CN106507756B - High-strength light unmanned plane vertical fin - Google Patents
High-strength light unmanned plane vertical finInfo
- Publication number
- CN106507756B CN106507756B CN200910123679.2A CN200910123679A CN106507756B CN 106507756 B CN106507756 B CN 106507756B CN 200910123679 A CN200910123679 A CN 200910123679A CN 106507756 B CN106507756 B CN 106507756B
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- CN
- China
- Prior art keywords
- fin
- fixed fin
- unmanned plane
- rudder
- vertical fin
- 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.)
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Abstract
A kind of high-strength light unmanned plane vertical fin proposed by the present invention, it is desirable to provide a kind of simple structure, number of parts are few, rigidity are high, lightweight, the unmanned plane vertical fin structure that rudder can be dismantled again.The PMI foam plasticss core filled composite material thin skins that its fixed fin is combined by piecemeal are constituted, the tail supporting rod being made up of composite material thin wall pipe passes through sleeve connection fixed fin, rudder is detachably connected fixed fin by being axially inserted into connector without protruding profile.The present invention is used, and is supported the foam plasticss sandwich of composite thin skin to bear aerodynamic loading, is not likely to produce and agitates and deform, can bear the shearing produced by aerodynamic loading.Vertical fin number of parts is few, lightweight, compares the vertical fin loss of weight 8% of the composite structure with inner skeleton, and number of parts reduces 56%, and rigidity is doubled.
Description
Technical field
The present invention relates to a kind of lightweight, simple unmanned plane vertical fin structure.
Background technology
Vertical fin is to be used for the part of directional control and balance on aircraft, be that aerodynamic loading is big, structure space is small,
The high important Pneumatic component of rigidity requirement.The unmanned plane vertical fin of Bi-Tail-Boom Layout leads to common metal or composite,
And carry the tail supporting rod of elongated thin-wall circular tube to increase the arm of force of empennage, improve driving efficiency.Tail supporting rod is whole
Structure is most simple in individual vertical fin, and stress is maximum, connection fixed fin, produced by transmission vertical fin and horizontal tail
The component of aerodynamic loading.
The unmanned plane of more early type typically constitutes tail fixed fin using the skeletons such as aluminum alloy beams, rib and covering,
The unmanned plane vertical fin of newer type then replaces aluminium alloy to constitute fixed fin with composite.Due to tail supporting rod knot
Structure is simple, and fixed fin complex structure, and both complex degree of structure great disparities are larger, generally with more multiple
Miscellaneous structure could be connected.Small-sized SUAV rudder, the connection of perpendicular stabilization is led to
Frequently with two ways：1. the non-removable connection of rudder, joint is directly embedded in fixed fin, and
Ensure the connector without the theoretical profile of protrusion；2. ensure that rudder is detachable, using the connection of the theoretical profile of protrusion
Part.In general, two ways is extremely difficult to take into account, the problem of attending to one thing and lose sight of another is constantly present.
At present, this fixed fin being made up of inner skeleton and covering, because covering is only in beam, rib etc.
There is support at skeleton, not only the part such as beam, rib and its connector quantity is more, weight big, assembling is complicated, and
And to prevent covering stress unstability, in addition it is also necessary to strengthen support strength with larger skin thickness, so as to cause
Weight increase.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of simple in construction, and number of parts is few, and rigidity is high,
It is lightweight, the unmanned plane vertical fin structure that rudder can be dismantled again.
In order to solve the above technical problems, the present invention proposes a kind of high-strength light unmanned plane vertical fin, including vertical peace
Determine face and rudder and tail supporting rod, it is characterised in that the PMI foamed plastics that fixed fin is combined by piecemeal
Sandwich integral coating composite thin skin is constituted, and the tail supporting rod being made up of composite material thin wall pipe passes through set
Cylinder connection fixed fin, sleeve 4 is coaxially assemblied in the thin-wall circular tube of tail supporting rod 1, and tail supporting rod 1 passes through set
The leading portion gemel connection of cylinder is integrated, and the back segment of sleeve 4 is glued solid with the wall thickness inner chamber fit of fixed fin 2
Connection；The rudder being movably connected with fixed fin 2, by without the protrusion axial rotating shaft (8) of profile and upper
The leaf of hinge 9 that end is connected firmly, 2 points of connection fixed fins 2, leaf of hinge 9 is inserted in fixed fin trailing edge
Groove part 10 in, and along groove slide downward, above-mentioned rotating shaft 8 is inserted in fixed fin root turning
In axis hole bushing 11 in plane.
