CN106379511B - A kind of integral type unmanned helicopter tail beam structure - Google Patents
A kind of integral type unmanned helicopter tail beam structure Download PDFInfo
- Publication number
- CN106379511B CN106379511B CN201611011871.9A CN201611011871A CN106379511B CN 106379511 B CN106379511 B CN 106379511B CN 201611011871 A CN201611011871 A CN 201611011871A CN 106379511 B CN106379511 B CN 106379511B
- Authority
- CN
- China
- Prior art keywords
- tail boom
- tail
- back segment
- stage casing
- integral type
- 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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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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)
- Remote Sensing (AREA)
- Excavating Of Shafts Or Tunnels (AREA)
Abstract
The present invention provides a kind of integral type unmanned helicopter tail beam structures, including integrally formed tail boom leading portion, tail boom stage casing, tail boom changeover portion and tail boom back segment；Tail boom leading portion is the trihedral structure being made of left side, right side and bottom mounting surfaces；Bottom mounting surfaces are made of high plane, low level face and arc transiting surface；Arc transiting surface is smoothly connected between high plane and low level face；Tail boom stage casing is the straight hollow pipe being connected between tail boom leading portion and tail boom changeover portion；Tail boom changeover portion is the smooth contraction hollow pipe being connected between tail boom stage casing and tail boom back segment；Tail boom back segment is straight hollow pipe, and U-lag mouth is equipped on the left side and right side of straight hollow pipe.The tail beam structure meets the demand of function and structure intensity simultaneously, saves overall volume and weight；Sufficiently large inner space is reserved to other mechanisms such as transmissions.
Description
Technical field
The present invention relates to a kind of tail boom structure, the unmanned helicopter tail beam structure of especially a kind of integral type.
Background technology
Unmanned helicopter is widely used in civil field at present, for example, agricultural plant protection, take photo by plane, high-altitude stringing, pipeline inspection,
The disaster relief, security protection etc..In actual use, load becomes the vital factor for influencing using effect.Therefore it goes straight up at nobody
In the design of machine structure, under the premise of ensureing housing construction intensity, need to reduce body weight as far as possible.
For traditional single rotor unmanned helicopter, tail boom is mainly used to transmit the anti-twisted power that tail-rotor generates, it is therefore desirable to
Enough structural strengths.It is internal simultaneously to need placement transmission system that power is transferred to tail-rotor, it is therefore desirable to which that certain inside is empty
Between.Simultaneously based on the considerations of pneumatic and good appearance, tail boom outer shape is preferably devised to smooth continuous.
Conventional in layout unmanned helicopter on the market at present, mostly uses simple open circles pillar tail pipe scheme, and some is outer
Covering is fixed in portion, to make its beautiful and optimizing pneumatic；Some directly abandons outer skin.This scheme cost is relatively low, still
Tail pipe, tail pipe covering, fastener etc. are needed, total weight is larger.Generally for loss of weight, tail pipe is thinner, and inner space is limited so that
Internal transmission part is placed narrow.In addition, tail pipe length is longer, cause radial rigidity usually insufficient, it usually needs slanting
Tail pipe supports to supplement rigidity.Tail pipe support not only further increases body weight, while the design for increasing tail pipe covering is difficult
Degree.In addition structure complexity is higher, more increases the global design difficulty of body.
Invention content
The technical problem to be solved by the present invention is to existing open circles pillar tail pipe there is complicated, weight it is big and
Covering is easy the problems such as damaged.
In order to solve the above technical problem, the present invention provides a kind of integral type unmanned helicopter tail beam structures, including one
Body formed tail boom leading portion, tail boom stage casing, tail boom changeover portion and tail boom back segment；Tail boom leading portion be by left side, right side with
And the trihedral structure that bottom mounting surfaces are constituted；Bottom mounting surfaces are made of high plane, low level face and arc transiting surface；Arc
Transition face is smoothly connected between high plane and low level face；Tail boom stage casing is to be connected between tail boom leading portion and tail boom changeover portion
Straight hollow pipe, and the one end in tail boom stage casing simultaneously connect with left side, right side and high plane, the other end in tail boom stage casing and
Tail boom changeover portion is connected；Tail boom changeover portion is the smooth contraction hollow pipe being connected between tail boom stage casing and tail boom back segment；Tail
Beam back segment is straight hollow pipe, and U-lag mouth is equipped on the left side and right side of straight hollow pipe.
