CN118790471B - A foldable main landing gear system for an electric vertical take-off and landing aircraft - Google Patents
A foldable main landing gear system for an electric vertical take-off and landing aircraft Download PDFInfo
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- CN118790471B CN118790471B CN202411281204.7A CN202411281204A CN118790471B CN 118790471 B CN118790471 B CN 118790471B CN 202411281204 A CN202411281204 A CN 202411281204A CN 118790471 B CN118790471 B CN 118790471B
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- 238000009434 installation Methods 0.000 description 19
- 238000012423 maintenance Methods 0.000 description 12
- 230000006378 damage Effects 0.000 description 8
- 208000027418 Wounds and injury Diseases 0.000 description 4
- 208000014674 injury Diseases 0.000 description 4
- 238000007689 inspection Methods 0.000 description 4
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- 238000011900 installation process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 2
- 230000008713 feedback mechanism Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000003578 releasing effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000005283 ground state Effects 0.000 description 1
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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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Abstract
本发明涉及电动垂直起降飞行器的主起落架技术领域，且公开了一种电动垂直起降飞行器的可折叠主起落架系统，主起落架组件底部一侧设有驱动轮；机身左右两侧均设有主起落架组件和驱动轮折叠后放置的放置槽；主起落架组件一侧设有连接组件，连接组件一侧设有提示组件，机身表面安装有位于连接组件一侧的盖板，盖板用于对连接组件和提示组件进行遮挡，通过电动推杆推动第一支撑杆、第二支撑杆和第一角片和第二角片的转动，使得主起落架组件能够迅速展开，驱动轮接触地面，在地面行驶模式下，展开的驱动轮提供了更好的稳定性和支撑力，通过当电动垂直起降飞行器进入飞行状态时，主起落架组件能够迅速且平稳地折叠并收入机身内部。
The invention relates to the technical field of main landing gear of an electric vertical take-off and landing aircraft, and discloses a foldable main landing gear system of an electric vertical take-off and landing aircraft, wherein a driving wheel is arranged on one side of the bottom of the main landing gear assembly; placement grooves for placing the main landing gear assembly and the driving wheel after folding are arranged on both the left and right sides of a fuselage; a connecting assembly is arranged on one side of the main landing gear assembly, a prompting assembly is arranged on one side of the connecting assembly, a cover plate located on one side of the connecting assembly is installed on the surface of the fuselage, the cover plate is used to shield the connecting assembly and the prompting assembly, and the main landing gear assembly can be quickly unfolded by pushing the first support rod, the second support rod and the first corner piece and the second corner piece to rotate through an electric push rod, so that the driving wheel contacts the ground, and in a ground driving mode, the unfolded driving wheel provides better stability and supporting force, and when the electric vertical take-off and landing aircraft enters a flight state, the main landing gear assembly can be quickly and smoothly folded and stored inside the fuselage.
Description
Technical Field
The invention relates to the technical field of main landing gears of electric vertical take-off and landing aircrafts, in particular to a foldable main landing gear system of an electric vertical take-off and landing aircrafts.
Background
The electric vertical take-off and landing aircraft is more popular and understood to be an electric aircraft which can take off and land vertically without a runway, and compared with the traditional helicopter, the manned electric vertical take-off and landing aircraft is purely electric in driving, low in noise, high in cost performance and more environment-friendly.
With the growing demand of low-altitude economy and social life, the electric vertical take-off and landing aircraft has become an important research object of the future urban air traffic industry, and the landing gear of the electric vertical take-off and landing aircraft comprises various configurations, mainly comprising a skid type landing gear, a fixed turbine type landing gear and the like, wherein the skid type landing gear is fixed with a fuselage, the aircraft cannot freely move in a ground stop state, the fixed turbine type landing gear can be used for realizing the movement of the aircraft in the ground state, but the landing gear cannot be fixed in the air, great air resistance can be brought, and the flight efficiency of the aircraft is reduced.
Disclosure of Invention
The present invention aims to provide a foldable main landing gear system for an electric vertical take-off and landing aircraft, which solves the problems set forth in the background art.
