CN112829928A - Support mechanism for landing of aircraft and use method thereof - Google Patents
Support mechanism for landing of aircraft and use method thereof Download PDFInfo
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- CN112829928A CN112829928A CN202110030428.0A CN202110030428A CN112829928A CN 112829928 A CN112829928 A CN 112829928A CN 202110030428 A CN202110030428 A CN 202110030428A CN 112829928 A CN112829928 A CN 112829928A
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- buffering
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a support mechanism for landing of an aircraft and a use method thereof, wherein the support mechanism comprises a mounting base plate, a rotary motor is arranged, a gear is used for meshing transmission to drive a rotary sleeve to rotate, the distance between supporting legs is adjusted, the density distribution is adjusted, the density of the supporting legs arranged on one side with large mass distribution is large, the density of the supporting legs arranged on one side with small mass distribution is small, the aircraft is effectively supported, and the phenomenon that the stress of individual supporting legs is too large is prevented; through setting up the double-rod pneumatic cylinder, utilize the double-rod pneumatic cylinder to drive first movable block and second movable block simultaneous movement, make the supporting leg interval grow of opposite flank to make the area of landing increase, utilize simultaneously to adjust the motor and drive the motion of adjusting the slider, and then the angle of adjusting the adjusting link, make the aircraft gesture become vertical state, avoid the aircraft slope to appear, lead to focus unstability or working state not good, improved user's comfortable degree simultaneously.
Description
Technical Field
The invention relates to a supporting mechanism, in particular to a supporting mechanism for landing of an aircraft and a using method thereof.
Background
With the development of the aerospace industry, various types of aircraft have been developed, which are composed of a plurality of precision modular components, wherein the support structures used when the aircraft is landed play a crucial role in the safe and stable landing of the aircraft.
The supporting structure in the prior art only focuses on strengthening treatment and shock absorption treatment of structural strength, cannot be adjusted according to the environment condition of a temporary landing place, is limited in use scene and lacks flexibility, and therefore, a supporting mechanism for landing of an aircraft and a use method thereof are provided.
Disclosure of Invention
The invention aims to provide a support mechanism for landing of an aircraft and a use method thereof, wherein a rotary motor is arranged, and a gear is used for meshing transmission to drive a rotary sleeve to rotate, so that the distance between supporting legs is adjusted and the density distribution is adjusted, the density of the supporting legs arranged on one side with large mass distribution is large, the density of the supporting legs arranged on one side with small mass distribution is small, the aircraft is effectively supported, and the influence on the service life and the strength of the supporting legs due to the overlarge stress of individual supporting legs is prevented; the double-rod hydraulic cylinder is arranged, the first movable block and the second movable block are driven by the double-rod hydraulic cylinder to move simultaneously, so that the distance between the supporting legs on the opposite side surfaces is increased, the landing area is increased, the adjusting motor is used for driving the adjusting slide block to move, the angle of the adjusting connecting rod is adjusted, the aircraft posture is changed into a vertical state, the aircraft is prevented from inclining, the gravity center is unstable or the working state is poor, and the comfort degree of a user is improved; through set up the multiunit spring respectively in vertical direction and horizontal direction, carry out multistage shock attenuation to the impact force when the aircraft lands, reduce the hard impact of aircraft, protected the overall structure stability of aircraft, improved the security performance of aircraft.
The technical problem solved by the invention is as follows:
(1) how to adjust the distance between the supporting legs and the density distribution by arranging a rotating motor and utilizing gear meshing transmission to drive a rotating sleeve to rotate so that the supporting legs arranged on one side with large mass distribution have large density and the supporting legs arranged on one side with small mass distribution have small density, and the problem that a supporting structure in the prior art cannot adjust the mass distribution of an aircraft is solved;
(2) how to increase the distance between the supporting legs on the opposite side surfaces by arranging the double-rod hydraulic cylinder and driving the first movable block and the second movable block to move simultaneously by using the double-rod hydraulic cylinder so as to increase the landing area, and simultaneously driving the adjusting slide block to move by using the adjusting motor so as to adjust the angle of the adjusting connecting rod, so that the attitude of the aircraft is changed into a vertical state, and the problem that the attitude of the aircraft cannot be adjusted by using a supporting structure in the prior art is solved;
(3) how to carry out multistage shock attenuation to the impact force when the aircraft lands through set up the multiunit spring respectively in vertical direction and horizontal direction, reduce the hard impact of aircraft, protected the overall structure stability of aircraft, strike great problem when solving among the prior art aircraft lands.