The trihedral structure constituted using left side, right side and bottom mounting surfaces needs to be inserted into body when mounted
Interior, it can either be conducive to be bonded opening area affixed, and that front can be increased with organism frame, be conducive to fuselage interior biography
The design and installation of motivation structure；Bottom mounting surfaces are constituted using high plane, low level face and arc transiting surface, it can either be to body
The installation site of frame fixes, and can fit with organism frame, meets installation stability and reliability is wanted
It asks；Linking transition of the tail boom stage casing tail boom leading portion to tail boom back segment disclosure satisfy that using tail boom changeover portion, and pass through tail boom transition
The smooth contraction of section can effectively reduce the volume of tail boom, reduce the weight of tail boom；It is convenient using the tail boom back segment of straight hollow pipe
Tail-rotor tail rotor is driven and the installation of control mechanism；The installation of tail-rotor mechanism can be facilitated to fix using U-lag mouth.
As a further limited solution of the present invention, the top surface in tail boom stage casing and the top surface of tail boom changeover portion are curved in transitionality
Folding, and bending angle is between 175 ° ~ 165 °.Larger structural strength can be played using transitionality bending.
As a further limited solution of the present invention, side mounting hole is equipped on left side and right side.Using side
Mounting hole facilitates side installation to fix.
As a further limited solution of the present invention, bottom surface mounting hole is equipped on low level face.Using bottom surface mounting hole energy
Bottom surface installation is enough facilitated to fix.
As a further limited solution of the present invention, the left side and right side of tail boom back segment are equipped with tail end mounting hole.
Tail rotor transmission and control mechanism installation can be facilitated to fix using tail end mounting hole.
As a further limited solution of the present invention, high plane, the bottom surface in tail boom stage casing, tail boom changeover portion bottom surface and
The bottom surface of tail boom back segment is respectively positioned on same plane.The design can ensure the straightness of tail boom, it is ensured that the overall structure of tail boom
Intensity.
As a further limited solution of the present invention, the top edge of left side and right side is arc-shaped side.
As a further limited solution of the present invention, the bottom surface, left side of tail boom back segment and right side inner wall are flat
Face.It is provided with conducive to tail rotor transmission and the installation of control mechanism using plane.
As a further limited solution of the present invention, circumferential and axis is equipped on the inner wall of tail boom stage casing and tail boom changeover portion
To interlaced reinforcing rib.Material integrated molding can both have been met with the same carbon fiber of tail boom using reinforcing rib, also might be used
To make metalwork（Such as aluminium, steel）, it is pre-buried before tail boom molding, after curing molding.Increasing in this way can be with after reinforcing rib
The appropriate integral thickness for reducing integrated tail boom, further mitigates weight.
As a further limited solution of the present invention, crossbeam is equipped on the inner wall of tail boom back segment top surface, crossbeam connects tail
The left side of beam back segment and right side inner wall.Open-topped intensity missing is made up using crossbeam, crossbeam can use aluminium or carbon
Fiber composite material etc..
The beneficial effects of the present invention are：（1）The trihedral knot constituted using left side, right side and bottom mounting surfaces
Structure needs to be inserted into body when mounted, can either be conducive to be bonded with organism frame affixed, and can increase opening for front
Open area is conducive to the design and installation of fuselage interior transmission mechanism；（2）Using high plane, low level face and arc transiting surface
Bottom mounting surfaces are constituted, the installation site of organism frame can either be fixed, and can fit with organism frame,
Meet the requirement of installation stability and reliability；（3）It disclosure satisfy that tail boom stage casing tail boom leading portion to tail boom using tail boom changeover portion
The linking transition of back segment, and the smooth contraction for passing through tail boom changeover portion can effectively reduce the volume of tail boom, reduce the weight of tail boom
Amount；（4）Facilitate tail rotor transmission and the installation of control mechanism of tail boom back segment using the tail boom back segment of straight hollow pipe；（5）Using U
Shape notch can facilitate the installation of tail-rotor mechanism to fix.
Description of the drawings
Fig. 1 is the dimensional structure diagram one of the present invention；
Fig. 2 is the dimensional structure diagram two of the present invention；
Fig. 3 is the right side structural representation of the present invention.
In figure:1, tail boom leading portion, 2, tail boom stage casing, 3, tail boom changeover portion, 4, tail boom back segment, 5, left side, 6, high plane,
7, right side, 8, low level face, 9, arc transiting surface, 10, bottom surface mounting hole, 11, side mounting hole, 12, arc-shaped side, 13, U-lag
Mouthful, 14, tail end mounting hole.
Specific implementation mode
Technical solution of the present invention is described in detail below in conjunction with the accompanying drawings, but protection scope of the present invention is not limited to
The embodiment.
Before the present invention is with heading, tail direction illustrates after being.
As shown in Figs. 1-3, integral type unmanned helicopter tail beam structure disclosed by the invention, including before integrally formed tail boom
Section 1, tail boom stage casing 2, tail boom changeover portion 3 and tail boom back segment 4.