In order to achieve the above purpose, the present invention provides the following technical solutions: a foldable main landing gear system of an electric vertical take-off and landing aircraft, comprising a main landing gear assembly and a fuselage, wherein one side of the bottom of the main landing gear assembly is provided with a driving wheel;
the left side and the right side of the machine body are respectively provided with a main landing gear assembly and a placing groove for placing the folded driving wheels;
one side of the main landing gear component is provided with a connecting component, one side of the connecting component is provided with a prompting component, the surface of the machine body is provided with a cover plate positioned at one side of the connecting component, and the cover plate is used for shielding the connecting component and the prompting component;
the main landing gear assembly comprises a mounting plate connecting frame, first supporting rods are hinged to two sides of the bottom of the connecting frame, and an electric push rod is hinged to the bottom of the connecting frame;
a first corner piece is fixed on one side of the bottom of the first supporting rod, a second corner piece is hinged to the bottom of the first corner piece, and a second supporting rod is fixed at the bottom of the second corner piece;
A limiting frame is fixed on the outer side of the mounting plate through a bolt, and a supporting frame hinged to the bottom of the second supporting rod is fixed on one side of the limiting frame through a bolt;
and a rotating shaft which is rotationally connected to one side of the machine body is inserted into one side of the limiting frame.
Preferably, the axle center of the driving wheel is connected with an axle, the bottom of the mounting plate is connected with a bottom plate through a bolt, the outer side of the axle is inserted into the inner sides of the mounting plate and the bottom plate, and the push rod end of the electric push rod is hinged to one side of the first support rod.
Preferably, when the push rod end of the electric push rod is retracted to the shortest, the hinge point between the first corner piece and the second corner piece is folded and rotated, so that the mounting plate drives the driving wheel to be stored inside the placing groove around the rotating shaft;
When the push rod end of the electric push rod extends out to the longest, the first support rod and the second support rod are coaxial, the mounting plate and the driving wheel rotate around the rotating shaft, and the mounting plate and the driving wheel are in an unfolding state.
Preferably, the connecting assembly comprises a first fixing frame and a second fixing frame, wherein a plurality of limiting grooves are formed in the bottom of the second fixing frame, a plurality of limiting blocks inserted into the inner sides of the limiting grooves are fixed at the top of the first fixing frame, and locking grooves are formed in one side of each limiting block.
Preferably, a second sliding groove is formed in the second fixing frame, a plurality of first sliding grooves are formed in the inner wall of the second sliding groove, and locking rods inserted into the locking grooves slide on the inner sides of the first sliding grooves.
Preferably, the inner side of the second sliding groove is slidably connected with a sliding rod, one side of the top of the locking rod is fixed on one side of the bottom of the sliding rod, and a spring is connected between one side of the locking rod and the inner side of the first sliding groove.
Preferably, the outer side of the second fixing frame is fixed on the inner side wall of the placing groove, and the bottom of the first fixing frame is fixed on the top of the connecting frame;
when the lock rod is inserted into the lock groove, the first fixing frame and the second fixing frame are in a connection state, and when the lock rod is not inserted into the lock groove, the first fixing frame and the second fixing frame are in a separation state.
Preferably, the prompting assembly comprises a plurality of sliding plates, wherein the bottoms of two sides of the sliding plates are respectively fixed with a bump and a sliding column, the bottoms of the sliding columns are fixed with a pushing plate, and the surfaces of the pushing plates are provided with through holes.
Preferably, a third sliding groove is formed in the inner wall of the limiting groove, and the outer side of the sliding plate is connected to the inner side of the third sliding groove in a sliding manner;
The second fixing frame is internally provided with a plurality of fourth sliding grooves, the bottom of the inner wall of each fourth sliding groove is fixedly provided with a switch positioned at the lower side of the push plate, the outer side of each switch is sleeved with a tension spring, and two ends of each tension spring are respectively connected to the inner side walls of the push plate and the fourth sliding grooves.
Preferably, a plurality of indicator lamps are mounted on one side of the second fixing frame, a storage battery is mounted on one side of the second fixing frame, the output end of the storage battery is electrically connected to the input end of the switch, and the output end of the switch is electrically connected to the input end of the indicator lamps;
When the push plate leaves the switch contact to enable the indicator lamp to be extinguished, the limiting block is mounted on the inner wall side of the limiting groove, and when the push plate abuts against the switch contact to enable the indicator lamp to be on, the limiting block is not mounted on the inner wall side of the limiting groove.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
The first support rod, the second support rod and the first corner piece and the second corner piece are pushed to rotate by the electric push rod, so that the main landing gear assembly can be rapidly unfolded, the driving wheels contact the ground, and the unfolded driving wheels provide better stability and supporting force in a ground running mode.
