircraft tire, a driving motor for driving the aircraft tire to rotate, and a force measuring platform positioned below the aircraft tire, wherein the force measuring platform is used for measuring the force of the aircraft tire;
the inner part of the aircraft tire is fixedly provided with an aircraft wheel hub, the outer parts of the two sides of the aircraft wheel hub are rotationally connected with connecting shafts, the outer part of the aircraft wheel hub is fixedly connected with a convex ring, and the outer side wall of the convex ring is provided with a circle of annular groove;
the landing gear comprises lifting rods and inverted U-shaped rods, wherein the lifting rods are fixedly connected with each other, the inverted U-shaped rods are positioned below the lifting rods, the tops of the lifting rods are fixedly clamped through hanging baskets, the tops of the hanging baskets are connected with lifting motors, and two sides of the bottoms of the inverted U-shaped rods are respectively and fixedly connected with two connecting shafts in a one-to-one correspondence manner;
the output end of the driving motor is provided with a rotating wheel, and a transmission belt which is clamped with the annular groove and used for driving the aircraft tire to rotate is arranged outside the rotating wheel;
the aircraft tire is characterized in that a fixed plate is arranged on the ground corresponding to the inner side of the aircraft tire, a first limit groove is formed in the front side wall of the fixed plate, an extension rod is arranged at the tail end of the connecting shaft and positioned on the inner side of the aircraft tire, the extension rod is connected with the first limit groove in a sliding mode, the upper section of the first limit groove is an arc section, the center of a rotating wheel of the driving motor is used as the center of a circle, the lower section of the first limit groove is a vertical section, a first spring is arranged in the bottom of the vertical section, a first baffle is arranged at the top of the first spring, a fixed block is arranged at the bottom of the driving motor, a second baffle is arranged at the rear end of the fixed block, the second baffle is connected with a second limit groove which is arranged on the front side wall of the fixed plate in a sliding mode, the bottom of the second baffle is provided with a second spring, the bottom of the second spring is fixedly connected with the bottom of the second limit groove, and the first baffle and the second baffle synchronously move.
Further, the landing gear and the force measuring platform are respectively provided with a three-way force sensor, a displacement sensor is arranged at the center of the wheel hub, the top of the inverted U-shaped rod is provided with the displacement sensor, the lifting rod is internally provided with a pressure sensor, and the outer side of the aircraft tire is provided with a high-speed camera.
Description: the data required for the experiment can be collected by the individual sensors.
Further, the top of the hanging basket is provided with a guide lock frame, the top of the guide lock frame is connected with the output end of the lifting motor through an electric control lock, and the lifting motor is fixedly connected with a fixed frame fixedly arranged on the ground.
Description: can realize the control to the undercarriage through direction lock frame and mount, guarantee the stability of whole device structure in the test process simultaneously.
Further, a connecting rod is arranged between the first baffle plate and the second baffle plate.
Description: the aircraft tire can be made to descend in an arc mode by taking the rotating wheel of the driving motor as the circle center through the fixing plate and the first limiting groove, so that the driving belt is kept to be always tight in the descending process, the driving belt is prevented from loosening and falling off, the vertical section arranged in the first limiting groove can enable the aircraft tire to descend together with the driving motor, the driving belt is prevented from loosening and falling off, and the landing contact test can be completed in the arc section or the vertical section as required.
Furthermore, a sliding block is arranged in the middle of the connecting rod, the sliding block is in sliding connection with a third limiting groove arranged on the front side wall of the fixed plate, two sides of the sliding block are respectively provided with a limiting block, and the limiting blocks are in sliding connection with sliding rails arranged on the inner side walls of the third limiting grooves.
Description: the arrangement of the third limit groove matched with the sliding block and the sliding rail enables the two baffles to be always stable, and the relative stability of the aircraft tire and the driving motor is kept in the whole test process.
Further, the radian of the arc section is 45-90 degrees, and the first baffle is located at the joint of the arc section and the vertical section of the first limiting groove.