The purpose of the invention can be realized by the following technical scheme: a supporting mechanism for landing of an aircraft comprises a mounting base plate, a first fixed block, a first movable block, a second movable block, a double-rod hydraulic cylinder, a rotating motor, a first gear, a second gear, a supporting column, a rotating sleeve, a supporting leg, a reinforcing sleeve, a reinforcing connecting rod, a limiting block, a reinforcing spring, a supporting seat, a damping box body, an adjusting connecting rod, an adjusting slider, an adjusting motor, a driving gear, a buffering base plate, a buffering connecting rod, a buffering slider, a buffering spring, a buffering guide shaft, a first buffering column, a first compression spring, a buffering mounting strip, a connecting top plate, a displacement guide column, a buffering mounting block, a second buffering column and a second compression spring, wherein the first fixed block is symmetrically connected to four sides of the bottom of the mounting base plate in a sliding mode, the first movable block and the second movable block are arranged at two ends of the first fixed block respectively, and are connected to the first fixed block in a sliding mode, the first movable block and the second movable block which are arranged on the four sides of the bottom of the mounting substrate and are adjacent are connected end to enclose a closed structure;
a double-rod hydraulic cylinder is fixedly arranged in the middle of the inner side of the first fixed block, two ends of the double-rod hydraulic cylinder are respectively and fixedly connected with one end of the first movable block and one end of the second movable block, the ends of the first movable block and the second movable block far away from the double-rod hydraulic cylinder are both provided with motor mounting grooves, a rotating motor is fixedly arranged in the motor mounting groove, the end part of an output shaft of the rotating motor is fixedly connected with a first gear, a second gear is also arranged in the motor mounting groove and is meshed and connected with the first gear through gear teeth, the bottoms of the second movable block and the first movable block are both provided with a support column, the second gear is fixedly connected with the support column, the bottom of the supporting column is coaxially provided with a rotating sleeve which is fixedly connected with the supporting column, one side of the rotating sleeve is provided with a supporting leg which is fixedly connected with the rotating sleeve;
be provided with the shock attenuation box directly over the mounting substrate, two regulation spouts have been seted up to the bottom of shock attenuation box, the symmetry is provided with adjusting slide block in the regulation spout, adjusting slide block and regulation spout sliding fit, the motor mounting hole has been seted up at adjusting slide block's top, fixed mounting has adjusting motor in the motor mounting hole, adjusting motor's output shaft tip fixedly connected with driving gear, the top of adjusting the spout link up and is provided with the rack mounting groove, fixed mounting has the rack on the lateral wall of rack mounting groove, the driving gear is connected with rack toothing.
The invention has further technical improvements that: one side of supporting leg is provided with the intensive sleeve, set up in the intensive sleeve and reinforce the spout, the symmetry is provided with the intensive connecting rod in the intensive spout, the one end fixedly connected with stopper of intensive connecting rod setting in the intensive spout, the one end that the stopper was kept away from to the intensive connecting rod is rotated with the supporting leg and is connected, stopper and intensive sleeve sliding connection, two be provided with the intensive spring between the stopper, the both ends of intensive spring respectively with the side fixed connection of two stoppers, the supporting leg is kept away from the one end fixedly connected with supporting legs of rotatory sleeve.
The invention has further technical improvements that: the two adjusting sliding grooves are arranged in a cross-shaped crossed mode, and the transverse section of each adjusting sliding groove is of a T-shaped structure.
The invention has further technical improvements that: the mounting structure is characterized in that two supporting seats are symmetrically arranged on four sides of the top of the mounting substrate, the supporting seats are fixedly connected with the top of the mounting substrate, one ends of adjusting connecting rods are connected to the supporting seats in a rotating mode, and the other ends of the adjusting connecting rods are connected with adjusting sliding blocks in a rotating mode.