Wherein, tail boom leading portion 1 is the trihedral structure being made of left side 5, right side 7 and bottom mounting surfaces；Bottom
Mounting surface is made of high plane 6, low level face 8 and arc transiting surface 9；Arc transiting surface 9 is smoothly connected in high plane 6 and low level
Between face 8；Tail boom stage casing 2 is the straight hollow pipe being connected between tail boom leading portion 1 and tail boom changeover portion 3, and the one of tail boom stage casing 2
End is connect with left side 5, right side 7 and high plane 6 simultaneously, and the other end in tail boom stage casing 2 is connected with tail boom changeover portion 3；
Tail boom changeover portion 3 is the smooth contraction hollow pipe being connected between tail boom stage casing 2 and tail boom back segment 4；Tail boom back segment 4 is straight hollow
Pipe, and U-lag mouth 13 is equipped on the left side and right side of straight hollow pipe；The top surface in tail boom stage casing 2 and tail boom changeover portion 3
Top surface is bent in transitional, and bending angle is between 175 ° ~ 165 °, preferably 170 °；It is set on left side 5 and right side 7
There is side mounting hole 11；Bottom surface mounting hole 10 is equipped on low level face 8；The left side and right side of tail boom back segment 4 are equipped with tail
Hold mounting hole 14；High plane 6, the bottom surface in tail boom stage casing 2, the bottom surface of tail boom changeover portion 3 and tail boom back segment 4 bottom surface be respectively positioned on
On same plane；The top edge of left side 5 and right side 7 is arc-shaped side 12；Bottom surface, left side and the right side of tail boom back segment 4
Face inner wall is plane.
In order to further enhance structural strength, it is equipped on the inner wall of tail boom stage casing 2 and tail boom changeover portion 3 circumferential and axial
Interlaced reinforcing rib.Material integrated molding can both have been met with the same carbon fiber of tail boom using reinforcing rib, it can also
Make metalwork（Such as aluminium, steel）, it is pre-buried before tail boom molding, after curing molding.It can be fitted after increasing reinforcing rib in this way
When the integral thickness for reducing integrated tail boom, further mitigate weight.Crossbeam is equipped on the inner wall of 4 top surface of tail boom back segment, it is horizontal
Beam connects left side and the right side inner wall of tail boom back segment 4.Make up open-topped intensity missing using crossbeam, crossbeam can be with
With aluminium or carbon-fiber composite material etc..
Tail boom leading portion 1, tail boom stage casing 2, tail boom changeover portion 3 and the tail boom back segment 4 of the present invention is that an integral hollow is different
Type duct member, using carbon fibre composite one-pass molding.The top surface of tail boom leading portion 1 hollows out, and trihedral structure is conducive to and machine
The fitting of body frame is affixed, and there are several side mounting holes 11 for bolt fastening in tail boom front side, can also use bonding side
Three planes of tail boom front outsides are fixed on fuselage ring by formula, and the top surface of tail boom leading portion 1, which hollows out, increases front opening face
Product, is conducive to the design and installation of tail-rotor transmission mechanism, tail boom front is hidden in body, and appearance is invisible.
Tail boom changeover portion 3 is the hollow pipe seamlessly transitted, and tail-rotor mechanism is narrowed down to from the transition of fuselage ring connecting part
The middle part of installation position, tail boom changeover portion 3 is connected with unmanned helicopter shell, is integral part, and specific shape-designing can be with
It is adjusted according to shape.
Tail boom back segment 4 is tail-rotor mechanism installation position, the inside of tail boom back segment 4 from the 3 gradual transition of tail boom changeover portion be a left side
Three plane, baseplane and right plane planes are conducive to tail rotor transmission and the installation of control mechanism, left and right, the bottom at rear portion
Three planes have several tail end mounting holes 14 for bolt fastening, for fixing tail rotor transmission and control mechanism, tail boom
The outside at rear portion is adjusted according to moulded design, keeps the consistency with middle part and fuselage cover.
The design key of the tail boom of the present invention is：With an integrally formed unmanned helicopter tail beam structure instead of original
This covering that may be used, tail pipe, tail pipe support etc., while possessing structural support, appearance and modeling, outer skin optimizing pneumatic etc.
Function；Installation or affixed position are designed to plane, are conducive to installation positioning；Using carbon fibre composite, class Taper Pipe moulding, it is ensured that
Enough strength and stiffness；Tail pipe support is eliminated, the complexity and overall weight of structure are reduced；The integral type nobody go straight up to
Tail girder construction meets the demand of function and structure intensity simultaneously, saves overall volume and weight；To other machines such as transmissions
Structure reserves sufficiently large inner space.
As described above, although the present invention has been indicated and described with reference to specific preferred embodiment, must not explain
For the limitation to invention itself.It without prejudice to the spirit and scope of the invention as defined in the appended claims, can be right
Various changes can be made in the form and details for it.