The invention also provides a method suitable for the single-wheel double-fork landing gear drop test of the aircraft, which is based on the belt rotating device suitable for the single-wheel double-fork landing gear drop test of the aircraft, and comprises the following steps:
s1, positioning: the lifting motor is used for controlling the lifting of the hanging basket, so that the landing gear and the aircraft tire are driven to be lifted, the extension rod slides upwards in the first limit groove until the extension rod contacts the uppermost end of the arc-shaped section of the first limit groove, and positioning is completed;
s2, rotating speed increasing: starting the driving motor to drive the rotating wheel to rotate, and driving the transmission belt to rotate through the rotating wheel so as to enable the convex ring and the rotating wheel to synchronously rotate, thereby realizing the rotation of the aircraft tire;
s3, descending contact, which comprises two test working conditions:
test condition one: calculating the height between the aircraft tire and the force measuring platform after the positioning is finished, and enabling the extension rod to be positioned in the vertical section of the first limit groove when the aircraft tire is in contact with the force measuring platform, wherein the specific method comprises the following steps:
the rotating speed of the aircraft tire is kept unchanged, the lifting motor is used for controlling the hanging basket to descend, so that the landing gear and the aircraft tire are driven to descend, the extension rod slides obliquely downwards in the arc section of the first limiting groove, the circle center of the aircraft tire rotates around the circle center of the rotating wheel at equal distance, the transmission belt is kept in a tight state all the time until the extension rod contacts the first baffle and continues to press the first baffle, the aircraft tire continues to descend vertically at the moment, and meanwhile, the driving motor synchronously descends vertically to avoid the transmission belt from loosening until the aircraft tire contacts the force measuring platform;
and (2) test working condition II: the height between the aircraft tire and the force measuring platform after the positioning is finished is calculated, so that the extension rod is still positioned in the arc section of the first limit groove when the aircraft tire is in contact with the force measuring platform, and the specific method comprises the following steps:
the rotating speed of the aircraft tire is kept unchanged, the lifting motor is used for controlling the hanging basket to descend, so that the landing gear and the aircraft tire are driven to descend, the extension rod slides obliquely downwards in the arc section of the first limiting groove, the circle center of the aircraft tire rotates around the circle center of the rotating wheel at equal intervals, the transmission belt is kept in a tight state all the time, and the aircraft tire is contacted with the force measuring platform before the extension rod touches the first baffle;
s4, data monitoring: and carrying out data monitoring statistics on the stress condition of the aircraft tire, the stress condition of the landing gear and the stress condition of the force measuring platform.
Further, the rotational speed of the aircraft tire in the step S2 is 20-40 m/S, and the descent speed of the aircraft tire in the step S3 is 1-5 m/S.
Description: the aircraft tire rotating speed and the aircraft tire descending speed are optimized to enable the aircraft tire rotating speed and the aircraft tire descending speed to be closer to the real aircraft navigation condition, and the S3 descending contact is optimized to enable the aircraft tire descending contact to be selected to finish the landing contact test in an arc section or a vertical section, so that two test requirements are met.
