CN206466156U - The nose-gear load mechanism of duct aircraft - Google Patents
The nose-gear load mechanism of duct aircraft Download PDFInfo
- Publication number
- CN206466156U CN206466156U CN201720054129.XU CN201720054129U CN206466156U CN 206466156 U CN206466156 U CN 206466156U CN 201720054129 U CN201720054129 U CN 201720054129U CN 206466156 U CN206466156 U CN 206466156U
- Authority
- CN
- China
- Prior art keywords
- support arm
- sole
- nose
- longitudinal support
- tripod
- 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.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of nose-gear load mechanism of duct aircraft, is assembled on sole, including horizontal support arm, longitudinal support arm, the first locking part and the second locking part.Horizontal support arm group separates support arm and tripod is separated out into left tripod and right tripod in sole and with support arm and tripod is separated；The front bottom end of longitudinal support arm offers buckling groove and rear end has junction surface, the front end of longitudinal support arm is buckled in sole from top to bottom by buckling groove, the rear end of longitudinal support arm is engaged at separation support arm by junction surface, and the nose-gear of duct aircraft is assembled at longitudinal support arm；Left and right directions of first locking part along sole is placed through front end and sole and lock longitudinal support arm and the sole of longitudinal support arm；Left and right directions of second locking part along sole is placed through junction surface with the junction surface that separates at support arm and lock with separating support arm, it is ensured that the reliability of rising and falling of nose-gear, also has the advantages that simple in construction.
Description
Technical field
The utility model is related to a kind of aircraft, more particularly to a kind of duct aircraft nose-gear load mechanism.
Background technology
As economic continues to develop and social continuous progress, the various consumer goods are provided for the life of people,
To meet the various material requisites of people, and duct aircraft is exactly 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, and duct aircraft is very by family
The fan of outer motion is favored.
At present, in existing duct aircraft, because the component of the bearing of its nose-gear is various, so that existing
Complicated, the assembling inconvenience of some bearings, and suffered impact capacity is limited, it is impossible to effectively ensure that rise and fall reliable
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.
Utility model content
The purpose of this utility model is the nose-gear load mechanism for providing a kind of duct aircraft, its is simple in construction,
Load is reliable and security is good.
To achieve the above object, the technical solution of the utility model is：A kind of nose-gear of duct aircraft is provided to hold
On force mechanisms, the sole for being assembled in duct aircraft.Wherein, the nose-gear load mechanism of the duct aircraft includes horizontal stroke
To support arm, longitudinal support arm, the first locking part and the second locking part.Right and left of the horizontal support arm along the sole
To being assembled on the sole, the middle part of the horizontal support arm has tripod, and the top of the tripod is upwardly disposed,
The separation that the middle part of the horizontal support arm is also extended the top for extending the tripod and struck up partnership with the top is supported
The tripod is separated out left tripod and right tripod by arm, the separation support arm；Longitudinal support arm is along the bottom
The fore-and-aft direction arrangement of plate rail, the front bottom end of longitudinal support arm offers buckling groove, the rear end of longitudinal support arm
With the junction surface engaged with the separation support arm, the front end of longitudinal support arm is detained from top to bottom by the buckling groove
At the sole, the rear end of longitudinal support arm is engaged at the separation support arm by the junction surface, institute
The nose-gear for stating duct aircraft is assembled at longitudinal support arm；Left and right of first locking part along the sole
Direction is placed through front end and the sole and lock longitudinal support arm and the sole of longitudinal support arm；Described
Left and right directions of two locking parts along the sole is placed through the junction surface with being connect at the separation support arm and described in locking
Conjunction portion and 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 comprising cooperate the first bolt and the first nut, first bolt from
Direction is turned right on the left of the sole through the front end of longitudinal support arm and sole, 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 comprising cooperate the second bolt and the second nut, second bolt from
Turned 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 for 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 is extended back
Preceding pipe joint and tube head is followed by, the horizontal support arm is by the preceding pipe joint and is followed by tube head and the sole grafting.
It is preferred that the support arm and the intersection of the tripod of separating is arc structure.
