CN106628103B - Nose landing gear force-bearing mechanism of ducted aircraft - Google Patents

Nose landing gear force-bearing mechanism of ducted aircraft Download PDF

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Publication number
CN106628103B
CN106628103B CN201710031287.8A CN201710031287A CN106628103B CN 106628103 B CN106628103 B CN 106628103B CN 201710031287 A CN201710031287 A CN 201710031287A CN 106628103 B CN106628103 B CN 106628103B
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China
Prior art keywords
arm
chassis frame
tripod
longitudinal
bearing arm
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CN201710031287.8A
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CN106628103A (en
Inventor
刘益华
罗文星
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Shenzhen Hoverstar Flight Technology Co ltd
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Shenzhen Hoverstar Flight Technology Co ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/04—Arrangement or disposition on aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Details Of Gearings (AREA)

Abstract

The invention discloses a nose landing gear bearing mechanism of a ducted aircraft, which is assembled on a chassis frame and comprises a transverse bearing arm, a longitudinal bearing arm, a first locking piece and a second locking piece. The transverse bearing arm is assembled on the chassis frame and is provided with a separation supporting arm and a tripod, and the separation supporting arm separates the tripod into a left tripod and a right tripod; the front end of the longitudinal bearing arm is buckled on the chassis frame from top to bottom by the buckling groove, the rear end of the longitudinal bearing arm is connected to the separation supporting arm by the joint, and the front landing gear of the ducted aircraft is assembled at the longitudinal bearing arm; the first locking piece penetrates through the front end of the longitudinal bearing arm and the chassis frame along the left-right direction of the chassis frame and locks the longitudinal bearing arm and the chassis frame; the second locking piece is penetrated at the joint part and the separation supporting arm along the left-right direction of the chassis frame and locks the joint part and the separation supporting arm, thereby ensuring the lifting reliability of the nose landing gear and having the advantage of simple structure.