The beneficial effects of the invention are as follows:
the belt rotating device suitable for the single-wheel double-fork landing gear drop test of the aircraft drives the aircraft tire to rotate by utilizing the transmission belt, so that higher and more accurate contact speed can be realized, the drop test loading is more real and accurate, meanwhile, compared with a friction wheel belt rotating mode, the abrasion to the tire is greatly reduced, the tire burst is avoided when the worn tire is in a high-speed contact state, the safety of the test is improved, the loss of the wheel speed from the friction wheel to the middle of landing gear throwing in the prior art is improved, the accuracy of the aircraft landing gear drop test is greatly improved, the structure is reasonable and simple, and the later-stage disassembly and inspection are convenient;
the belt rotating device suitable for the single-wheel double-fork landing gear drop test of the aircraft can enable the aircraft tire to make arc-shaped descent by taking the rotating wheel of the driving motor as the center of a circle through the arrangement of the fixed plate and the first limiting groove, so that the transmission belt is kept to be always tight in the descent process, the transmission belt is prevented from loosening and falling off, meanwhile, the vertical section arranged on the first limiting groove can enable the aircraft tire to descend together with the driving motor, the transmission belt is prevented from loosening and falling off, the landing contact test can be completed in the arc section or the vertical section according to the requirement, the two baffles are kept stable all the time through the arrangement of the third limiting groove and the sliding block, and the relative stability of the aircraft tire and the driving motor is kept in the whole test process;
the method suitable for the landing gear drop test of the single wheel double fork type landing gear of the aircraft can restore and simulate the stress condition of the landing gear when the aircraft tire falls to the ground to the maximum extent, and can finish the landing contact in an arc section or a vertical section, so that the tests of different research side points are carried out;
drawings
FIG. 1 is a side view of the overall construction of a belt steering apparatus of the present invention suitable for use in a single-wheel, double-fork landing gear drop test of an aircraft;
FIG. 2 is a schematic view of a front view of a belt steering apparatus of the present invention adapted for use in a single wheel, double fork landing gear drop test of an aircraft, with the upper portion of the lifter omitted;
FIG. 3 is a schematic view of the rear structure of the belt steering device of the present invention with the retaining plate omitted for single wheel, double fork landing gear drop test of an aircraft;
FIG. 4 is a schematic view of the structure of a fixed plate in the belt-turning device suitable for the single-wheel double-fork landing gear drop test of the aircraft;
FIG. 5 is a schematic view of the structure of the extension rod moving in the first limiting groove in the belt rotating device suitable for the single wheel double fork landing gear drop test of the aircraft;
FIG. 6 is a schematic view of the connection between the slider and the third limiting groove in the belt rotating device for the single-wheel double-fork landing gear drop test of the present invention;
FIG. 7 is a flow chart of a landing gear drop test method of the present invention for a single wheel, double fork landing gear of an aircraft.
The device comprises a 1-aircraft tire, a 11-wheel hub, a 12-connecting shaft, a 13-convex ring, a 14-annular groove, a 15-extension rod, a 2-landing gear, a 21-lifting rod, a 22-inverted U-shaped rod, a 23-hanging basket, a 24-lifting motor, a 25-guiding lock frame, a 26-electric control lock, a 27-fixing frame, a 3-driving motor, a 31-rotating wheel, a 32-driving belt, a 33-fixing block, a 4-force measuring platform, a 5-fixing plate, a 51-first limit groove, a 52-second limit groove, a 53-third limit groove, a 54-first spring, a 55-second spring, a 56-first baffle, a 57-second baffle, a 58-sliding rail, a 6-connecting rod, a 61-sliding block and a 62-limit block.