The invention has further technical improvements that: the damping box comprises a damping box body, and is characterized in that a buffering groove is formed in the top of the damping box body, a buffering substrate is fixedly connected to the bottom of the buffering groove, a connecting top plate is arranged right above the buffering substrate, the connecting top plate is in sliding fit with the buffering groove, displacement guide pillars are symmetrically fixed to the bottom of the connecting top plate, a buffering mounting strip is arranged right below the connecting top plate, the two displacement guide pillars penetrate through two ends of the buffering mounting strip and are in sliding connection with the buffering mounting strip, buffering mounting blocks are symmetrically arranged on the outer sides of the buffering mounting strip, the buffering mounting blocks are both in sliding connection with the buffering mounting strip, two buffering connecting rods are symmetrically arranged on two sides of the buffering mounting block and are both in rotating connection with the buffering mounting blocks;
the buffer base plate side has been seted up a plurality of horizontal dashpot, all be provided with buffering slider and buffering guide shaft in the horizontal dashpot, the both ends of buffering guide shaft run through buffering slider and respectively with the both sides wall fixed connection of horizontal dashpot, buffering slider and buffering guide shaft sliding connection, the outside of buffering guide shaft is provided with buffer spring, buffer spring's both ends respectively with the cell wall of horizontal dashpot and the side looks butt of buffering slider, the one end that buffering installation piece was kept away from to the buffering connecting rod rotates with buffering slider and is connected.
The invention has further technical improvements that: the utility model discloses a buffer base plate, including buffer base plate, a plurality of first dashpot, the concrete figure of first dashpot is unanimous with the concrete figure of buffering connecting rod, the bar groove has been seted up to the side of buffering connecting rod, the bar inslot rolls and is connected with the roll round pin, one side of rolling the round pin is provided with first buffering post, rolls the round pin and rotates with first buffering post to be connected, the one end setting of first buffering post is in first dashpot, first buffering post and first dashpot sliding fit, be provided with first compression spring in the first dashpot, the one end of first compression spring and the bottom fixed connection of first buffering post, the other end and the buffer base plate fixed connection of first compression spring.
The invention has further technical improvements that: the second dashpot has been seted up at the top of buffering installation piece, be provided with second compression spring in the second dashpot, second compression spring's one end and buffering installation piece fixed connection, second compression spring's other end fixedly connected with second dashpot, the one end setting of second dashpot just second dashpot and second dashpot sliding fit in the second dashpot, the one end that second compression spring was kept away from to the second dashpot and the bottom fixed connection of being connected the roof, the top fixedly connected with of connecting the roof.
The using method specifically comprises the following steps:
the method comprises the following steps: when the aircraft needs to land, the positions of the plurality of supporting legs are adjusted according to the mass distribution of the aircraft, the rotating motor is started, the end part of the output shaft of the rotating motor rotates to drive the first gear to rotate, so that the second gear is driven to rotate through gear tooth meshing transmission, the rotating sleeve rotates for a certain angle, and the distance between the supporting legs on the side with large mass distribution is reduced;
step two: when the ground is low in flatness, the double-rod hydraulic cylinder is started, so that the hydraulic rods at the two ends of the double-rod hydraulic cylinder extend out simultaneously to drive the first movable block and the second movable block to slide towards the direction far away from the first fixed block, the landing area is increased, the aircraft posture can incline due to uneven ground, at the moment, the adjusting motor at the side with low horizontal height is started, the end part of an output shaft of the adjusting motor rotates to drive the driving gear to rotate, the adjusting slider is driven to slide in the adjusting chute through meshing transmission of the driving gear and the adjusting motor, the adjusting connecting rod is driven to change the angle, and the aircraft posture is adjusted to be in a vertical state;
step three: when the aircraft landed, under gravity and impact force effect, it makes the second cushion post form the extrusion to second compression spring to connect roof downstream simultaneously, thereby drive buffering installation piece downstream, the angle increase between the buffering connecting rod of setting in buffering installation piece both sides, and promote the buffering slider and slide in horizontal dashpot, form the extrusion to buffer spring, make buffer spring take place elastic deformation, the bar inslot rolls round pin and takes place relative roll with buffering connecting rod simultaneously, and drive first cushion post downstream and form the extrusion to first compression spring, make first compression spring take place elastic deformation, what the multiunit spring accomplished from horizontal and vertical direction and cushion the shock attenuation to the aircraft.