Description

Nose landing gear force-bearing mechanism of ducted aircraft
Technical Field
The invention relates to an aircraft, in particular to a nose landing gear bearing mechanism of a ducted aircraft.
Background
With the continuous development of economy and the continuous progress of society, various consumer products are provided for the life of people to meet various material demands of people, and a ducted aircraft is one of the consumer products.
As is well known, a ducted aircraft provides a flying tool for a fan in outdoor exercises, and the fan in outdoor exercises can achieve the aim of flying at low altitude by operating the ducted aircraft, so that the ducted aircraft is favored by the fan in outdoor exercises.
At present, in the existing ducted aircraft, the components of the bearing device of the nose landing gear are numerous, so that the structure of the existing bearing device is complex, the assembly is inconvenient, the impact capability is limited, the reliability of landing can not be effectively ensured, and the safety is poor.
Accordingly, there is a need to provide a nose landing gear load mechanism for a ducted aircraft that overcomes the above-described drawbacks.
Disclosure of Invention
The invention aims to provide a nose landing gear bearing mechanism of a ducted aircraft, which has the advantages of simple structure, reliable bearing and good safety.
In order to achieve the above purpose, the technical scheme of the invention is as follows: a nose landing gear bearing mechanism of a ducted aircraft is provided, and is assembled on a chassis frame of the ducted aircraft. The nose landing gear bearing mechanism of the ducted aircraft comprises a transverse bearing arm, a longitudinal bearing arm, a first locking piece and a second locking piece. The transverse bearing arm is assembled on the chassis frame along the left-right direction of the chassis frame, a tripod is arranged in the middle of the transverse bearing arm, the top of the tripod is upwards arranged, a separation supporting arm which extends to the top of the tripod and is integrated with the top of the tripod is also extended from the middle of the transverse bearing arm, the separation supporting arm vertically bisects the tripod, and the separation supporting arm separates the tripod into a left tripod and a right tripod; the longitudinal bearing arm is arranged along the front-back direction of the chassis frame, a buckling groove is formed in the bottom of the front end of the longitudinal bearing arm, a joint part which is jointed with the separation supporting arm is formed in the rear end of the longitudinal bearing arm, the front end of the longitudinal bearing arm is buckled at the chassis frame from top to bottom by means of the buckling groove, a separation groove matched with the joint part is formed in the separation supporting arm, the joint part is inserted into the separation groove, the rear end of the longitudinal bearing arm is jointed at the separation supporting arm by means of the joint part, and the front landing gear of the ducted aircraft is assembled at the longitudinal bearing arm; the first locking piece penetrates through the front end of the longitudinal bearing arm and the chassis frame along the left-right direction of the chassis frame and locks the longitudinal bearing arm and the chassis frame; the second locking piece penetrates through the joint part and the separation supporting arm along the left-right direction of the chassis frame and locks the joint part and the separation supporting arm.
Preferably, the longitudinal bearing arms vertically bisect the transverse bearing arms.
Preferably, the joint part is inserted into the separation groove from front to back.
Preferably, the first locking member comprises a first bolt and a first nut which are matched with each other, the first bolt passes through the front end of the longitudinal bearing arm and the chassis frame from the left side of the chassis frame to the right side, and the first nut is screwed into the first bolt and locks the longitudinal bearing arm and the chassis frame together with the first bolt.
Preferably, the second locking member comprises a second bolt and a second nut which are matched with each other, the second bolt penetrates through the joint part of the longitudinal bearing arm and the separation supporting arm from the left side of the chassis frame to the right side, and the second nut is screwed into the second bolt and locks the joint part of the longitudinal bearing arm and the separation supporting arm together with the second bolt.
Preferably, the part of the transverse bearing arm adjacent to the corner of the tripod extends forwards and backwards to form a front connector and a rear connector respectively, and the transverse bearing arm is spliced with the chassis frame through the front connector and the rear connector.
Preferably, the intersection of the separation supporting arm and the tripod is in an arc structure.
Compared with the prior art, the nose landing gear bearing mechanism comprises the transverse bearing arm, the longitudinal bearing arm, the first locking piece and the second locking piece, and the longitudinal bearing arm can be assembled at the chassis frame and the transverse bearing arm more conveniently and rapidly by means of the buckling groove and the joint part of the longitudinal bearing arm and the first locking piece and the second locking piece, so that the nose landing gear bearing mechanism is more convenient to assemble. The middle part of the transverse bearing arm is provided with the tripod, the top of the tripod is upwards arranged, the middle part of the transverse bearing arm also extends to the top of the tripod and is integrated with the top, the tripod is vertically divided into the tripod by the separation supporting arm, the tripod is separated into the left tripod and the right tripod by the separation supporting arm, the front end of the longitudinal bearing arm is locked with the chassis frame through the first locking piece, the joint part at the rear end of the longitudinal bearing arm is locked with the separation supporting arm through the second locking piece, and the safety of the landing of the ducted aircraft is ensured according to the characteristic that the triangle is not easy to deform, so that the longitudinal bearing arm can be more reliably fixed on the transverse bearing arm and the chassis frame, the upward impact force generated by the landing of the nose landing gear is relieved to the maximum extent, and the first locking piece and the second locking piece are in a sheared state under the upward impact force, so that the upward impact force born by the first locking piece and the second locking piece is larger, and the reliability of the landing of the nose landing gear is further improved.