Detailed Description
Example 1: as shown in fig. 1, the rotating device suitable for the single-wheel double-fork landing gear drop test of an aircraft comprises an aircraft tire 1, a landing gear 2 for fixing the aircraft tire 1, a driving motor 3 for driving the aircraft tire 1 to rotate, and a force measuring platform 4 positioned below the aircraft tire 1;
as shown in fig. 2, a wheel hub 11 is fixedly arranged in the aircraft tire 1, connecting shafts 12 are rotatably connected to the outer parts of two sides of the wheel hub 11, a convex ring 13 is fixedly connected to the outer part of the wheel hub 11, and a circle of annular grooves 14 are formed in the outer side wall of the convex ring 13;
as shown in fig. 1, the landing gear 2 comprises a lifting rod 21 and an inverted U-shaped rod 22, wherein the lifting rod 21 and the inverted U-shaped rod 22 are fixedly connected with each other, the top of the lifting rod 21 is fixedly clamped by a hanging basket 23, the top of the hanging basket 23 is connected with a lifting motor 24, two sides of the bottom of the inverted U-shaped rod 22 are respectively and fixedly connected with two connecting shafts 12 in a one-to-one correspondence manner, the top of the hanging basket 23 is provided with a guide lock frame 25, the top of the guide lock frame 25 is connected with the output end of the lifting motor 24 through an electric control lock 26, and the lifting motor 24 is fixedly connected with a fixed frame 27 fixedly arranged on the ground;
as shown in fig. 1 and 2, the output end of the driving motor 3 is provided with a rotating wheel 31, and a transmission belt 32 which is clamped with the annular groove 14 and used for driving the aircraft tire 1 to rotate is arranged outside the rotating wheel 31;
as shown in fig. 3-6, a fixed plate 5 is arranged on the ground corresponding to the inner side of the aircraft tire 1, a first limit groove 51 is arranged on the front side wall of the fixed plate 5, an extension rod 15 is arranged at the tail end of a connecting shaft 12 positioned at the inner side of the aircraft tire 1, the extension rod 15 is in sliding clamping connection with the first limit groove 51, the upper section of the first limit groove 51 is an arc section, the arc section takes the center of a rotating wheel 31 of the driving motor 3 as a circle center, the lower section of the first limit groove 51 is a vertical section, a first spring 54 is arranged at the bottom of the vertical section, a first baffle 56 is arranged at the top of the first spring 54, the radian of the arc section is 60 degrees, the first baffle 56 is positioned at the joint of the arc section of the first limit groove 51 and the vertical section, a fixed block 33 is arranged at the bottom of the driving motor 3, a second baffle 57 is arranged at the rear end of the fixed block 33, the second baffle 57 is in sliding connection with a second limit groove 52 arranged on the front side wall of the fixed plate 5, the bottom of the second baffle 57 is provided with a second limit spring 55, the bottom of the second baffle 55 is fixedly connected with the bottom of the second limit groove 52, the first baffle 56 and the second baffle 57 are fixedly connected with the bottom of the second limit groove 52 through a limit block 53, a sliding connection rod 61 is arranged at the side wall 6, a sliding connection with the side wall 61 is arranged at the side wall of the first baffle 53 is provided with a third side wall, and a sliding stop block 61 is connected with the side wall 53 is provided with a side wall 61;
the landing gear 2 and the force measuring platform 4 are both provided with three-way force sensors, the model specification of the three-way force sensors is 9377C, the allowable error/precision grade is less than or equal to 1 percent FS, the center of the wheel hub 11 is provided with an LXU-3000III type displacement sensor, the top of the inverted U-shaped rod 22 is provided with an LXU-500III type displacement sensor, the inside of the lifting rod 21 is provided with a PA-23SY type pressure sensor, the outside of the aircraft tire 1 is provided with a micro 3 type high-speed camera, and in addition, a SIRUSe universal data collector, a Pro3600 inclinometer and an LEO2 digital pressure gauge are also needed.
Example 2: this embodiment differs from embodiment 1 in that:
the arc of the arc section of the first limiting groove 51 is 45 degrees.
Example 3: this embodiment differs from embodiment 1 in that:
the arc of the arc section of the first limiting groove 51 is 90 degrees.
Description: according to the radian of the arc section of the first limiting groove 51 is adjusted as required, the longer the radian is, the longer the movement distance of the extension rod 15 is, so that the test under the condition that the aircraft tire 1 touches a table is completed in the arc section, the shorter the radian is, the shorter the movement distance of the extension rod 15 is, and the test under the condition that the aircraft tire 1 touches a table is completed in the vertical section.