Compared with the prior art, the invention has the beneficial effects that:
1. when the invention is used, when the aircraft needs to land, according to the mass distribution of the aircraft, the positions of a plurality of supporting legs are adjusted, a rotating motor is started, the end part of an output shaft of the rotating motor rotates to drive a first gear to rotate, so that a second gear is driven to rotate through gear tooth meshing transmission, further rotating the rotary sleeve by a certain angle to reduce the space between the supporting legs on the side with large mass distribution, driving the rotary sleeve to rotate by the gear meshing transmission through arranging the rotary motor, the distance between the supporting legs is adjusted and the density distribution is adjusted, so that the supporting legs arranged at the side with large mass distribution have large density, the supporting legs arranged at the side with small mass distribution have small density, the aircraft is effectively supported, and the influence on the service life and strength of the supporting legs due to overlarge stress of individual supporting legs is prevented;
2. when the ground planeness of the landing is low, the double-rod hydraulic cylinder is started, the hydraulic rods at the two ends of the double-rod hydraulic cylinder extend out simultaneously to drive the first movable block and the second movable block to slide towards the direction far away from the first fixed block, so that the landing area is increased, the landing is backward, the posture of the aircraft can incline due to the uneven ground, at the moment, the adjusting motor at the side with low horizontal height is started, the end part of the output shaft of the adjusting motor rotates to drive the driving gear to rotate, the adjusting sliding block is driven to slide in the adjusting sliding groove through the meshing transmission of the driving gear and the adjusting motor, so that the angle change of the adjusting connecting rod is driven to adjust the posture of the aircraft to a vertical state, the double-rod hydraulic cylinder is arranged to drive the first movable block and the second movable block to move simultaneously, the distance between the supporting legs at the opposite sides is increased, and the, meanwhile, the adjusting motor is utilized to drive the adjusting slide block to move, so that the angle of the adjusting connecting rod is adjusted, the attitude of the aircraft is changed into a vertical state, the aircraft is prevented from inclining, the gravity center is not stable or the working state is not good, and the comfort degree of a user is improved;
3. when the aircraft lands, under the action of gravity and impact force, the connecting top plate moves downwards and simultaneously enables the second buffer column to extrude the second compression spring, so as to drive the buffer mounting block to move downwards, the angle between the buffer connecting rods arranged at two sides of the buffer mounting block is increased, the buffer sliding block is pushed to slide in the transverse buffer groove, the buffer spring is extruded, the buffer spring is elastically deformed, meanwhile, the rolling pin in the strip-shaped groove and the buffer connecting rod roll relatively, the first buffer column is driven to move downwards to extrude the first compression spring, the first compression spring is elastically deformed, the multiple groups of springs finish the buffer damping of the aircraft from the transverse direction and the vertical direction, the multiple groups of springs are respectively arranged in the vertical direction and the horizontal direction, the impact force when the aircraft lands is subjected to multi-stage damping, and the hard impact of the aircraft is reduced, the integral structure stability of the aircraft is protected, and the safety performance of the aircraft is improved.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic overall perspective view of the present invention;
FIG. 2 is a schematic view of a reinforcing structure of the support leg of the present invention;
FIG. 3 is a schematic view of an angle adjustment structure of the support leg of the present invention;
FIG. 4 is a schematic view of the internal structure of the damping box of the present invention.
In the figure: 1. a mounting substrate; 2. a first fixed block; 3. a first movable block; 4. a second movable block; 5. a double-rod hydraulic cylinder; 6. a rotating electric machine; 7. a first gear; 8. a second gear; 9. a support pillar; 10. rotating the sleeve; 11. supporting legs; 12. reinforcing the sleeve; 13. reinforcing the connecting rod; 14. a limiting block; 15. a reinforcing spring; 16. a supporting seat; 17. a damping box body; 18. adjusting the connecting rod; 19. adjusting the sliding block; 20. adjusting the motor; 21. a driving gear; 22. a buffer substrate; 23. a buffer connecting rod; 24. a buffer slide block; 25. a buffer spring; 26. a buffer guide shaft; 27. a first buffer column; 28. a first compression spring; 29. buffering the mounting bar; 30. connecting the top plate; 31. a displacement guide post; 32. a buffer mounting block; 33. a second buffer column; 34. a second compression spring.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, a support mechanism for landing an aircraft includes a mounting substrate 1, a first fixed block 2, a first movable block 3, a second movable block 4, a dual-rod hydraulic cylinder 5, a rotating motor 6, a first gear 7, a second gear 8, a support pillar 9, a rotating sleeve 10, a support leg 11, a reinforcing sleeve 12, a reinforcing link 13, a limit block 14, a reinforcing spring 15, a support seat 16, a damping box 17, an adjusting link 18, an adjusting slider 19, an adjusting motor 20, a driving gear 21, a buffer substrate 22, a buffer link 23, a buffer slider 24, a buffer spring 25, a buffer guide shaft 26, a first buffer column 27, a first compression spring 28, a buffer mounting bar 29, a connecting top plate 30, a displacement guide column 31, a buffer mounting block 32, a second buffer column 33 and a second compression spring 34, four sides of the bottom of the mounting substrate 1 are symmetrically connected with the first fixed block 2 in a sliding manner, a first movable block 3 and a second movable block 4 are respectively arranged at two ends of the first fixed block 2, the first movable block 3 and the second movable block 4 are both connected with the first fixed block 2 in a sliding manner, and the adjacent first movable block 3 and the second movable block 4 which are arranged on four sides of the bottom of the mounting substrate 1 are connected end to form a closed structure;