Through when the electric vertical take-off and landing aircraft enters a flight state, the main landing gear assembly can be rapidly and stably folded and retracted into the fuselage, the windward area of the electric vertical take-off and landing aircraft in the air is remarkably reduced, and therefore the flight resistance is reduced, in the flight process, the main landing gear assembly is folded and retracted into the fuselage, the risk that the main landing gear assembly becomes an obstacle in flight or is impacted by the outside can be avoided, and through the foldable main landing gear assembly, the electric vertical take-off and landing aircraft can optimize the overall structural layout of the electric vertical take-off and landing aircraft on the premise that the ground travelling capacity is not sacrificed, so that the electric vertical take-off and landing aircraft can more compactly and more efficiently utilize the space.
The lock rod is unlocked by intuitively pushing the slide rod to operate, so that maintenance personnel can complete disassembly without special skills or knowledge, maintenance difficulty is reduced, more maintenance personnel can be enabled to be qualified for the operation, flexibility and reliability of maintenance are improved, stable operation of disassembly is ensured by unlocking the lock rod and compressing the spring in the disassembly process, risks of accidental damage or injury caused by improper operation are reduced, and the main landing gear assembly is easily disassembled, so that the maintenance personnel can more easily perform comprehensive inspection and cleaning on the main landing gear assembly, and necessary replacement is facilitated, potential problems can be found and solved in time, small problems are prevented from being evolved into big problems, and safety and reliability of the aircraft are ensured.
The main landing gear assembly can be installed through simple sliding rod pushing and releasing actions, the installation steps are greatly simplified, the installation efficiency is improved, the accurate positioning of the main landing gear assembly in the installation process is ensured by the limiting block and the limiting groove, the main landing gear assembly can be ensured to be installed at the correct position by aligning the limiting block to the inner side of the limiting groove, the installation problem caused by position deviation is avoided, and the installation efficiency is improved.
Through inserting the spacing groove and touching the lug when the stopper, can trigger a series of mechanical actions, finally lead to the extinction or the extinction of pilot lamp, instant feedback mechanism lets the staff know installation progress and state rapidly, need not to carry out extra inspection or measurement, through the cooperation of stopper and spacing groove, and the promotion of lug to slide and push pedal, can ensure that main undercarriage subassembly is installed the assigned position accurately, the extinction of pilot lamp provides audio-visual signal for the staff, make the installation more convenient, help reducing because of the repeated dismantlement and the installation work that the improper lead to of installation.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the main landing gear assembly of the present invention in an extended configuration;
FIG. 2 is a schematic view of the main landing gear assembly retraction fuselage structure of the present invention;
FIG. 3 is a schematic view of the main landing gear assembly of the present invention;
FIG. 4 is a schematic view of the structure of the driving wheel of the present invention;
FIG. 5 is a schematic view of the structure of the support frame of the present invention;
FIG. 6 is a schematic view of the first gusset and the second gusset of the present invention;
FIG. 7 is a schematic view of a front cross-sectional structure of a second fixing frame according to the present invention;
FIG. 8 is a schematic view of the structure of the area A in FIG. 7 according to the present invention;
FIG. 9 is a schematic perspective view of a slide bar according to the present invention;
fig. 10 is a schematic perspective view of a skateboard according to the present invention.
Reference numerals illustrate: 1. a main landing gear assembly; 101. a mounting plate; 102. a connecting frame; 103. an electric push rod; 104. a first support bar; 105. a first gusset; 106. a second gusset; 107. a second support bar; 108. a bottom plate; 109. a rotating shaft; 110. a support frame; 111. a limiting frame; 2. a driving wheel; 3. a body; 4. a placement groove; 5. a cover plate; 6. a connection assembly; 601. a first fixing frame; 602. a limiting block; 603. a locking groove; 604. a slide bar; 605. the second fixing frame; 606. a first chute; 607. a second chute; 608. a spring; 609. a lock lever; 610. a limit groove; 7. a prompting component; 701. a bump; 702. a third chute; 703. an indicator light; 704. a slide plate; 705. a spool; 706. a push plate; 707. a tension spring; 708. a switch; 709. a fourth chute; 710. a through hole; 8. and a storage battery.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for the purpose of understanding and reading the disclosure, and are not intended to limit the scope of the application, which is defined by the claims, but rather by the claims, unless otherwise indicated, and that any structural modifications, proportional changes, or dimensional adjustments, which would otherwise be apparent to those skilled in the art, would be made without departing from the spirit and scope of the application.