Drawings
Fig. 1 is a schematic perspective view of a nose landing gear load-bearing mechanism of a ducted aircraft of the present invention assembled at a chassis frame.
Fig. 2 is a schematic perspective exploded view of the nose landing gear load mechanism of the ducted aircraft of fig. 1 separated from the chassis frame.
Fig. 3 is a schematic perspective view of the nose landing gear load mechanism, nose landing gear and nose wheel of the ducted aircraft of the present invention assembled together.
Fig. 4 is a schematic perspective view of the nose landing gear load-bearing mechanism of the ducted aircraft of the present invention.
Fig. 5 is a schematic perspective exploded view of the nose landing gear load bearing mechanism of the ducted aircraft of the present invention.
Detailed Description
Embodiments of the present invention will now be described with reference to the drawings, wherein like reference numerals represent like elements throughout.
Referring to fig. 1 and 2, a nose landing gear bearing mechanism 100 of a ducted aircraft of the present invention is assembled on a chassis frame 200 of the ducted aircraft, and the chassis frame 200 provides mounting support. The nose landing gear bearing mechanism 100 of the present invention includes a transverse bearing arm 10, a longitudinal bearing arm 20, a first locking member 30, and a second locking member 40. The transverse force bearing arm 10 is assembled on the chassis frame 200 along the left-right direction of the chassis frame 200, and the chassis frame 200 provides mounting support for the transverse force bearing arm 10; the middle part of the transverse bearing arm 10 is provided with a tripod 11, the top of the tripod 11 is upwards arranged, and the problem that the structure of the chassis frame 200 is heavy due to downwards arrangement of the top of the tripod 11 is prevented; the middle part of the transverse bearing arm 10 also extends to the top of the tripod 11 and is integrated with the top into a whole, and the tripod 11 is separated from a left tripod 11a and a right tripod 11b by the separation supporting arm 12; specifically, in the present embodiment, the separation supporting arm 12 vertically bisects the tripod 11, so that the sizes of the left tripod 11a and the right tripod 11b are consistent, and the impact force born by the tripod 11 is greater, but not limited thereto. In order to improve the convenience of assembling and disassembling the transverse bearing arm 10 and the chassis frame 200, the front connector 14 and the rear connector 15 extend forwards and backwards from the part of the transverse bearing arm 10 adjacent to the corner of the tripod 11, so that the transverse bearing arm 10 is spliced with the chassis frame 200 through the front connector 14 and the rear connector 15, and three-way connection of the transverse bearing arm 10 and the chassis frame 200 is realized, but not limited to the above; in order to make the stress concentration at the corners of the tripod 11 smaller, the intersection of the partition supporting arm 12 and the tripod 11 is a circular arc structure 13, so that the connection between the partition supporting arm 12 and the tripod 12 is more reliable, and the reliability of landing gear is further ensured.
As shown in fig. 3 to 5, the longitudinal bearing arm 20 is arranged along the front-rear direction of the chassis frame 200, the front end bottom of the longitudinal bearing arm 20 is provided with a buckling groove 21, the rear end of the longitudinal bearing arm 20 is provided with a joint 22 jointed with the separation supporting arm 12, and the front end of the longitudinal bearing arm 20 is buckled at the chassis frame 200 from top to bottom by means of the buckling groove 21, so that the front end of the longitudinal bearing arm 20 and the chassis frame 200 are assembled and disassembled more quickly; nose landing gear 300 of the ducted aircraft is assembled at longitudinal moment arm 20; the rear end of the longitudinal bearing arm 20 is jointed at the separation supporting arm 12 by the joint part 22, the separation supporting arm 12 supports the rear end of the longitudinal bearing arm 20, the separation supporting arm 12 is a shared triangular edge of the left tripod 11a and the right tripod 11b, and the longitudinal bearing arm 20 can bear larger punching force under the support of the separation supporting arm 12 by the characteristic of being not easy to change due to the triangle, so that the stability and the reliability during landing can be ensured; specifically, in the present embodiment, the longitudinal bearing arm 20 vertically bisects the transverse bearing arm 10, so that the supporting force of the transverse bearing arm 10 received by the longitudinal bearing arm 20 is more uniform and reliable, but not limited thereto; for example, in the present embodiment, the separation supporting arm 12 is provided with a separation groove 121 matching with the joint portion 22, and the joint portion 22 is inserted into the separation groove 121 from front to back, so that the assembly and disassembly between the longitudinal bearing arm 20 and the separation supporting arm 12 are more convenient; for example, in the present embodiment, the specific assembly process of the longitudinal bearing arm 20 is: the joint 22 of the longitudinal bearing arm 20 is inserted into the separation groove 121 from front to back, then the longitudinal bearing arm 20 is buckled in the chassis frame 200 from top to bottom by the buckling groove 21. The front end of the longitudinal bearing arm 20 is locked with the chassis frame 200 by the first locking member 30, and the joint portion 22 of the longitudinal bearing arm 20 is locked with the separating support arm 12 by the second locking member 40, so that the purpose of rapid assembly of the longitudinal bearing arm 20 is achieved, but not limited thereto.