the middle part of the inner side of the first fixed block 2 is fixedly provided with a double-rod hydraulic cylinder 5, the two ends of the double-rod hydraulic cylinder 5 are respectively fixedly connected with one end of a first movable block 3 and one end of a second movable block 4, one ends of the first movable block 3 and the second movable block 4, which are far away from the double-rod hydraulic cylinder 5, are respectively provided with a motor mounting groove, a rotating motor 6 is fixedly arranged in the motor mounting groove, the end part of an output shaft of the rotating motor 6 is fixedly connected with a first gear 7, a second gear 8 is also arranged in the motor mounting groove, the second gear 8 is connected with the first gear 7 through gear tooth meshing, the bottoms of the second movable block 4 and the first movable block 3 are respectively provided with a support column 9, the second gear 8 is fixedly connected with the support column 9, the bottom of the support column 9 is coaxially provided with a rotating sleeve 10, and the rotating sleeve 10 is fixedly, one side of the rotating sleeve 10 is provided with a supporting leg 11, and the supporting leg 11 is fixedly connected with the rotating sleeve 10;
be provided with the shock attenuation box 17 directly over mounting substrate 1, two regulation spouts have been seted up to the bottom of shock attenuation box 17, the symmetry is provided with adjusting slide 19 in the regulation spout, adjusting slide 19 and regulation spout sliding fit, the motor mounting hole has been seted up at adjusting slide 19's top, fixed mounting has adjusting motor 20 in the motor mounting hole, adjusting motor 20's output shaft tip fixedly connected with driving gear 21, the top of adjusting the spout link up and is provided with the rack mounting groove, fixed mounting has the rack on the lateral wall of rack mounting groove, driving gear 21 is connected with rack toothing.
One side of supporting leg 11 is provided with reinforceing sleeve 12, it has reinforceed the spout to have seted up in the reinforcement sleeve 12, the symmetry is provided with reinforceed connecting rod 13 in the reinforceing spout, the one end fixedly connected with stopper 14 of reinforceing the connecting rod 13 setting in reinforceing the spout, the one end that reinforceing connecting rod 13 kept away from stopper 14 rotates with supporting leg 11 to be connected, stopper 14 and reinforcement sleeve 12 sliding connection, two be provided with between the stopper 14 and reinforce spring 15, reinforce spring 15's both ends respectively with two stopper 14's side fixed connection, the one end fixedly connected with supporting legs of rotatory sleeve 10 are kept away from to supporting leg 11.
The two adjusting sliding grooves are arranged in a cross-shaped crossed mode, and the transverse section of each adjusting sliding groove is of a T-shaped structure.
The top four sides of mounting substrate 1 all the symmetry be provided with two supporting seats 16, supporting seat 16 all with mounting substrate 1's top fixed connection, supporting seat 16 rotates and is connected with the one end of adjusting connecting rod 18, the other end of adjusting connecting rod 18 all rotates with adjusting slider 19 and is connected.
The damping box body 17 is provided with a buffer groove at the top, the bottom of the buffer groove is fixedly connected with a buffer base plate 22, a connecting top plate 30 is arranged right above the buffer base plate 22, the connecting top plate 30 is in sliding fit with the buffer groove, the bottom of the connecting top plate 30 is symmetrically fixed with displacement guide pillars 31, a buffer mounting bar 29 is arranged right below the connecting top plate 30, the two displacement guide pillars 31 penetrate through the two ends of the buffer mounting bar 29, the displacement guide pillars 31 are in sliding connection with the buffer mounting bar 29, the outer sides of the buffer mounting bar 29 are symmetrically provided with buffer mounting blocks 32, the buffer mounting blocks 32 are both in sliding connection with the buffer mounting bar 29, the two buffer connecting rods 23 are both symmetrically arranged on the two sides of the buffer mounting block 32, and the buffer connecting rods 23 are both rotationally connected with the buffer mounting blocks 32;
a plurality of horizontal dashpot has been seted up to buffering base plate 22 side, all be provided with buffering slider 24 and buffering guide shaft 26 in the horizontal dashpot, buffering slider 24 and the both ends of buffering guide shaft 26 run through buffering slider 24 and respectively with the both sides wall fixed connection of horizontal dashpot, buffering slider 24 and buffering guide shaft 26 sliding connection, the outside of buffering guide shaft 26 is provided with buffer spring 25, buffer spring 25's both ends respectively with the cell wall of horizontal dashpot and the side looks butt of buffering slider 24, the one end that buffering installation piece 32 was kept away from to buffering connecting rod 23 rotates with buffering slider 24 to be connected.