Example 4: the method for the single-wheel double-fork landing gear drop test of the aircraft is described in this embodiment, and based on the belt rotating device for the single-wheel double-fork landing gear drop test of the aircraft in embodiment 1, as shown in fig. 7, the method comprises the following steps:
s1, positioning: lifting the hanging basket 23 through the lifting motor 24, so as to drive the landing gear 2 and the aircraft tire 1 to lift, and enable the extension rod 15 to slide upwards in the first limit groove 51 until the extension rod 15 contacts the uppermost end of the arc-shaped section of the first limit groove 51, thereby completing positioning;
s2, rotating speed increasing: starting the driving motor 3 to drive the rotating wheel 31 to rotate, and driving the transmission belt 32 to rotate through the rotating wheel 31 so as to synchronously rotate the convex ring 13 and the rotating wheel 31, thereby realizing the rotation of the aircraft tire 1, wherein the rotating speed of the aircraft tire 1 is 30m/s;
s3, descending contact: the height between the aircraft tire 1 and the force measuring platform 4 after the positioning is finished is calculated, so that the extension rod 15 is positioned in the vertical section of the first limit groove 51 when the aircraft tire 1 is contacted with the force measuring platform 4, and the specific method is as follows: the rotating speed of the aircraft tire 1 is kept unchanged, the lifting motor 24 controls the hanging basket 23 to descend, so that the landing gear 2 and the aircraft tire 1 are driven to descend, the descending speed of the aircraft tire 1 is 3m/s, the extension rod 15 slides obliquely downwards in the arc section of the first limit groove 51, the circle center of the aircraft tire 1 rotates around the circle center of the rotating wheel 31 at equal intervals, the transmission belt 32 is always kept in a tight state until the extension rod 15 contacts the first baffle 56 and continues to press the first baffle 56, at the moment, the aircraft tire 1 continues to descend vertically, and meanwhile, the driving motor 3 synchronously descends to avoid the looseness of the transmission belt 32 until the aircraft tire 1 contacts the force measuring platform 4;
s4, data monitoring: and carrying out data monitoring statistics on the stress condition of the aircraft tire 1, the stress condition of the landing gear 2 and the stress condition of the force measuring platform 4.
Example 5: this embodiment differs from embodiment 4 in that:
the height between the aircraft tire 1 and the force measuring platform 4 after the positioning is finished is calculated in step S3, so that the extension rod 15 is still positioned in the arc section of the first limit groove 51 when the aircraft tire 1 is in contact with the force measuring platform 4, and the specific method is as follows:
s3, descending contact: the rotating speed of the aircraft tire 1 is kept unchanged, the lifting motor 24 controls the hanging basket 23 to descend, so that the landing gear 2 and the aircraft tire 1 are driven to descend, the extension rod 15 slides obliquely downwards in the arc section of the first limiting groove 51, the circle center of the aircraft tire 1 rotates around the circle center of the rotating wheel 31 at equal intervals, the transmission belt 32 is kept in a tight state all the time, and the aircraft tire 1 is contacted with the force measuring platform 4 before the extension rod 15 touches the first baffle 56.
Example 6: this embodiment differs from embodiment 4 in that:
the rotational speed of the aircraft tire 1 in step S2 is 20m/S, and the descent speed of the aircraft tire 1 in step S3 is 1m/S.
Example 7: this embodiment differs from embodiment 4 in that:
the rotational speed of the aircraft tire 1 in step S2 is 40m/S, and the descent speed of the aircraft tire 1 in step S3 is 5m/S.
Description: the rotating speed and the descending speed of the aircraft tire 1 can be reasonably adjusted according to the size and the actual use condition of the aircraft tire 1.
Working principle: in the following, the structure of the device according to the present invention will be further described with reference to the method according to the present invention, if the method according to embodiment 4 is selected and tested, when the aircraft tire 1 contacts the force measuring platform 4, the extension rod 15 is located in the vertical section of the first limit groove 51, and when step S3 is performed, the lifting motor 24 is used to control the lifting basket 23 to descend, and the guiding lock frame 25 is used to slide the lifting basket 23 laterally to counteract the lateral sliding generated by the first limit groove 51, so that the extension rod 15 contacts the first baffle 56 and continues to press the first baffle 56, compressing the first spring 54, and simultaneously the first baffle 56 drives the connecting rod 6 and the second baffle 57 to move downward synchronously, and the slide block 61 slides in the third limit groove 53, so that the stopper 62 slides relatively with the slide rail 58, thereby maintaining the stability of the whole structure until the aircraft tire 1 contacts the force measuring platform 4, and at this time, the stress situation when the aircraft tire 1 vertically descends to contact the force measuring platform 4 is mainly simulated.