As shown in fig. 1 to 5, the first locking member 30 is inserted between the front end of the longitudinal support arm 20 and the chassis frame 200 in the left-right direction of the chassis frame 200 and locks the longitudinal support arm 20 and the chassis frame 200, so that the first locking member 30 selectively allows or prohibits the assembly and disassembly between the front end of the longitudinal support arm 20 and the chassis frame 200, thereby facilitating the assembly of the longitudinal support arm 20 at the chassis frame 200; specifically, as shown in fig. 5, in the present embodiment, the first locking member 30 includes a first bolt 31 and a first nut 32 that are mutually matched, the first bolt 31 passes through the front end of the longitudinal support arm 20 and the chassis frame 200 from the left side to the right side of the chassis frame 200, and the first nut 32 is screwed into the first bolt 31 and locks the longitudinal support arm 20 and the chassis frame 200 together with the first bolt 31, so that the longitudinal support arm 20 is convenient to be assembled and disassembled at the chassis frame 200, but not limited thereto. In order to make the connection between the front end of the longitudinal bearing arm 20 and the chassis frame 200 more reliable, the first locking member 30 further includes a first washer 33 penetrating the first bolt 31 and locked by the first nut 32, so as to improve the shock resistance through the first washer 33, and effectively prevent the first nut 32 from accidentally falling off the first bolt 31, but not limited thereto. It can be understood that in other embodiments, the first locking member 30 is a screw, and correspondingly, a threaded structure is formed on one side of the front end of the longitudinal bearing arm 20, so that the screw penetrates from one side of the front end of the longitudinal bearing arm 20 without the threaded structure, and is screwed with the threaded structure through the chassis frame 200, so that the purpose of locking the longitudinal bearing arm 20 and the chassis frame 200 by the screw can be achieved, but not limited thereto.
As shown in fig. 1 to 5, the second locking member 40 is inserted through the joint 22 and the partition support arm 12 in the left-right direction of the chassis frame 200 and locks the joint 22 and the partition support arm 12, so that the assembly and disassembly between the joint 22 of the longitudinal bearing arm 20 and the partition support arm 12 is selectively allowed or forbidden by the second locking member 40, thereby facilitating the assembly of the longitudinal bearing arm 20 at the partition support arm 12; specifically, as shown in fig. 5, in the present embodiment, the second locking member 40 includes a second bolt 41 and a second nut 42 that are mutually matched, the second bolt 41 passes through the joint portion 22 of the longitudinal support arm 20 and the separation support arm 12 from the left side to the right side of the chassis frame 200, and the second nut 42 is screwed into the second bolt 41 and locks the joint portion 22 of the longitudinal support arm 20 and the separation support arm 12 together with the second bolt 41, so as to facilitate assembly and disassembly of the joint portion 22 of the longitudinal support arm 20 at the separation support arm 12, but not limited thereto; in order to make the connection between the joint 22 of the longitudinal bearing arm 20 and the separation supporting arm 12 more reliable, the second locking member 40 further includes a second washer 43 penetrating the second bolt 41 and locked by the second nut 42, so as to improve the shock resistance through the second washer 43, and effectively prevent the second nut 42 from accidentally falling off the second bolt 41, but not limited thereto. It should be understood that in other embodiments, the second locking member 40 is a screw, and correspondingly, a threaded structure is formed on one side of the joint portion 22 of the longitudinal support arm 20, so that the screw penetrates from the side of the joint portion 22 of the longitudinal support arm 20 without the threaded structure, and is screwed with the threaded structure through the separation support arm 12, so that the purpose of locking the joint portion 22 of the longitudinal support arm 20 and the separation support arm 12 by the screw can be achieved, but not limited thereto.
Compared with the prior art, the nose landing gear bearing mechanism 100 of the invention comprises the transverse bearing arm 10, the longitudinal bearing arm 20, the first locking piece 30 and the second locking piece 40, and the longitudinal bearing arm 20 can be assembled at the chassis frame 200 and the transverse bearing arm 10 more conveniently and rapidly by means of the buckling groove 21 and the joint part 22 of the longitudinal bearing arm 20 and the first locking piece 30 and the second locking piece 40, so that the nose landing gear bearing mechanism 100 of the invention is more convenient to assemble. The middle part of the transverse bearing arm 10 is provided with the tripod 11, the top of the tripod 11 is upwards arranged, the middle part of the transverse bearing arm 10 also extends to the separation supporting arm 12 which extends to the top of the tripod 11 and is integrated with the top, the separation supporting arm 12 separates the tripod 11 from the left tripod 11a and the right tripod 11b, the front end of the longitudinal bearing arm 20 is locked with the chassis frame 200 through the first locking piece 30, the joint part 22 at the rear end of the longitudinal bearing arm 20 is locked with the separation supporting arm 12 through the second locking piece 40, and the joint part is not easy to deform according to the triangle, so that the longitudinal bearing arm 20 can be more reliably fixed on the transverse bearing arm 10 and the chassis frame 200, the upward impact force generated by the nose landing gear during landing is relieved to the maximum extent, and the first locking piece 30 and the second locking piece 40 are in a sheared state under the upward impact force, so that the upward impact force born by the first locking piece 30 and the second locking piece 40 is larger, the reliability of the nose landing gear during landing is further improved, and the safety of the landing gear is ensured.
The foregoing description of the preferred embodiments of the present invention is not intended to limit the scope of the claims, which follow, as defined in the claims.