Compared with prior art, held because nose-gear load mechanism of the present utility model includes horizontal support arm, longitudinal direction
The arm of force, the first locking part and the second locking part, buckling groove and junction surface by longitudinal support arm, and the first locking part and
Two locking parts so that be assembled in longitudinal support arm energy more convenient and quicker at sole and horizontal support arm, so that this practicality
The assembling of new nose-gear load mechanism is more convenient.Again because the middle part of horizontal support arm has tripod, tripod
Top is upwardly disposed, and the top for extending tripod and the separation struck up partnership with the top are also extended in the middle part of horizontal support arm
Support arm, separates support arm and tripod is separated out into left tripod and right tripod, and the front end of longitudinal support arm passes through first
Locking part is locked together with sole, and the junction surface of the rear end of longitudinal support arm is locked by the second locking part with separating support arm
Gu yielding characteristic together, is not allowed according to triangle, so that longitudinal support arm can more reliably be fixed on and laterally hold
On the arm of force and sole, it is produced to upthrust in landing to alleviate nose-gear to greatest extent, and the first locking part and
Second locking part is in by scissor state under upward momentum effect, so that what the first locking part and the second locking part were born
It is bigger to upthrust, and then reliability when nose-gear rises and falls is improved, thereby, it is ensured that the security that duct aircraft rises and falls.
Brief description of the drawings
Fig. 1 is that the nose-gear load mechanism of duct aircraft of the present utility model is assembled in the stereochemical structure at sole
Schematic diagram.
Stereo decomposing when Fig. 2 is nose-gear load mechanism and the sole phase separation of the duct aircraft shown in Fig. 1
Structural representation.
Fig. 3 is nose-gear load mechanism, nose-gear and the front-wheel three assembling of duct aircraft of the present utility model
Dimensional structure diagram when together.
Fig. 4 is the dimensional structure diagram of the nose-gear load mechanism of duct aircraft of the present utility model.
Fig. 5 is the dimensional decomposition structure diagram of the nose-gear load mechanism of duct aircraft of the present utility model.
Embodiment
Element numbers similar in embodiment of the present utility model, accompanying drawing, which are described, with reference now to accompanying drawing represents similar member
Part.
Fig. 1 and Fig. 2 is referred to, the nose-gear load mechanism 100 of duct aircraft of the present utility model is assembled in duct
On the sole 200 of aircraft, installation support is provided by sole 200.Wherein, nose-gear load mechanism of the present utility model
100 include horizontal support arm 10, longitudinal support arm 20, the first locking part 30 and the second locking part 40.Horizontal support arm 10 is the bottom of along
The left and right directions of plate rail 200 is assembled on sole 200, is that horizontal support arm 10 provides installation support by sole 200；Laterally
The middle part of support arm 10 has tripod 11, and the top of tripod 11 is upwardly disposed, prevents the top of tripod 11 because of cloth down
Put and cause the structure bulky of sole 200；The middle part of horizontal support arm 10 also extend the top that extends tripod 11 and with
The separation support arm 12 that the top strikes up partnership, separates support arm 12 and tripod 11 is separated out into left tripod 11a and right triangle
Frame 11b；Specifically, in the present embodiment, separate support arm 12 and vertically divide tripod 11 equally so that left tripod 11a and the right side three
Corner bracket 11b's is in the same size, so that the impulsive force that tripod 11 is born is bigger, but is not limited.In order to improve horizontal stroke
To support arm 10 and the convenience of the assembling and dismantling of sole 200, therefore position of the horizontal support arm 10 outside the corner of tripod 11 is divided
Pipe joint 14 and tube head 15 is followed by not forward and before extending back so that horizontal support arm 10 is by preceding pipe joint 14 and is followed by
Tube head 15 and the grafting of sole 200, realize that horizontal support arm 10 is connected with the threeway of sole 200, but be not limited；In order to
So that the stress concentration of the corner of tripod 11 is smaller, therefore the intersection for separating support arm 12 and tripod 11 is arc structure
13, so that the connection separated between support arm 12 and tripod 12 is more reliable, and then ensure reliability when undercarriage lands.
