CN106628103A - Front landing gear bearing mechanism of ducted air vehicle - Google Patents
Front landing gear bearing mechanism of ducted air vehicle Download PDFInfo
- Publication number
- CN106628103A CN106628103A CN201710031287.8A CN201710031287A CN106628103A CN 106628103 A CN106628103 A CN 106628103A CN 201710031287 A CN201710031287 A CN 201710031287A CN 106628103 A CN106628103 A CN 106628103A
- Authority
- CN
- China
- Prior art keywords
- support arm
- sole
- nose
- tripod
- longitudinal support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
Abstract
The invention discloses a front landing gear bearing mechanism of a ducted air vehicle. The front landing gear bearing mechanism is assembled on a chassis frame and comprises transverse bearing arms, longitudinal bearing arms, a first locking piece and a second locking piece. The transverse bearing arms are assembled on the chassis frame and provided with dividing supporting arms and tripods, and the tripods are divided into the left tripod and the right tripod by the dividing supporting arms; fastening grooves are formed in the bottoms of the front ends of the longitudinal bearing arms, connecting parts are installed at the rear ends of the longitudinal bearing arms, and the chassis frame is fastened with the front ends of the longitudinal bearing arms from top to bottom by the aid of the fastening grooves; the rear ends of the longitudinal bearing arms are connected to the dividing supporting arms by the aid of the connecting parts, and a front landing gear of the ducted air vehicle is assembled on the longitudinal bearing arms; the first locking piece is installed at the front ends of the longitudinal bearing arms and the chassis frame in the left-right direction of the chassis frame in a penetrating mode and locks the longitudinal bearing arms and the chassis frame, the second locking piece is installed on the connecting parts and the dividing supporting arms in the left-right direction of the chassis frame in a penetrating mode and locks the connecting parts and the dividing supporting arms, and landing reliability of the front landing gear is guaranteed; and the front landing gear bearing mechanism of the ducted air vehicle further has the advantage of being simple in structure.
Description
Technical field
The present invention relates to a kind of aircraft, more particularly to a kind of nose-gear load mechanism of duct aircraft.
Background technology
With economic continuous development and the continuous progress of society, the life for people provides the various consumer goods,
To meet the various material requisites of people, and duct aircraft is exactly the one kind in many consumer goods.
It is well known that duct aircraft provides a kind of utensil of flight, the love of outdoor exercises for the fan of outdoor exercises
Good person just can reach the purpose in low-latitude flying by the operation to duct aircraft, therefore, duct aircraft is very subject to family
The fan of outer motion is favored.
At present, in existing duct aircraft, due to the component of the bearing of its nose-gear it is various so that existing
The complex structure of some bearings, assembling inconvenience, and suffered impact capacity is limited, it is impossible to effectively ensure that the reliability risen and fallen
Property, therefore security is poor.
Therefore, it is necessary to provide a kind of nose-gear load mechanism of duct aircraft to overcome above-mentioned defect.
The content of the invention
It is an object of the invention to provide a kind of nose-gear load mechanism of duct aircraft, its simple structure, load
Reliability and security is good.
For achieving the above object, the technical scheme is that：A kind of nose-gear load machine of duct aircraft is provided
Structure, is assembled on the sole of duct aircraft.Wherein, the nose-gear load mechanism of the duct aircraft includes laterally holding
The arm of force, longitudinal support arm, the first locking part and the second locking part.Left and right directions group of the horizontal support arm along the sole
Loaded on the sole, the middle part of the horizontal support arm has tripod, and the top of the tripod is upwardly disposed, described
Laterally the top for extending the tripod and the separation support arm struck up partnership with the top, institute are also extended in the middle part of support arm
State separation support arm and the tripod is separated out into left tripod and right tripod；Longitudinal support arm is along the sole
Fore-and-aft direction arranges, the front bottom end of longitudinal support arm offers buckling groove, the rear end of longitudinal support arm have with
The junction surface for separating support arm engagement, the front end of longitudinal support arm is fastened on from top to bottom institute by the buckling groove
State at sole, the rear end of longitudinal support arm is engaged at the separation support arm by the junction surface, the duct
The nose-gear of aircraft is assembled at longitudinal support arm；First locking part is worn along the left and right directions of the sole
The front end of longitudinal support arm is placed in the sole and lock longitudinal support arm and sole；Second locking
Part along the left and right directions of the sole be placed through the junction surface with it is described separation support arm at and lock the junction surface with
The separation support arm.