It should be noted that: due to the arrangement of the sliding block 61 and the sliding rail 58, before the extension rod 15 contacts the first baffle 56, that is, when the first baffle 56, the second baffle 57 and the connecting rod 6 are located at the initial uppermost position, the whole of the first baffle 56, the second baffle 57 and the connecting rod 6 is kept stable under the action of the acting force of the two springs and the friction force of the limiting block 62 and the sliding rail 58.
If the method in example 5 is selected for testing, the extension rod 15 is located in the arc section of the first limiting groove 51 when the aircraft tire 1 contacts the force measuring platform 4, the arc of the arc section is 60 °, and the arc of the arc section through which the extension rod 15 slides when the aircraft tire 1 contacts the force measuring platform 4 is 50 °, so that the stress situation when the aircraft tire 1 descends obliquely downwards and contacts the force measuring platform 4 is mainly simulated.
Experimental example: the device and the method according to the invention are verified in the following according to specific tests, the aircraft model for which the aircraft tire 1 is suitable is a certain type of aircraft, the lifting rod 21 of the landing gear 2 is also a lifting rod on the landing gear of a certain type of aircraft, and the test method of each measurement item is as follows:
(1) The vertical load and the heading load on the aircraft tire 1 are measured by a three-way force sensor;
(2) The gravity center displacement (namely, the upper mass vertical displacement) of the hanging basket 23 is measured by a stay wire type displacement sensor arranged between the hanging basket 23 and the ground, and the stay wire type displacement sensor is arranged on a mounting seat on the fixing frame 27 to ensure that a stay wire is vertical to the ground;
(3) The vertical acceleration of the basket 23 is measured by an acceleration sensor installed at the center of the bottom plate of the basket 23;
(4) The tire compression is measured by a high-speed camera which is arranged on the front side surface of the center of the aircraft tire 1, and the height is that the lens of the high-speed camera is right opposite to the center of the wheel hub 11 at the moment of the contact of the aircraft tire 1.
The data processing method comprises the following steps:
buffer system absorbs work amount:
，
wherein: a, absorbing the work amount by a buffer system and kJ; p (P) y -ground vertical load kN; y is cmax Maximum value of center of gravity displacement, m.
Buffer system efficiency coefficient:
，
wherein: η—buffer system efficiency coefficient; a, absorbing the work amount by a buffer system and kJ; p (P) ycmax -maximum ground vertical load kN; y is cmax Maximum value of center of gravity displacement, m.
Coefficient of friction:
，
wherein:-coefficient of friction; />-heading load maximum, kN; />-the cranking load, i.e. the corresponding vertical load at the maximum heading load kN.
Conclusion of the test: the metering equipment and the sensor used in the landing and airworthiness verification test of the aircraft tire 1 and the landing gear 2 of a certain type of aircraft are required to be qualified through the metering technical mechanism, the test precision is better than 1% F.S in the effective service period, other test equipment is complete, and the data obtained by the test are complete and effective. The following can be concluded:
a) The landing gear 2 buffer system of a certain type of airplane can absorb energy and meet the impact load, the structural and the design requirements;
b) Providing basis for determining applicable filling parameters and design modification of the buffer system, and ensuring landing impact safety of the aircraft;
c) In the drop test, the front landing gear limits the maximum travel of the buffer support column travel of the drop test to about 178mm, which is less than 180mm;
d) In the limited drop test, the maximum ground reaction coefficient of the front landing gear limited drop test is 3.37g and is less than 3.6g;
e) After all drop tests (including reserve work tests) are completed, the prop parts are visually inspected for no visible damage;
f) In the drop test of each working condition, the maximum time of one forward and reverse stroke of the buffer support column is 0.528s and less than 1.2s;
g) After all the drop tests are finished, the landing gear 2 is free from air leakage and oil leakage.