As shown in Figures 3 to 5, before fore-and-aft direction arrangement of longitudinal support arm 20 along sole 200, longitudinal support arm 20
End bottom offers buckling groove 21, and the rear end of longitudinal support arm 20 has with separating the junction surface 22 that support arm 12 is engaged, longitudinal direction
The front end of support arm 20 is fastened at sole 200 from top to bottom 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 support, and separate share three arms of angle of the support arm 12 for left tripod 11a and right tripod 11b, it is difficult by triangle
The characteristic of change, so that longitudinal support arm 20 can bear bigger power of going out in the case where separating the support of support arm 12, thus more
It 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, 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；For example, at this
In embodiment, the specific assembling process of longitudinal support arm 20 is：The junction surface 22 of longitudinal support arm 20 is first set to plant from front to back
In 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.The front end of longitudinal support arm 20 and sole 200 are locked by the first locking part 30 again, and by the second locking part 40
The junction surface 22 of longitudinal support arm 20 is locked with separating support arm 12, thus realizes the mesh of the quick assembling of longitudinal support arm 20
, but be not limited.
As shown in Figures 1 to 5, left and right directions of first locking part 30 along sole 200 is placed through longitudinal support arm 20
Front end and sole 200 and lock longitudinal support arm 20 and sole 200, to be 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 includes the first bolt 31 and first cooperated
Nut 32, the left side of the first bolt 31 from sole 200 direction of turning right passes through front end and the sole of longitudinal support arm 20
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
Connection between sole 200 is more reliable, 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, effectively prevents 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 is penetrated, and is threadedly coupled again with helicitic texture 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, left and right directions of second locking part 40 along sole 200 is placed through junction surface 22 and separation
At the support arm 12 and junction surface 22 that locks is with separating support arm 12, to selectively allow 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 cooperated and
Second nut 42, the left side of the second bolt 41 from sole 200 turn right direction pass through longitudinal support arm 20 junction surface 22 and
Separate support arm 12, the second nut 42 screws in the second bolt 41 and longitudinal support arm 20 that locks together with second bolt 41 connects
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 for obtaining the junction surface 22 of longitudinal support arm 20 and separating between support arm 12 is more reliable, therefore second
Locking part 40 is also comprising the second packing ring 43 for being placed through on the second bolt 41 and being locked by the second nut 42, to pass through second packing ring
43 go to improve shock resistance, effectively prevent the accident of the second nut 42 and the second bolt 41 from coming off, but be 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 in screw from the side without helicitic texture at the junction surface 22 of longitudinal support arm 20, is passed through
Separate support arm 12 to be threadedly coupled with helicitic texture again, can equally realize the junction surface 22 of the longitudinal support arm 20 of screw locking with dividing
Every the purpose of support arm 12, but it is not limited.
Compared with prior art, horizontal support arm 10 is included due to nose-gear load mechanism 100 of the present utility model, it is vertical
To support arm 20, the first locking part 30 and the second locking part 40, buckling groove 21 and junction surface 22 by longitudinal support arm 20, with
And first 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
At horizontal support arm 10, so that the assembling of nose-gear load mechanism 100 of the present utility model is more convenient.Again due to laterally holding
The middle part of the arm of force 10 has tripod 11, and the top of tripod 11 is upwardly disposed, and the middle part of horizontal support arm 10, which is also extended, stretches
The separation support arm 12 struck up partnership to the top of tripod 11 and with the top, separates support arm 12 and is separated out tripod 11
Left tripod 11a and right tripod 11b, and the front end of longitudinal support arm 20 is locked by the first locking part 30 and sole 200
Together, the junction surface 22 of the rear end of longitudinal support arm 20 is locked together by the second locking part 40 with separating support arm 12,
Yielding characteristic is not allowed according to triangle so that longitudinal support arm 20 can more reliably be fixed on horizontal support arm 10 with
On sole 200, it is produced to upthrust in landing to alleviate nose-gear to greatest extent, and the first locking part 30 and the
Two locking parts 40 are in by scissor state under upward momentum effect, so that the first locking part 30 and the second locking part 40 are held
That receives is bigger to upthrust, and then improves reliability when nose-gear rises and falls, thereby, it is ensured that the safety that duct aircraft rises and falls
Property.