It is preferred that the separation support arm vertically divides the tripod equally.
It is preferred that longitudinal support arm vertically divides the horizontal support arm equally.
It is preferred that the separation support arm offers the separation trough matched with the junction surface, the junction surface is by going to
After be inserted in the separation trough.
It is preferred that first locking part includes the first bolt for cooperating and the first nut, first bolt from
Turn right on the left of the sole front end and sole of the direction through longitudinal support arm, first nut screws in institute
State the first bolt and lock together with first bolt longitudinal support arm and sole.
It is preferred that second locking part includes the second bolt for cooperating and the second nut, second bolt from
Turn right on the left of the sole direction through longitudinal support arm junction surface and separate support arm, second nut
Screw in second bolt and the junction surface of the longitudinal support arm that locks together with second bolt and separation support arm.
It is preferred that position of the horizontal support arm outside the corner of the tripod respectively forwardly and extends back
Front pipe joint and tube head is followed by, the horizontal support arm is by the front pipe joint and is followed by tube head with the sole grafting.
It is preferred that the separation support arm is arc structure with the intersection of the tripod.
Compared with prior art, due to the nose-gear load mechanism of the present invention include horizontal support arm, longitudinal support arm,
First locking part and the second locking part, the buckling groove and junction surface by longitudinal support arm, and the first locking part and the second lock
Firmware so that be assembled at sole and horizontal support arm, so that before the present invention to longitudinal support arm energy more convenient and quicker
The assembling of undercarriage load mechanism is more convenient.Again because the middle part of horizontal support arm has tripod, the top of tripod is upward
The top for extending tripod and the separation support arm struck up partnership with the top are also extended in arrangement, the middle part of horizontal support arm,
Separate support arm and tripod be separated out into left tripod and right tripod, and the front end of longitudinal support arm by the first locking part with
Sole is locked together, and the junction surface of the rear end of longitudinal support arm locks one by the second locking part with support arm is separated
Rise, yielding characteristic do not allowed according to triangle so that longitudinal support arm can more reliably be fixed on horizontal support arm with
On sole, it is produced to upthrust in landing to alleviate nose-gear to greatest extent, and the first locking part and the second lock
Firmware is under momentum effect upwards and receives scissor state, so that the punching upwards that the first locking part and the second locking part are born
Power is bigger, and then improves reliability when nose-gear rises and falls, thereby, it is ensured that the security that duct aircraft rises and falls.
Description of the drawings
Fig. 1 is that the stereochemical structure that the nose-gear load mechanism of the duct aircraft of the present invention is assembled at sole is illustrated
Figure.
Fig. 2 is the stereo decomposing when nose-gear load mechanism of the duct aircraft shown in Fig. 1 is separated with sole
Structural representation.
Fig. 3 is that nose-gear load mechanism, nose-gear and the front-wheel three of the duct aircraft of the present invention are assembled in one
Dimensional structure diagram when rising.
Fig. 4 is the dimensional structure diagram of the nose-gear load mechanism of the duct aircraft of the present invention.
Fig. 5 is the dimensional decomposition structure diagram of the nose-gear load mechanism of the duct aircraft of the present invention.
Specific embodiment
With reference now to Description of Drawings embodiments of the invention, the element numbers being similar in accompanying drawing represent similar element.