The utility model discloses a buffer base plate 22, including buffer base plate 22, bar groove, first buffer slot, rolling pin, first buffer slot's the concrete figure is unanimous with buffer connecting rod 23's the concrete figure, buffer connecting rod 23's side has been seted up the bar groove, the bar inslot rolls and is connected with the rolling pin, one side of rolling the pin is provided with first cushion column 27, rolls the pin and rotates with first cushion column 27 to be connected, the one end setting of first cushion column 27 is in first buffer slot, first cushion column 27 and first buffer slot sliding fit, be provided with first compression spring 28 in the first buffer slot, the one end of first compression spring 28 and the bottom fixed connection of first cushion column 27, the other end and the buffer base plate 22 fixed connection of first compression spring 28.
The second dashpot has been seted up at the top of buffering installation piece 32, be provided with second compression spring 34 in the second dashpot, second compression spring 34's one end and buffering installation piece 32 fixed connection, second compression spring 34's other end fixedly connected with second cushion column 33, the one end setting of second cushion column 33 is in the second dashpot and second cushion column 33 and second dashpot sliding fit, and second cushion column 33 keeps away from the one end of second compression spring 34 and the bottom fixed connection who is connected roof 30, the top fixedly connected with 35 of connecting roof 30.
The using method specifically comprises the following steps:
the method comprises the following steps: when the aircraft needs to land, the positions of the plurality of supporting legs 11 are adjusted according to the mass distribution of the aircraft, the rotating motor 6 is started, the end part of the output shaft of the rotating motor 6 rotates to drive the first gear 7 to rotate, so that the second gear 8 is driven to rotate through gear tooth meshing transmission, the rotating sleeve 10 is further rotated by a certain angle, and the distance between the supporting legs 11 on the side with large mass distribution is reduced;
step two: when the planeness of the landed ground is low, the double-rod hydraulic cylinder 5 is started, the hydraulic rods at two ends of the double-rod hydraulic cylinder 5 extend out simultaneously to drive the first movable block 3 and the second movable block 4 to slide in the direction away from the first fixed block 2, so that the landed area is increased, the landing area is lagged, the attitude of the aircraft can incline due to the uneven ground, at the moment, the adjusting motor 20 at the side with low horizontal height is started, the end part of an output shaft of the adjusting motor 20 rotates to drive the driving gear 21 to rotate, and the adjusting slide block 19 is driven to slide in the adjusting chute through the meshing transmission of the driving gear 21 and the adjusting motor 20, so that the adjusting connecting rod 18 is driven to change the angle, and the attitude of the aircraft is adjusted to be in;
step three: when the aircraft lands, under gravity and impact force effect, connect roof 30 downstream and make second cushion post 33 form the extrusion to second compression spring 34 simultaneously, thereby drive buffering installation piece 32 downstream, the angle increase between the buffering connecting rod 23 of setting at buffering installation piece 32 both sides, and promote buffering slider 24 and slide in horizontal dashpot, form the extrusion to buffer spring 25, make buffer spring 25 take place elastic deformation, the roll round pin in the bar inslot takes place relative roll with buffering connecting rod 23 simultaneously, and drive first cushion post 27 downstream and form the extrusion to first compression spring 28, make first compression spring 28 take place elastic deformation, what multiunit spring accomplished the shock attenuation of buffering to the aircraft from horizontal and vertical direction.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation and a specific orientation configuration and operation, and thus, should not be construed as limiting the present invention. Furthermore, "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate member, or they may be connected through two or more elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
While one embodiment of the present invention has been described in detail, the description is only a preferred embodiment of the present invention and should not be taken as limiting the scope of the invention. All equivalent changes and modifications made within the scope of the present invention shall fall within the scope of the present invention.