Claims (7)

1. The utility model provides a nose gear force-bearing mechanism of ducted aircraft, assembles on the chassis frame of ducted aircraft, its characterized in that, nose gear force-bearing mechanism of ducted aircraft includes:
the transverse bearing arm is assembled on the chassis frame along the left-right direction of the chassis frame, a tripod is arranged in the middle of the transverse bearing arm, the top of the tripod is upwards arranged, a separation supporting arm which extends to the top of the tripod and is integrated with the top of the tripod is also extended from the middle of the transverse bearing arm, the separation supporting arm vertically bisects the tripod, and the separation supporting arm separates the tripod into a left tripod and a right tripod;
the longitudinal bearing arm is arranged along the front-back direction of the chassis frame, a buckling groove is formed in the bottom of the front end of the longitudinal bearing arm, a joint part which is jointed with the separation supporting arm is formed in the rear end of the longitudinal bearing arm, the front end of the longitudinal bearing arm is buckled at the chassis frame from top to bottom by means of the buckling groove, a separation groove matched with the joint part is formed in the separation supporting arm, the joint part is inserted into the separation groove, the rear end of the longitudinal bearing arm is jointed at the separation supporting arm by means of the joint part, and the front landing gear of the ducted aircraft is assembled at the longitudinal bearing arm;
the first locking piece is penetrated in the front end of the longitudinal bearing arm and the chassis frame along the left-right direction of the chassis frame and locks the longitudinal bearing arm and the chassis frame; and
the second locking piece is penetrated at the joint part and the separation supporting arm along the left-right direction of the chassis frame and locks the joint part and the separation supporting arm.
2. The nose landing gear load mechanism of a ducted aircraft of claim 1, wherein the longitudinal load arm vertically bisects the transverse load arm.
3. The nose landing gear load mechanism of a ducted aircraft of claim 1, wherein the engagement portion is inserted into the separation slot from front to back.
4. The nose landing gear load-carrying mechanism of a ducted aircraft of claim 1, wherein the first locking member comprises a first bolt and a first nut that are mutually matched, the first bolt passes through the front end of the longitudinal load-carrying arm and the chassis frame from the left side to the right side of the chassis frame, and the first nut is screwed into the first bolt and locks the longitudinal load-carrying arm and the chassis frame together with the first bolt.
5. The nose landing gear load-carrying mechanism of a ducted aircraft of claim 1, wherein the second locking member comprises a second bolt and a second nut that cooperate with each other, the second bolt passing through the engagement portion of the longitudinal load-carrying arm and the separation support arm from the left side to the right side of the chassis frame, the second nut being threaded into the second bolt and locking the engagement portion of the longitudinal load-carrying arm and the separation support arm together with the second bolt.
6. The nose landing gear load-bearing mechanism of ducted aircraft of claim 1, wherein the portion of the lateral load-bearing arm adjacent to the outside of the corner of the tripod extends forward and rearward respectively out of a front connector and a rear connector, through which the lateral load-bearing arm is plugged with the chassis frame.
7. The nose landing gear load-bearing mechanism of a ducted aircraft of claim 1, wherein the intersection of the separator support arms and the tripod is a circular arc structure.
CN201710031287.8A 2017-01-17 2017-01-17 Nose landing gear force-bearing mechanism of ducted aircraft Active CN106628103B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710031287.8A CN106628103B (en) 2017-01-17 2017-01-17 Nose landing gear force-bearing mechanism of ducted aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710031287.8A CN106628103B (en) 2017-01-17 2017-01-17 Nose landing gear force-bearing mechanism of ducted aircraft

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CN106628103B true CN106628103B (en) 2023-07-18

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Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1531619A (en) * 1923-03-29 1925-03-31 Laddon Isaac Machlin Landing gear
US4392622A (en) * 1980-12-22 1983-07-12 The Boeing Company Combined beam support for landing gear
FR2948096B1 (en) * 2009-07-15 2011-11-25 Messier Dowty Sa FRONT AIRCRAFT TRAIN WITH SINGLE CONTROL DEVICE FOR LIFT AND STEERING
FR2998868B1 (en) * 2012-11-30 2016-02-05 Airbus Operations Sas INTERMEDIATE FASTENING DEVICE BETWEEN AN AIRCRAFT FUSELAGE AND AN AIRCRAFT LANDING TRAIN
CN206466156U (en) * 2017-01-17 2017-09-05 深圳市哈威飞行科技有限公司 The nose-gear load mechanism of duct aircraft

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