Specific test parameters for vertical segment landing are shown in table 1:
table 1 landing gear 2 landing limit drop test data at vertical section
Specific test parameters for arc segment landing are shown in table 2:
table 2 landing gear 2 landing limit drop test data at arcuate segment
。
Claims (3)
1. The belt rotating device suitable for the single-wheel double-fork landing gear drop test of the aircraft is characterized by comprising an aircraft tire (1), a landing gear (2) for fixing the aircraft tire (1), a driving motor (3) for driving the aircraft tire (1) to rotate and a force measuring platform (4) positioned below the aircraft tire (1);
the aircraft tire (1) is characterized in that an aircraft wheel hub (11) is fixedly arranged in the aircraft tire (1), connecting shafts (12) are rotatably connected to the outer parts of two sides of the aircraft wheel hub (11), a convex ring (13) is fixedly connected to the outer part of the aircraft wheel hub (11), and a circle of annular grooves (14) are formed in the outer side wall of the convex ring (13);
the landing gear (2) comprises lifting rods (21) and inverted U-shaped rods (22) which are fixedly connected with each other, wherein the inverted U-shaped rods (22) are positioned below the lifting rods (21), the tops of the lifting rods (21) are fixedly clamped through hanging baskets (23), lifting motors (24) are connected to the tops of the hanging baskets (23), and two sides of the bottoms of the inverted U-shaped rods (22) are fixedly connected with two connecting shafts (12) in one-to-one correspondence respectively;
the output end of the driving motor (3) is provided with a rotating wheel (31), and a transmission belt (32) which is clamped with the annular groove (14) and used for driving the aircraft tire (1) to rotate is arranged outside the rotating wheel (31);
a fixed plate (5) is arranged on the ground corresponding to the inner side of the aircraft tire (1), a first limit groove (51) is formed in the front side wall of the fixed plate (5), one connecting shaft (12) positioned on the inner side of the aircraft tire (1) is provided with an extension rod (15) at the tail end, the extension rod (15) is in sliding clamping connection with the first limit groove (51), the upper section of the first limit groove (51) is an arc section, the arc section takes the center of a rotating wheel (31) of the driving motor (3) as a center, the lower section of the first limit groove (51) is a vertical section, a first spring (54) is arranged at the bottom in the vertical section, a first baffle (56) is arranged at the top of the first spring (54), a fixed block (33) is arranged at the bottom of the driving motor (3), a second baffle (57) is arranged at the rear end of the fixed block (33), the second baffle (57) is in sliding connection with a second limit groove (52) arranged on the front side wall of the fixed plate (5), the second baffle (57) is provided with a second spring (55), and the second spring (55) is connected with the second spring (55) and the second baffle (55) in a moving mode;
the landing gear (2) and the force measuring platform (4) are respectively provided with a three-way force sensor, a displacement sensor is arranged at the center of the wheel hub (11), a displacement sensor is arranged at the top of the inverted U-shaped rod (22), a pressure sensor is arranged in the lifting rod (21), and a high-speed camera is arranged at the outer side of the aircraft tire (1);
the top of the hanging basket (23) is provided with a guide lock frame (25), the top of the guide lock frame (25) is connected with the output end of the lifting motor (24) through an electric control lock (26), and the lifting motor (24) is fixedly connected with a fixed frame (27) fixedly arranged on the ground;
be equipped with connecting rod (6) between first baffle (56) and second baffle (57), connecting rod (6) middle part is equipped with slider (61), slider (61) with third spacing groove (53) sliding connection that are equipped with on the preceding lateral wall of fixed plate (5), the both sides of slider (61) respectively are equipped with stopper (62), stopper (62) with slide rail (58) sliding connection that third spacing groove (53) inside wall was equipped with, the radian of arc section is 45~90, first baffle (56) are located the junction of arc section and perpendicular section of first spacing groove (51).