Fig. 1 and Fig. 2 is referred to, the nose-gear load mechanism 100 of the duct aircraft of the present invention is assembled in duct flight
On the sole 200 of device, provide installation by sole 200 and support.Wherein, nose-gear load mechanism 100 of the invention includes
Horizontal support arm 10, longitudinal support arm 20, the first locking part 30 and the second locking part 40.Laterally support arm 10 is along sole 200
Left and right directions be assembled on sole 200, by sole 200 for horizontal support arm 10 provide installation support；Horizontal support arm
10 middle part has tripod 11, and the top of tripod 11 is upwardly disposed, and the top for preventing tripod 11 is made because arranging down
Into the structure bulky of sole 200；Laterally the middle part of support arm 10 also extend the top that extends tripod 11 and with the top
The separation support arm 12 for striking up partnership, separates support arm 12 and tripod 11 is separated out into left tripod 11a and right tripod 11b；
Specifically, in the present embodiment, separate support arm 12 and vertically divide tripod 11 equally so that left tripod 11a and right tripod 11b
It is in the same size so that the impulsive force that tripod 11 is born is bigger, but be not limited.In order to improve horizontal support arm
10 with the convenience of the assembling and dismantling of sole 200, therefore laterally position of the support arm 10 outside the corner of tripod 11 respectively forwardly and
Extend back front pipe joint 14 and be followed by tube head 15 so that laterally support arm 10 by front pipe joint 14 and be followed by tube head 15 with
The grafting of sole 200, realizes that horizontal support arm 10 is connected with the threeway of sole 200, but is not limited；In order that triangle
The stress concentration of the corner of frame 11 is less, therefore it is arc structure 13 to separate support arm 12 with the intersection of tripod 11, so as to
So that the connection separated between support arm 12 and tripod 12 is more reliable, and then reliability when guaranteeing that undercarriage lands.
As shown in Figures 3 to 5, longitudinal support arm 20 along sole 200 fore-and-aft direction arrange, before longitudinal support arm 20
End bottom offers buckling groove 21, and the rear end of longitudinal support arm 20 has and separates the junction surface 22 that support arm 12 is engaged, longitudinal direction
The front end of support arm 20 is fastened on from top to bottom at sole 200 by buckling groove 21 so that the front end of longitudinal support arm 20 with
The group of sole 200 unloads faster；The nose-gear 300 of duct aircraft is assembled at longitudinal support arm 20；Longitudinal support arm
20 rear end is engaged at separation support arm 12 by junction surface 22, is entered by the rear end of 12 pairs of longitudinal support arms 20 of separation support arm
Row is supported, and separates share three arms of angle of the support arm 12 for left tripod 11a and right tripod 11b, is difficult by triangle
The characteristic of change, so that longitudinal support arm 20 can bear bigger power of going out under the support for separating support arm 12, thus more
Can ensure that steady reliability during landing；Specifically, in the present embodiment, longitudinal support arm 20 vertically divides horizontal support arm equally
10 so that the support force of the horizontal support arm 10 suffered by longitudinal support arm 20 is evenly reliable, but is not limited；Citing and
Speech, in the present embodiment, separates support arm 12 and offers the separation trough 121 matched with junction surface 22, and junction surface 22 is from front to back
It is inserted in separation trough 121 so that longitudinal support arm 20 and the group separated between support arm 12 unload more convenient；Illustrate, at this
In embodiment, the concrete assembling process of longitudinal support arm 20 is：Plant from front to back at the junction surface 22 for first making longitudinal support arm 20
In separation trough 121, and then, longitudinal support arm 20 is set to be fastened in sole 200 by buckling groove 21 from top to bottom, so
Afterwards.Again the front end of longitudinal support arm 20 is locked with sole 200 by the first locking part 30, and by the second locking part 40
The junction surface 22 of longitudinal support arm 20 is locked with support arm 12 is separated, thus realizes the mesh of the quick assembling of longitudinal support arm 20
, but be not limited.