Examples
Referring to fig. 1-10, the present invention provides a technical solution: a foldable main landing gear system of an electric vertical take-off and landing aircraft comprises a main landing gear assembly 1 and a main body 3, wherein one side of the bottom of the main landing gear assembly 1 is provided with a driving wheel 2, and a hub motor is arranged in the driving wheel 2; the left side and the right side of the machine body 3 are respectively provided with a main landing gear component 1 and a placing groove 4 which is placed after the driving wheel 2 is folded;
A connecting component 6 is arranged on one side of the main landing gear component 1, a prompting component 7 is arranged on one side of the connecting component 6, a cover plate 5 positioned on one side of the connecting component 6 is arranged on the surface of the main body 3, and the cover plate 5 is used for shielding the connecting component 6 and the prompting component 7;
In order to make more compact and more efficient use of space of the electric vertical take-off and landing aircraft, the electric vertical take-off and landing aircraft is provided with a main landing gear assembly 1, the main landing gear assembly 1 comprises a mounting plate 101 and a connecting frame 102, both sides of the bottom of the connecting frame 102 are hinged with a first supporting rod 104, the bottom of the connecting frame 102 is hinged with an electric push rod 103, one side of the bottom of the first supporting rod 104 is fixed with a first corner piece 105, the bottom of the first corner piece 105 is hinged with a second corner piece 106, the bottom of the second corner piece 106 is fixed with a second supporting rod 107, and the push rod end of the electric push rod 103 extends out to a mechanical dead point, so that the first supporting rod 104 and the second supporting rod 107 can be automatically locked;
The outside of the mounting plate 101 is fixed with a limit frame 111 through a bolt, one side of the limit frame 111 is fixed with a support frame 110 hinged to the bottom of the second support rod 107 through a bolt, one side of the limit frame 111 is inserted with a rotating shaft 109 rotatably connected to one side of the machine body 3, and the driving wheel 2 is driven to rotate around the rotating shaft 109, so that the driving wheel 2 can be retracted or put down.
The axle center of the driving wheel 2 is connected with an axle, the bottom of the mounting plate 101 is connected with a bottom plate 108 through a bolt, the outer side of the axle is inserted into the inner sides of the mounting plate 101 and the bottom plate 108, the push rod end of the electric push rod 103 is hinged to one side of the first support rod 104, the mounting plate 101 and the driving wheel 2 on one side of the main landing gear assembly 1 are in an unfolding state, and the driving wheel 2 can drive the electric vertical take-off and landing aircraft to run on a road surface;
When the push rod end of the electric push rod 103 is retracted to the shortest, the hinge point between the first corner piece 105 and the second corner piece 106 is folded and rotated, so that the mounting plate 101 drives the driving wheel 2 to be stored inside the placing groove 4 around the rotating shaft 109, the mounting plate 101 and the driving wheel 2 on one side of the main landing gear assembly 1 are rotated to the inside of the placing groove 4, and the main landing gear assembly 1 can be folded and retracted into the body 3 when the electric vertical take-off and landing aircraft flies, and the flying resistance is reduced;
when the push rod end of the electric push rod 103 extends to the longest, the first support rod 104 and the second support rod 107 are coaxial, the mounting plate 101 and the driving wheel 2 rotate around the rotating shaft 109, the mounting plate 101 and the driving wheel 2 are in a unfolded state, the mounting plate 101 and the driving wheel 2 on one side of the main landing gear assembly 1 are in a unfolded state, and the driving wheel 2 can drive the electric vertical take-off and landing aircraft to run on the road.
In order to facilitate maintenance of the main landing gear assembly 1, a connecting assembly 6 is arranged, the connecting assembly 6 comprises a first fixing frame 601 and a second fixing frame 605, a plurality of limiting grooves 610 are formed in the bottom of the second fixing frame 605, a plurality of limiting blocks 602 inserted into the limiting grooves 610 are fixed at the top of the first fixing frame 601, locking grooves 603 are formed in one side of the limiting blocks 602, second sliding grooves 607 are formed in the second fixing frame 605, a plurality of first sliding grooves 606 are formed in the inner wall of each second sliding groove 607, sliding rods 604 are pushed to one side, at the moment, the sliding rods 604 push a plurality of locking rods 609 to slide on the inner sides of the first sliding grooves 606, locking rods 609 inserted into the inner sides of the locking grooves 603 slide on the inner sides of the first sliding grooves 606, the locking rods 609 compress springs 608, and the locking rods 609 leave the inner sides of the locking grooves 603.