Upper disclosed only preferred embodiment of the present utility model, can not limit the utility model with this certainly
Interest field, therefore equivalent variations made according to present utility model application the scope of the claims still belong to what the utility model was covered
Scope.
Claims (8)
1. on a kind of nose-gear load mechanism of duct aircraft, the sole for being assembled in duct aircraft, it is characterised in that
The nose-gear load mechanism of the duct aircraft includes：
Horizontal support arm, is assembled on the sole along the left and right directions of the sole, the middle part of the horizontal support arm
With tripod, the top of the tripod is upwardly disposed, and the middle part of the horizontal support arm, which is also extended, 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, is arranged, the front bottom end of longitudinal support arm offers fastening along the fore-and-aft direction of the sole
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 of longitudinal support arm is placed through with the sole simultaneously along the left and right directions of the sole
Lock longitudinal support arm and sole；And
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 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 support
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 support
Arm offers the separation trough matched with the junction surface, and the junction surface is inserted in the separation trough from front to back.
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 and the first nut cooperated, and first bolt direction of being turned right on 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 and the second nut cooperated, and second bolt direction of being turned right on 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 pipe joint and is followed by tube head respectively forwardly and before extending back, the transverse direction
Support arm is by the preceding pipe joint and is followed by tube head and the sole grafting.
8. the nose-gear load mechanism of duct aircraft according to claim 1, it is characterised in that the separation support
The intersection of arm and the tripod is arc structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054129.XU CN206466156U (en) | 2017-01-17 | 2017-01-17 | The nose-gear load mechanism of duct aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054129.XU CN206466156U (en) | 2017-01-17 | 2017-01-17 | The nose-gear load mechanism of duct aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206466156U true CN206466156U (en) | 2017-09-05 |
Family
ID=59706233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720054129.XU Expired - Fee Related CN206466156U (en) | 2017-01-17 | 2017-01-17 | The nose-gear load mechanism of duct aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206466156U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628103A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Front landing gear bearing mechanism of ducted air vehicle |
| US10940917B2 (en) | 2016-09-12 | 2021-03-09 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| US10946939B1 (en) | 2020-04-22 | 2021-03-16 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11485457B1 (en) | 2021-06-14 | 2022-11-01 | Kai Concepts, LLC | Hydrojet propulsion system |
| US11878775B2 (en) | 2021-07-13 | 2024-01-23 | Kai Concepts, LLC | Leash system and methods of use |
| US11897583B2 (en) | 2020-04-22 | 2024-02-13 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propulsion system |
-
2017
- 2017-01-17 CN CN201720054129.XU patent/CN206466156U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10940917B2 (en) | 2016-09-12 | 2021-03-09 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| US11479324B2 (en) | 2016-09-12 | 2022-10-25 | Kai Concepts, LLP | Watercraft device with hydrofoil and electric propeller system |
| US11919608B2 (en) | 2016-09-12 | 2024-03-05 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propeller system |
| CN106628103A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Front landing gear bearing mechanism of ducted air vehicle |
| US10946939B1 (en) | 2020-04-22 | 2021-03-16 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11091232B1 (en) | 2020-04-22 | 2021-08-17 | Kai Concepts, LLC | Watercraft having a waterproof container and a waterproof electrical connector |
| US11801919B2 (en) | 2020-04-22 | 2023-10-31 | Kai Concepts, LLC | Waterproof container having a waterproof electrical connector |
| US11897583B2 (en) | 2020-04-22 | 2024-02-13 | Kai Concepts, LLC | Watercraft device with hydrofoil and electric propulsion system |
| US11485457B1 (en) | 2021-06-14 | 2022-11-01 | Kai Concepts, LLC | Hydrojet propulsion system |
| US11878775B2 (en) | 2021-07-13 | 2024-01-23 | Kai Concepts, LLC | Leash system and methods of use |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170905 Termination date: 20220117 |