Claims (10)
1. a kind of integral type unmanned helicopter tail beam structure, including integrally formed tail boom leading portion (1), tail boom stage casing (2), tail boom
Changeover portion (3) and tail boom back segment (4), it is characterised in that：Tail boom leading portion (1) is by left side (5), right side (7) and bottom
The trihedral structure that portion's mounting surface is constituted；Bottom mounting surfaces are by high plane (6), low level face (8) and arc transiting surface (9) structure
At；Arc transiting surface (9) is smoothly connected between high plane (6) and low level face (8)；Tail boom stage casing (2) is before being connected to tail boom
Section (1) and tail boom changeover portion (3) between straight hollow pipe, and the one end of tail boom stage casing (2) at the same with left side (5), right side
(7) and high plane (6) connection, the other end of tail boom stage casing (2) are connected with tail boom changeover portion (3)；Tail boom changeover portion (3) is
The smooth contraction hollow pipe being connected between tail boom stage casing (2) and tail boom back segment (4)；Tail boom back segment (4) is straight hollow pipe, and
The left side and right side of straight hollow pipe are equipped with U-lag mouth (13).
2. integral type unmanned helicopter tail beam structure according to claim 1, it is characterised in that：The top in tail boom stage casing (2)
Face and the top surface of tail boom changeover portion (3) are bent in transitional, and bending angle is between 175 °~165 °.
3. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：In left side (5) and
Right side (7) is equipped with side mounting hole (11).
4. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：On low level face (8)
Equipped with bottom surface mounting hole (10).
5. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：Tail boom back segment (4)
Left side and right side are equipped with tail end mounting hole (14).
6. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：High plane (6), tail
The bottom surface of the bottom surface in beam stage casing (2), the bottom surface of tail boom changeover portion (3) and tail boom back segment (4) is respectively positioned on same plane.
7. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：Left side (5) and the right side
The top edge of side (7) is arc-shaped side (12).
8. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：Tail boom back segment (4)
Bottom surface, left side and right side inner wall are plane.
9. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：In tail boom stage casing (2)
It is equipped with circumferential and axial interlaced reinforcing rib with the inner wall of tail boom changeover portion (3).
10. integral type unmanned helicopter tail beam structure according to claim 1 or 2, it is characterised in that：In tail boom back segment
(4) inner wall of top surface is equipped with crossbeam, and crossbeam connects left side and the right side inner wall of tail boom back segment (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611011871.9A CN106379511B (en) | 2016-11-17 | 2016-11-17 | A kind of integral type unmanned helicopter tail beam structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611011871.9A CN106379511B (en) | 2016-11-17 | 2016-11-17 | A kind of integral type unmanned helicopter tail beam structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106379511A CN106379511A (en) | 2017-02-08 |
| CN106379511B true CN106379511B (en) | 2018-10-30 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611011871.9A Expired - Fee Related CN106379511B (en) | 2016-11-17 | 2016-11-17 | A kind of integral type unmanned helicopter tail beam structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN106379511B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202012002493U1 (en) * | 2012-03-13 | 2012-06-12 | Eurocopter Deutschland Gmbh | helicopter tail |
| CN103097244A (en) * | 2010-09-20 | 2013-05-08 | 贝尔直升机泰克斯特龙公司 | Airfoil shaped tail boom |
| CN104309813A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Design method for shape of helicopter tail beam |
| CN205366073U (en) * | 2016-01-29 | 2016-07-06 | 上海翔鸿无人飞行器导航控制技术有限公司 | Integrated into one piece unmanned aerial vehicle carbon fiber horn |
| CN206384134U (en) * | 2016-11-17 | 2017-08-08 | 常州弧光航空科技有限公司 | A kind of integral type depopulated helicopter tail beam structure |
-
2016
- 2016-11-17 CN CN201611011871.9A patent/CN106379511B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103097244A (en) * | 2010-09-20 | 2013-05-08 | 贝尔直升机泰克斯特龙公司 | Airfoil shaped tail boom |
| DE202012002493U1 (en) * | 2012-03-13 | 2012-06-12 | Eurocopter Deutschland Gmbh | helicopter tail |
| CN104309813A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Design method for shape of helicopter tail beam |
| CN205366073U (en) * | 2016-01-29 | 2016-07-06 | 上海翔鸿无人飞行器导航控制技术有限公司 | Integrated into one piece unmanned aerial vehicle carbon fiber horn |
| CN206384134U (en) * | 2016-11-17 | 2017-08-08 | 常州弧光航空科技有限公司 | A kind of integral type depopulated helicopter tail beam structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106379511A (en) | 2017-02-08 |
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Granted publication date: 20181030 Termination date: 20201117 |