The inner side of the second sliding groove 607 is connected with a sliding rod 604 in a sliding way, one side of the top of the locking rod 609 is fixed on one side of the bottom of the sliding rod 604, a spring 608 is connected between one side of the locking rod 609 and the inner side of the first sliding groove 606, the unlocking of the locking rod 609 and the compression of the spring 608 ensure the stable disassembly action, the risk of accidental damage or injury caused by improper operation is reduced, the outer side of the second fixing frame 605 is fixed on the inner side wall of the placing groove 4, and the bottom of the first fixing frame 601 is fixed on the top of the connecting frame 102;
when the lock rod 609 is inserted into the lock groove 603, the first fixing frame 601 and the second fixing frame 605 are in a connection state, the limiting block 602 is aligned to the inner side of the limiting groove 610, so that the main landing gear assembly 1 can be ensured to be installed at a correct position, the installation problem caused by position deviation is avoided, and the installation step is greatly simplified; when the locking lever 609 is not inserted into the inside of the locking groove 603, the first fixing frame 601 and the second fixing frame 605 are in a separated state, the unlocking of the locking lever 609 and the compression of the spring 608 ensure the smooth proceeding of the disassembling action, and the risk of accidental damage or injury caused by improper operation is reduced.
In order to facilitate prompt whether the main landing gear assembly 1 is accurately mounted at a designated position, a prompt assembly 7 is arranged, the prompt assembly 7 comprises a plurality of sliding plates 704, the bottoms of two sides of the sliding plates 704 are respectively fixed with a convex block 701 and a sliding column 705, when a limiting block 602 touches the bottoms of the convex blocks 701, the convex blocks 701 push the sliding plates 704 to slide inside the third sliding grooves 702, a push plate 706 is fixed at the bottoms of the sliding columns 705, through holes 710 are formed in the surfaces of the push plates 706, the through holes 710 enable the air pressures of two sides of the push plates 706 to be consistent, the inner walls of the limiting grooves 610 are provided with the third sliding grooves 702, limiting sliding rods are fixed on the inner walls of the third sliding grooves 702 and movably penetrate through one side of the sliding plates 704, and the outer sides of the sliding plates 704 are slidably connected to the inner sides of the third sliding grooves 702;
A plurality of fourth sliding grooves 709 are formed in the second fixing frame 605, a switch 708 positioned on the lower side of the pushing plate 706 is fixed at the bottom of the inner wall of the fourth sliding groove 709, the sliding plate 704 drives the sliding column 705 to move upwards, when the pushing plate 706 slides upwards on the inner side of the fourth sliding groove 709, the pushing plate 706 leaves a contact of the switch 708, the indicator lamp 703 is extinguished, a tension spring 707 is sleeved on the outer side of the switch 708, two ends of the tension spring 707 are respectively connected to the pushing plate 706 and the inner side wall of the fourth sliding groove 709, and the tension spring 707 enables the pushing plate 706 to recover to an original position for the next prompt.
A plurality of indicator lamps 703 are arranged on one side of the second fixing frame 605, a storage battery 8 is arranged on one side of the second fixing frame 605, the storage battery 8 is a rechargeable battery, the output end of the storage battery 8 is electrically connected with the input end of the switch 708, the output end of the switch 708 is electrically connected with the input end of the indicator lamps 703, and when the limiting block 602 is inserted into the top of the inner wall of the limiting groove 610, the indicator lamps 703 are turned on;
When push pedal 706 leaves the switch 708 contact and makes pilot lamp 703 extinguish, stopper 602 installs the inner wall side of spacing groove 610, when push pedal 706 contradicts the switch 708 contact and makes pilot lamp 703 light up, stopper 602 does not install the inner wall side of spacing groove 610, the cooperation of stopper 602 and spacing groove 610 to and the promotion of lug 701 to slide 704 and push pedal 706 can ensure that main landing gear subassembly 1 is installed the assigned position accurately, the light up and the light out of pilot lamp 703 provides audio-visual signal for the staff, makes the installation more convenient.