As shown in Figures 1 to 5, the first locking part 30 is placed through longitudinal support arm 20 along the left and right directions of sole 200
Front end and sole 200 and lock longitudinal support arm 20 and sole 200, being selectively allowed for by the first locking part 30 or
Forbid the assembling and dismantling between the front end of longitudinal support arm 20 and sole 200, consequently facilitating longitudinal support arm 20 is at sole 200
Assembling；Specifically, as shown in figure 5, in the present embodiment, the first locking part 30 is comprising the first bolt 31 and first for cooperating
Nut 32, the first bolt 31 is turned right front end and sole of the direction through longitudinal support arm 20 from the left side of sole 200
200, the first nut 32 screws in the first bolt 31 and lock together with first bolt 31 longitudinal support arm 20 and sole 200,
Consequently facilitating assembling and dismantling of longitudinal support arm 20 at sole 200, but be not limited.To cause the front end of longitudinal support arm 20
It is more reliable with the connection between sole 200, therefore the first locking part 30 is also included and is placed through on the first bolt 31 and by the first nut
First packing ring 33 of 32 lockings, to go to improve shock resistance by the first packing ring 33, is effectively prevented the first nut 32 and the first spiral shell
The accident of bolt 31 comes off, but is not limited.It will be appreciated that in other embodiments, the first locking part 30 is a screw, right
Ying Di, the side of the front end of longitudinal support arm 20 offers helicitic texture, therefore not the having from the front end of longitudinal support arm 20 in screw
The side for having helicitic texture penetrates, and is threadedly coupled with helicitic texture again by sole 200, can equally realize screw locking longitudinal direction
The purpose of support arm 20 and sole 200, but be not limited.
As shown in Figures 1 to 5, the second locking part 40 is placed through junction surface 22 and separates along the left and right directions of sole 200
At support arm 12 and lock junction surface 22 with separate support arm 12, to be selectively allowed for by the second locking part 40 or forbid indulging
Assembling and dismantling between the junction surface 22 of support arm 20 and separation support arm 12, consequently facilitating longitudinal support arm 20 is in separation support arm 12
The assembling at place；Specifically, as shown in figure 5, in the present embodiment, the second locking part 40 comprising the second bolt 41 for cooperating and
Second nut 42, the second bolt 41 from the left side of sole 200 turn right direction through longitudinal support arm 20 junction surface 22 and
Separate connecing for support arm 12, the second bolt 41 of screw-in of the second nut 42 and longitudinal support arm 20 that locks together with second bolt 41
Conjunction portion 22 and separation support arm 12, consequently facilitating assembling and dismantling of the junction surface 22 of longitudinal support arm 20 at separation support arm 12, but
It is not limited；In order that the connection between the junction surface 22 of longitudinal support arm 20 and separation support arm 12 is more reliable, therefore second
Locking part 40 is also included and is placed through on the second bolt 41 and by the second packing ring 43 of the locking of the second nut 42, with by second packing ring
43 go to improve shock resistance, are effectively prevented the second nut 42 and come off with the accident of the second bolt 41, but are not limited.It is appreciated that
, in other embodiments, the second locking part 40 is a screw, accordingly, the side at the junction surface 22 of longitudinal support arm 20
Helicitic texture is offered, therefore is penetrated from the side without helicitic texture at the junction surface 22 of longitudinal support arm 20 in screw, passed through
Separate support arm 12 to be threadedly coupled with helicitic texture again, can equally realize the junction surface 22 of screw locking longitudinal direction support arm 20 and divide
Every the purpose of support arm 12, but it is not limited.
Compared with prior art, because the nose-gear load mechanism 100 of the present invention includes that horizontal support arm 10, longitudinal direction hold
The arm of force 20, the first locking part 30 and the second locking part 40, the buckling groove 21 and junction surface 22, Yi Ji by longitudinal support arm 20
One locking part 30 and the second locking part 40 so that longitudinal support arm 20 can be assembled in more convenient and quicker sole 200 and horizontal
At support arm 10, so that the assembling of the nose-gear load mechanism 100 of the present invention is more convenient.Again due to horizontal support arm 10
Middle part has tripod 11, and the top of tripod 11 is upwardly disposed, and the middle part of horizontal support arm 10 is also extended and extends tripod
11 top and the separation support arm 12 struck up partnership with the top, separate support arm 12 and tripod 11 are separated out into left tripod
11a and right tripod 11b, and the front end of longitudinal support arm 20 is locked together by the first locking part 30 with sole 200, is indulged
Junction surface 22 to the rear end of support arm 20 locks together by the second locking part 40 with support arm 12 is separated, according to triangle
Yielding characteristic is not allowed, so that longitudinal support arm 20 can more reliably be fixed on horizontal support arm 10 and sole 200
On, it is produced to upthrust in landing to alleviate nose-gear to greatest extent, and the first locking part 30 and the second locking part
40 are in by scissor state, so that the first locking part 30 and the second locking part 40 are born upwards under momentum effect upwards
Impulse force is bigger, and then improves reliability when nose-gear rises and falls, thereby, it is ensured that the security that duct aircraft rises and falls.