Claims (8)
1. A support mechanism for aircraft landing, characterized by: the mounting structure comprises a mounting substrate (1) and a first fixed block (2), wherein four sides of the bottom of the mounting substrate (1) are symmetrically connected with the first fixed block (2) in a sliding manner, two ends of the first fixed block (2) are respectively provided with a first movable block (3) and a second movable block (4), the first movable block (3) and the second movable block (4) are both connected with the first fixed block (2) in a sliding manner, and the first movable block (3) and the second movable block (4) which are adjacent to each other and arranged on four sides of the bottom of the mounting substrate (1) are connected end to form a closed structure;
the double-rod hydraulic cylinder (5) is fixedly arranged in the middle of the inner side of the first fixed block (2), two ends of the double-rod hydraulic cylinder (5) are fixedly connected with one end of the first movable block (3) and one end of the second movable block (4) respectively, a motor mounting groove is formed in one end, far away from the double-rod hydraulic cylinder (5), of the first movable block (3) and the second movable block (4), a rotating motor (6) is fixedly arranged in the motor mounting groove, a first gear (7) is fixedly connected to the end portion of an output shaft of the rotating motor (6), a second gear (8) is further arranged in the motor mounting groove, the second gear (8) is connected with the first gear (7) through gear tooth meshing, supporting columns (9) are arranged at the bottoms of the second movable block (4) and the first movable block (3), and the second gear (8) is fixedly connected with the supporting columns (9), a rotating sleeve (10) is coaxially arranged at the bottom of the supporting column (9), the rotating sleeve (10) is fixedly connected with the supporting column (9), a supporting leg (11) is arranged on one side of the rotating sleeve (10), and the supporting leg (11) is fixedly connected with the rotating sleeve (10);
be provided with directly over mounting substrate (1) shock attenuation box (17), two regulation spouts have been seted up to the bottom of shock attenuation box (17), the symmetry is provided with adjusting block (19) in the regulation spout, adjusting block (19) and regulation spout sliding fit, the motor mounting hole has been seted up at adjusting block's (19) top, fixed mounting has adjusting motor (20) in the motor mounting hole, the output shaft end fixedly connected with driving gear (21) of adjusting motor (20), the top of adjusting the spout link up and is provided with the rack mounting groove, fixed mounting has the rack on the lateral wall of rack mounting groove, driving gear (21) are connected with rack toothing.
2. A support mechanism for aircraft landing according to claim 1, one side of the supporting leg (11) is provided with a reinforced sleeve (12), a reinforced sliding groove is arranged in the reinforced sleeve (12), the strengthening sliding chute is internally and symmetrically provided with strengthening connecting rods (13), one end of each strengthening connecting rod (13) arranged in the strengthening sliding chute is fixedly connected with a limiting block (14), one end of the reinforced connecting rod (13) far away from the limiting block (14) is rotatably connected with the supporting leg (11), the limiting blocks (14) are connected with the reinforced sleeve (12) in a sliding way, a reinforced spring (15) is arranged between the two limiting blocks (14), two ends of the reinforced spring (15) are respectively fixedly connected with the side surfaces of the two limit blocks (14), one end of the supporting leg (11) far away from the rotating sleeve (10) is fixedly connected with a supporting leg.
3. A support mechanism for landing an aircraft according to claim 1, wherein said two adjustment runners are arranged crosswise in a cross, the transverse cross-section of said adjustment runners being of a T-shaped configuration.
4. The supporting mechanism for landing of aircraft according to claim 1, wherein two supporting seats (16) are symmetrically arranged on each of four sides of the top of the mounting base plate (1), the supporting seats (16) are fixedly connected with the top of the mounting base plate (1), one end of an adjusting connecting rod (18) is rotatably connected to each supporting seat (16), and the other end of each adjusting connecting rod (18) is rotatably connected to an adjusting sliding block (19).
5. The supporting mechanism for landing of an aircraft according to claim 1, wherein a buffer slot is formed at the top of the damping box body (17), a buffer base plate (22) is fixedly connected to the bottom of the buffer slot, a connecting top plate (30) is arranged right above the buffer base plate (22), the connecting top plate (30) is in sliding fit with the buffer slot, displacement guide pillars (31) are symmetrically fixed at the bottom of the connecting top plate (30), a buffer mounting bar (29) is arranged right below the connecting top plate (30), two displacement guide pillars (31) penetrate through two ends of the buffer mounting bar (29), the displacement guide pillars (31) are in sliding connection with the buffer mounting bar (29), buffer mounting blocks (32) are symmetrically arranged on the outer side of the buffer mounting bar (29), and the buffer mounting blocks (32) are both in sliding connection with the buffer mounting bar (29), two sides of the buffer mounting block (32) are symmetrically provided with two buffer connecting rods (23), and the buffer connecting rods (23) are rotatably connected with the buffer mounting block (32);
buffer substrate (22) side has seted up the horizontal buffer tank of a plurality of, all be provided with buffering slider (24) and buffering guide shaft (26) in the horizontal buffer tank, the both ends of buffering guide shaft (26) run through buffering slider (24) and respectively with the both sides wall fixed connection of horizontal buffer tank, buffering slider (24) and buffering guide shaft (26) sliding connection, the outside of buffering guide shaft (26) is provided with buffer spring (25), the both ends of buffer spring (25) respectively with the cell wall of horizontal buffer tank and the side looks butt of buffering slider (24), the one end that buffering installation piece (32) was kept away from in buffering connecting rod (23) rotates with buffering slider (24) and is connected.