Working principle: when the electric vertical take-off and landing aircraft is on the ground, the push rod end of the electric push rod 103 extends to the longest end, the electric push rod 103 pushes the first support rod 104 to rotate around the hinge point, then the first corner piece 105 and the second corner piece 106 rotate around the hinge point, the first support rod 104 and the second support rod 107 rotate in a following way, the first support rod 104 and the second support rod 107 are coaxial, the first support rod 104 and the second support rod 107 push the support frame 110, the limit frame 111 and the limit frame 111 to rotate around the rotating shaft 109, the mounting plate 101 and the driving wheel 2 on one side of the main landing gear assembly 1 are in an unfolding state, and the electric vertical take-off and landing aircraft can be driven to run on a road surface through the driving wheel 2;
When the electric vertical take-off and landing aircraft is in flight, the push rod end of the electric push rod 103 is retracted, the electric push rod 103 is mechanically locked, the push rod end drives the first support rod 104 to rotate inwards, the first corner piece 105 and the second corner piece 106 rotate around the hinge point separately, then the second support rod 107 drives the support frame 110 and the limiting frame 111 to rotate around the rotating shaft 109, the mounting plate 101 and the driving wheel 2 on one side of the main landing gear assembly 1 rotate to the inner side of the placing groove 4, and the main landing gear assembly 1 can be folded into the fuselage 3 when the electric vertical take-off and landing aircraft flies, so that the flight resistance is reduced;
when the main landing gear assembly 1 needs to be maintained, only the cover plate 5 needs to be opened at the moment, then the sliding rod 604 is pushed to one side, at the moment, the sliding rod 604 pushes the plurality of locking rods 609 to slide on the inner side of the first sliding groove 606, so that the locking rods 609 compress the springs 608, the locking rods 609 leave the inner side of the locking grooves 603, at the moment, the first fixing frame 601 is pulled downwards, and at the moment, the main landing gear assembly 1 needing to be maintained can be conveniently detached;
When the main landing gear assembly 1 after maintenance is required to be installed, the plurality of limiting blocks 602 are aligned to the inner side of the limiting groove 610, then the sliding rod 604 is pushed to one side, so that the locking rod 609 is positioned at the inner side of the first sliding groove 606, then the pushing force of the pushing sliding rod 604 is released, at the moment, the locking rod 609 slides on one side of the limiting block 602 under the pushing force of the spring 608, when the locking rod 609 slides to one side of the locking groove 603, at the moment, the locking rod 609 is inserted into the inner side of the limiting groove 610 under the elastic force of the spring 608, and at the moment, the installation of the main landing gear assembly 1 is completed;
When the limiting block 602 is inserted into the inner side of the limiting groove 610, when the limiting block 602 touches the bottom of the protruding block 701, the protruding block 701 pushes the sliding plate 704 to slide into the inner side of the third sliding groove 702, at this time, the sliding plate 704 drives the sliding column 705 and the pushing plate 706 to move upwards, when the pushing plate 706 slides into the inner side of the fourth sliding groove 709, at this time, the pushing plate 706 leaves the contact of the switch 708, at this time, the indicator lamp 703 is extinguished, a worker can know that the limiting block 602 has been inserted into the top of the inner wall of the limiting groove 610, and when the limiting block 602 has been inserted into the top of the inner wall of the limiting groove 610, the indicator lamp 703 is lighted.
In summary, the rotation of the first support bar 104, the second support bar 107, the first corner piece 105 and the second corner piece 106 is pushed by the electric push bar 103, so that the main landing gear assembly 1 can be rapidly unfolded, the driving wheel 2 contacts the ground, and the unfolded driving wheel 2 provides better stability and supporting force in the ground running mode.
By folding and taking in the main landing gear assembly 1 into the fuselage 3 during the flight, the risk of being an obstacle in flight or being impacted by the outside can be avoided, and by the foldable main landing gear assembly 1, the electric vertical take-off and landing aircraft can optimize its overall structural layout without sacrificing ground travelling capacity, so that the electric vertical take-off and landing aircraft can utilize space more compactly and more efficiently;
The lock rod 609 is unlocked by intuitively pushing the slide rod 604 to operate, so that maintenance personnel can complete the disassembly work without special skill or knowledge, the maintenance difficulty is reduced, more maintenance personnel can be qualified for the work, the flexibility and reliability of maintenance are improved, in the disassembly process, the smooth proceeding of the disassembly action is ensured by the unlocking of the lock rod 609 and the compression of the spring 608, the risk of accidental damage or injury caused by improper operation is reduced, the main landing gear assembly 1 is easily disassembled, the maintenance personnel can more easily perform comprehensive inspection and cleaning, and necessary replacement is facilitated, potential problems can be timely found and solved, the small problems are prevented from being evolved into big problems, and the safety and reliability of an aircraft are ensured;
The main landing gear assembly 1 can be installed through simple pushing and releasing actions of the sliding rod 604, so that the installation steps are greatly simplified, the installation efficiency is improved, the limiting block 602 and the limiting groove 610 ensure the accurate positioning of the main landing gear assembly 1 in the installation process, the limiting block 602 is aligned to the inner side of the limiting groove 610, the main landing gear assembly 1 can be ensured to be installed in the correct position, the installation problem caused by position deviation is avoided, and the installation efficiency is improved;
When the limiting block 602 is inserted into the limiting groove 610 and touches the protruding block 701, a series of mechanical actions can be triggered, and finally, the indicator lamp 703 is turned off or turned on, so that an immediate feedback mechanism enables a worker to quickly know the installation progress and state without additional inspection or measurement, the main landing gear assembly 1 can be ensured to be accurately installed at a designated position through the cooperation of the limiting block 602 and the limiting groove 610 and the pushing of the protruding block 701 to the sliding plate 704 and the pushing plate 706, visual signals are provided for the worker through the turning on and off of the indicator lamp 703, the installation process is more convenient, and repeated disassembly and installation work caused by improper installation can be reduced.