Upper disclosed only the preferred embodiments of the present invention, can not limit the right model of the present invention with this certainly
Enclose, therefore the equivalent variations made according to scope of the present invention patent, still belong to the scope that the present invention is covered.
Claims (8)
1. a kind of nose-gear load mechanism of duct aircraft, is assembled on the sole of duct aircraft, it is characterised in that
The nose-gear load mechanism of the duct aircraft includes：
Laterally support arm, is assembled on the sole, the middle part of the horizontal support arm along the left and right directions of the sole
With tripod, the top of the tripod is upwardly disposed, and the middle part of the horizontal support arm is also extended and extends the triangle
The tripod is separated out left triangle by the top of frame and the separation support arm struck up partnership with the top, the separation support arm
Frame and right tripod；
Longitudinal support arm, the fore-and-aft direction along the sole arranges that the front bottom end of longitudinal support arm offers fastening
Groove, the rear end of longitudinal support arm has the junction surface engaged with the separation support arm, the front end of longitudinal support arm
It is fastened on from top to bottom at the sole by the buckling groove, the rear end of longitudinal support arm connects by the junction surface
At the separation support arm, the nose-gear of the duct aircraft is assembled at longitudinal support arm；
First locking part, the front end for being placed through longitudinal support arm along the left and right directions of the sole is with the sole simultaneously
Lock longitudinal support arm and sole；And
Second locking part, is placed through the junction surface and separates at support arm and lock with described along the left and right directions of the sole
The junction surface and the separation support arm.
2. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that the separation is supported
Arm vertically divides the tripod equally.
3. the nose-gear load mechanism of duct aircraft according to claim 2, it is characterised in that longitudinal load
Arm vertically divides the horizontal support arm equally.
4. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that the separation is supported
Arm offers the separation trough matched with the junction surface, and the junction surface is inserted in from front to back in the separation trough.
5. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that first locking
Part includes the first bolt for cooperating and the first nut, and first bolt direction of turning right from the left of the sole is worn
Front end and the sole of longitudinal support arm are crossed, first nut screws in first bolt and together with first bolt
Lock longitudinal support arm and sole.
6. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that second locking
Part includes the second bolt for cooperating and the second nut, and second bolt direction of turning right from the left of the sole is worn
Cross the junction surface of longitudinal support arm and separate support arm, second nut screw in second bolt and with second spiral shell
Bolt lock together longitudinal support arm junction surface and separate support arm.
7. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that the horizontal load
Position of the arm outside the corner of the tripod respectively forwardly and extends back front pipe joint and is followed by tube head, it is described laterally
Support arm is by the front pipe joint and is followed by tube head with the sole grafting.
8. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that the separation is supported
Arm is arc structure with the intersection of the tripod.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628103A true CN106628103A (en) | 2017-05-10 |
| CN106628103B CN106628103B (en) | 2023-07-18 |
Family
ID=58840531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710031287.8A Active CN106628103B (en) | 2017-01-17 | 2017-01-17 | Nose landing gear force-bearing mechanism of ducted aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628103B (en) |
Citations (5)
| 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 |
| CN102639397A (en) * | 2009-07-15 | 2012-08-15 | 梅西耶-布加蒂-道提公司 | Nose gear of an aircraft comprising a single control device for retraction and steering |
| CN103847958A (en) * | 2012-11-30 | 2014-06-11 | 空中客车运营简化股份公司 | Device for intermediate fastening between aircraft fuselage and aircraft landing gear |
| 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 |
-
2017
- 2017-01-17 CN CN201710031287.8A patent/CN106628103B/en active Active
Patent Citations (5)
| 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 |
| CN102639397A (en) * | 2009-07-15 | 2012-08-15 | 梅西耶-布加蒂-道提公司 | Nose gear of an aircraft comprising a single control device for retraction and steering |
| CN103847958A (en) * | 2012-11-30 | 2014-06-11 | 空中客车运营简化股份公司 | Device for intermediate fastening between aircraft fuselage and aircraft landing gear |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628103B (en) | 2023-07-18 |
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