6. A support mechanism for aircraft landing according to claim 5, the top of the buffer base plate (22) is provided with a plurality of first buffer grooves, the specific number of the first buffer grooves is consistent with the specific number of the buffer connecting rods (23), a strip-shaped groove is arranged on the side surface of the buffer connecting rod (23), a rolling pin is connected in the strip-shaped groove in a rolling way, one side of the rolling pin is provided with a first buffer column (27), the rolling pin is rotationally connected with the first buffer column (27), one end of the first buffer column (27) is arranged in the first buffer groove, the first buffer column (27) is in sliding fit with the first buffer groove, a first compression spring (28) is arranged in the first buffer groove, one end of the first compression spring (28) is fixedly connected with the bottom of the first buffer column (27), and the other end of the first compression spring (28) is fixedly connected with the buffer base plate (22).
7. The supporting mechanism for landing of the aircraft as claimed in claim 5, wherein a second buffer slot is formed in the top of the buffer mounting block (32), a second compression spring (34) is arranged in the second buffer slot, one end of the second compression spring (34) is fixedly connected with the buffer mounting block (32), a second buffer column (33) is fixedly connected to the other end of the second compression spring (34), one end of the second buffer column (33) is arranged in the second buffer slot, the second buffer column (33) is in sliding fit with the second buffer slot, one end, far away from the second compression spring (34), of the second buffer column is fixedly connected with the bottom of the connecting top plate (30), and the top of the connecting top plate (30) is fixedly connected with the second buffer column (35).
8. Use of a support mechanism for landing an aircraft, characterized in that it comprises in particular the following steps:
the method comprises the following steps: when the aircraft needs to land, the positions of the plurality of supporting legs (11) are adjusted according to the mass distribution of the aircraft, the rotating motor (6) is started, the end part of the output shaft of the rotating motor (6) rotates to drive the first gear (7) to rotate, so that the second gear (8) is driven to rotate through gear tooth meshing transmission, the rotating sleeve (10) rotates for a certain angle, and the distance between the supporting legs (11) on the side with large mass distribution is reduced;
step two: when the ground is low in flatness, the double-rod hydraulic cylinder (5) is started, hydraulic rods at two ends of the double-rod hydraulic cylinder (5) extend out simultaneously to drive the first movable block (3) and the second movable block (4) to slide towards the direction far away from the first fixed block (2), so that the landing area is increased, the aircraft falls behind, the attitude of the aircraft can incline due to uneven ground, at the moment, the adjusting motor (20) at one side with low horizontal height is started, the output shaft end part of the adjusting motor (20) rotates to drive the driving gear (21) to rotate, the adjusting slide block (19) is driven to slide in the adjusting chute through meshing transmission of the driving gear (21) and the adjusting motor (20), so that the adjusting connecting rod (18) is driven to change the angle, and the attitude of the aircraft is adjusted to be in a vertical state;
step three: when the aircraft landed, under gravity and impact force effect, connect roof (30) downstream and make second cushion post (33) form the extrusion to second compression spring (34) simultaneously, thereby drive buffering installation piece (32) downstream, the angle increase between buffering connecting rod (23) of setting in buffering installation piece (32) both sides, and promote buffering slider (24) and slide in horizontal dashpot, form the extrusion to buffer spring (25), make buffer spring (25) take place elastic deformation, the roll round pin in the bar inslot takes place relative roll with buffering connecting rod (23) simultaneously, and drive first cushion post (27) downstream and form the extrusion to first compression spring (28), make first compression spring (28) take place elastic deformation, the shock attenuation is cushioned to the aircraft from horizontal and vertical direction completion of multiunit spring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110030428.0A CN112829928A (en) | 2021-01-07 | 2021-01-07 | Support mechanism for landing of aircraft and use method thereof |
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