2. The method suitable for the single-wheel double-fork landing gear drop test of the aircraft is based on the belt rotating device suitable for the single-wheel double-fork landing gear drop test of the aircraft as claimed in claim 1, and is characterized by comprising the following steps:
s1, positioning: lifting of the hanging basket (23) is controlled through the lifting motor (24), so that the landing gear (2) and the aircraft tire (1) are driven to lift, the extension rod (15) slides upwards in the first limit groove (51) until the extension rod (15) contacts the uppermost end of the arc-shaped section of the first limit groove (51), and positioning is completed;
s2, rotating speed increasing: starting a driving motor (3) to drive a rotating wheel (31) to rotate, and driving a transmission belt (32) to rotate through the rotating wheel (31) so as to synchronously rotate a convex ring (13) and the rotating wheel (31), thereby realizing the rotation of an aircraft tire (1);
s3, descending contact, which comprises two test working conditions:
test condition one: the height between the aircraft tire (1) and the force measuring platform (4) after the positioning is finished is calculated, so that the extension rod (15) is positioned in the vertical section of the first limit groove (51) when the aircraft tire (1) is in contact with the force measuring platform (4), and the specific method is as follows:
the rotating speed of the aircraft tire (1) is kept unchanged, the lifting motor (24) is used for controlling the hanging basket (23) to descend, so that the landing gear (2) and the aircraft tire (1) are driven to descend, the extension rod (15) slides obliquely downwards in the arc section of the first limit groove (51), the circle center of the aircraft tire (1) rotates around the circle center of the rotating wheel (31) at equal intervals, the driving belt (32) is kept in a tight state all the time until the extension rod (15) contacts the first baffle (56) and continuously presses the first baffle (56), the aircraft tire (1) continuously descends vertically at the moment, and meanwhile, the driving motor (3) synchronously descends vertically to avoid the loosening of the driving belt (32) until the aircraft tire (1) contacts the force measuring platform (4);
and (2) test working condition II: after the positioning is finished, calculating the height between the aircraft tire (1) and the force measuring platform (4), and enabling the extension rod (15) to be still positioned in the arc section of the first limit groove (51) when the aircraft tire (1) is in contact with the force measuring platform (4), wherein the specific method comprises the following steps:
the rotating speed of the aircraft tire (1) is kept unchanged, the lifting motor (24) is used for controlling the hanging basket (23) to descend, so that the landing gear (2) and the aircraft tire (1) are driven to descend, the extension rod (15) slides obliquely downwards in the arc section of the first limit groove (51), the circle center of the aircraft tire (1) rotates around the circle center of the rotating wheel (31) at equal intervals, the transmission belt (32) is kept in a tight state all the time, and the aircraft tire (1) is contacted with the force measuring platform (4) before the extension rod (15) touches the first baffle (56);
s4, data monitoring: and carrying out data monitoring statistics on the stress condition of the aircraft tire (1), the stress condition of the landing gear (2) and the stress condition of the force measuring platform (4).
3. The method for the single-wheel double-fork landing gear drop test of the aircraft according to claim 2, wherein the rotation speed of the aircraft tire (1) in the step S2 is 20-40 m/S, and the descent speed of the aircraft tire (1) in the step S3 is 1-5 m/S.
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| CN117141742B (en) * | 2023-10-23 | 2024-01-26 | 中国飞机强度研究所 | Device and method for measuring vertical rigidity of aviation aircraft tire |
| CN117141744B (en) * | 2023-10-31 | 2024-01-30 | 中国飞机强度研究所 | Dual-wheel landing gear course speed simulation test device in full-aircraft drop test |
| CN117184445B (en) * | 2023-11-08 | 2024-01-30 | 中国飞机强度研究所 | Model parameter equivalent correction method for aircraft tire rigidity test |
| CN117465691B (en) * | 2023-12-28 | 2024-03-08 | 中国飞机强度研究所 | Aircraft landing gear drop test device and method considering high temperature influence |
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