Those skilled in the art will appreciate that the features recited in the various embodiments of the invention and/or in the claims may be combined in various combinations and/or combinations, even if such combinations or combinations are not explicitly recited in the invention. In particular, the features recited in the various embodiments of the invention and/or in the claims can be combined in various combinations and/or combinations without departing from the spirit and teachings of the invention. All such combinations and/or combinations fall within the scope of the invention.
Claims (8)
1. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft comprising a main landing gear assembly (1) and a fuselage (3), characterized in that: a driving wheel (2) is arranged at one side of the bottom of the main landing gear assembly (1);
The left side and the right side of the machine body (3) are respectively provided with a main landing gear assembly (1) and a placing groove (4) which is placed after the driving wheel (2) is folded;
A connecting component (6) is arranged on one side of the main landing gear component (1), a prompting component (7) is arranged on one side of the connecting component (6), a cover plate (5) positioned on one side of the connecting component (6) is arranged on the surface of the machine body (3), and the cover plate (5) is used for shielding the connecting component (6) and the prompting component (7);
The main landing gear assembly (1) comprises a mounting plate (101) and a connecting frame (102), wherein first supporting rods (104) are hinged to two sides of the bottom of the connecting frame (102), and an electric push rod (103) is hinged to the bottom of the connecting frame (102);
a first corner piece (105) is fixed on one side of the bottom of the first supporting rod (104), a second corner piece (106) is hinged to the bottom of the first corner piece (105), and a second supporting rod (107) is fixed on the bottom of the second corner piece (106);
A limiting frame (111) is fixed on the outer side of the mounting plate (101) through a bolt, and a supporting frame (110) hinged to the bottom of the second supporting rod (107) is fixed on one side of the limiting frame (111) through a bolt;
a rotating shaft (109) which is rotatably connected with one side of the machine body (3) is inserted into one side of the limiting frame (111);
the axle center of the driving wheel (2) is connected with an axle, the bottom of the mounting plate (101) is connected with a bottom plate (108) through a bolt, the outer side of the axle is inserted into the inner sides of the mounting plate (101) and the bottom plate (108), and the push rod end of the electric push rod (103) is hinged to one side of the first support rod (104);
when the push rod end of the electric push rod (103) is retracted to the shortest, the hinge point between the first corner piece (105) and the second corner piece (106) is folded and rotated, so that the mounting plate (101) drives the driving wheel (2) to be stored inside the placing groove (4) around the rotating shaft (109);
When the push rod end of the electric push rod (103) stretches out to the longest, the first support rod (104) and the second support rod (107) are coaxial, the mounting plate (101) and the driving wheel (2) rotate around the rotating shaft (109), and the mounting plate (101) and the driving wheel (2) are in an unfolding state.
2. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 1, wherein: the connecting assembly (6) comprises a first fixing frame (601) and a second fixing frame (605), a plurality of limiting grooves (610) are formed in the bottom of the second fixing frame (605), a plurality of limiting blocks (602) which are inserted into the inner sides of the limiting grooves (610) are fixed at the top of the first fixing frame (601), and locking grooves (603) are formed in one side of each limiting block (602).
3. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 2, wherein: the second fixing frame (605) is internally provided with a second sliding groove (607), the inner wall of the second sliding groove (607) is provided with a plurality of first sliding grooves (606), and the inner side of the first sliding groove (606) is provided with a locking rod (609) inserted into the inner side of the locking groove (603).
4. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 3, wherein: the inside sliding connection of second spout (607) has slide bar (604), the top one side of locking lever (609) is fixed in the bottom one side of slide bar (604), be connected with spring (608) between one side of locking lever (609) and the inside of first spout (606).
5. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 4, wherein: the outer side of the second fixing frame (605) is fixed on the inner side wall of the placing groove (4), and the bottom of the first fixing frame (601) is fixed on the top of the connecting frame (102);
When the lock rod (609) is inserted into the lock groove (603), the first fixing frame (601) and the second fixing frame (605) are in a connection state, and when the lock rod (609) is not inserted into the lock groove (603), the first fixing frame (601) and the second fixing frame (605) are in a separation state.
6. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 5, wherein: the prompting assembly (7) comprises a plurality of sliding plates (704), wherein protruding blocks (701) and sliding columns (705) are respectively fixed at the bottoms of two sides of the sliding plates (704), pushing plates (706) are fixed at the bottoms of the sliding columns (705), and through holes (710) are formed in the surfaces of the pushing plates (706).
7. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 6, wherein: a third chute (702) is arranged on the inner wall of the limit groove (610), and the outer side of the sliding plate (704) is connected to the inner side of the third chute (702) in a sliding manner;
A plurality of fourth sliding grooves (709) are formed in the second fixing frame (605), a switch (708) located at the lower side of the pushing plate (706) is fixed at the bottom of the inner wall of the fourth sliding grooves (709), a tension spring (707) is sleeved on the outer side of the switch (708), and two ends of the tension spring (707) are respectively connected to the pushing plate (706) and the inner side walls of the fourth sliding grooves (709).
8. A collapsible main landing gear system for an electric vertical takeoff and landing aircraft according to claim 7, wherein: a plurality of indicator lamps (703) are mounted on one side of the second fixing frame (605), a storage battery (8) is mounted on one side of the second fixing frame (605), the output end of the storage battery (8) is electrically connected with the input end of a switch (708), and the output end of the switch (708) is electrically connected with the input end of the indicator lamps (703);
when the pushing plate (706) leaves the switch (708) contact to enable the indicator lamp (703) to be extinguished, the limiting block (602) is mounted on the inner wall side of the limiting groove (610), and when the pushing plate (706) abuts against the switch (708) contact to enable the indicator lamp (703) to be on, the limiting block (602) is not mounted on the inner wall side of the limiting groove (610).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411281204.7A CN118790471B (en) | 2024-09-13 | 2024-09-13 | A foldable main landing gear system for an electric vertical take-off and landing aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411281204.7A CN118790471B (en) | 2024-09-13 | 2024-09-13 | A foldable main landing gear system for an electric vertical take-off and landing aircraft |
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| CN118790471B true CN118790471B (en) | 2024-11-22 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207072432U (en) * | 2017-07-01 | 2018-03-06 | 深圳市道通智能航空技术有限公司 | A kind of undercarriage and the unmanned plane with this undercarriage |
| CN117944916A (en) * | 2023-12-15 | 2024-04-30 | 中航贵州飞机有限责任公司 | Self-adaptive semi-retractable nose landing gear system of unmanned training machine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2884801B1 (en) * | 2005-04-22 | 2008-11-14 | Eurocopter France | NOSE AUXILLARY LIGHT, CARRIER STRUCTURE AND AIRCRAFT WITH A ROTARY SAIL |
| CN214824065U (en) * | 2020-12-25 | 2021-11-23 | 苏州市双美航空科技有限公司 | Undercarriage winding and unwinding devices |
| CN219008166U (en) * | 2023-01-10 | 2023-05-12 | 长春长光博翔无人机有限公司 | Unmanned aerial vehicle wheeled undercarriage and unmanned aerial vehicle |
| CN219339752U (en) * | 2023-02-15 | 2023-07-14 | 浙江华飞智能科技有限公司 | Undercarriage and unmanned aerial vehicle |
| CN221394000U (en) * | 2023-12-19 | 2024-07-23 | 上海多弗众云航空科技有限公司 | Retractable landing gear and aircraft |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207072432U (en) * | 2017-07-01 | 2018-03-06 | 深圳市道通智能航空技术有限公司 | A kind of undercarriage and the unmanned plane with this undercarriage |
| CN117944916A (en) * | 2023-12-15 | 2024-04-30 | 中航贵州飞机有限责任公司 | Self-adaptive semi-retractable nose landing gear system of unmanned training machine |
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