The composite thin skin of described fixed fin, be by carbon cloth and resin matrix solidification institute into；
The piecemeal combination PMI foam cores of described fixed fin, by through digital control processing, different densities and by force
Upper and lower two blocks of PMI foamed plastics of degree are combined.Foam core utilizes composite when covering solidifies
Matrix resin in thin skin is directly solidified togather with composite thin skin, at the same complete top foam with
The solidification of glued membrane between the foam of bottom.
The present invention has following good effect compared to prior art.
The present invention is vertical by sleeve connection with the part of a simple composite material thin wall circular tube structure tail supporting rod
Stabilization, that is, realize the connection of tail supporting rod and fixed fin, transmission is hung down, horizontal tail is produced all shearings,
Moment of flexure and moment of torsion.Both ensure that has enough bonding strengths between fixed fin and tail supporting rod, alleviate again
The weight of fixed fin.
The fixed fin surface topography of composite material skin is smooth, internal integrally-built foam core support
Composite thin skin, bears shearing produced by aerodynamic loading, aerodynamic loading, and when bearing aerodynamic force,
It is not likely to produce and agitates and deform.The less fixed fin top itself of stress is born with the less foam of density
Aerodynamic loading, and bear with the reinforcement foam that foam density is larger, intensity is higher larger vertical stable of stress
Itself aerodynamic loading of face bottom, the horizontal tail load and rudder steering wheel load of the transmission of horizontal tail joint, its intensity foot
The concentrfated load produced is transmitted to meet horizontal tail rear adapter, steering wheel bearing, rudder rotating axle bushing.Both increased
Add the strength and stiffness of fixed fin, also reduce the weight of itself.It is this to be covered by light composite material
The interlayer unmanned plane vertical fin of skin and foam core composition, with very high intensity and toughness.And due to being only 0.3mm
The covering of thickness, density is only 50kg/m3~200kg/m3Foamed plastics supporting framework, total weight very little
Vertical fin, compared to the composite structure vertical fin loss of weight 20% with inner skeleton, number of parts reduces 50%,
Rigidity is doubled.
The connection of rudder and fixed fin passes through the axle of lower end by the way of being axially inserted into the present invention
Hole coordinates and upper end leaf of hinge forms dismountable 2 points of connections, and lower end limits rudder flat perpendicular to axis
Two translation freedoms in face, upper end leaf of hinge is limited to the axially translated free degree of rudder and except pivoting
Outside 2 rotational freedoms, rudder is only remained a rotational freedom around axle, the not only side of ensure that
It is detachable to this small size rudder face of rudder (long 300mm, mean breadth 50mm, average thickness 5mm),
And it ensure that the connection of rudder and fixed fin without any object for protruding from profile.
Brief description of the drawings
Fig. 1 is that schematic perspective view cuts open in the office of high-strength light unmanned plane vertical fin of the present invention.
Fig. 2 is the installation decomposing schematic representation of rudder in Fig. 1.
In figure：1 tail supporting rod, 2 fixed fins, 3 rudders, 4 sleeves, 5 coverings, 6 top foams,
7 bottom foams, 8 rotating shafts, 9 leaf of hinge, 10 groove parts, 11 axis hole bushings.
Embodiment
With reference to embodiment, the invention will be further described.
Refering to Fig. 1, in the unmanned plane vertical fin being made up of tail supporting rod 1, fixed fin 2 and rudder 3,
Connected between tail supporting rod 1 and fixed fin 2 by sleeve 4.Tail supporting rod 1 is by composite material thin wall
Pipe is constituted.Sleeve 4 is coaxially assemblied in the thin-wall circular tube of tail supporting rod 1.The leading portion that tail supporting rod 1 passes through sleeve
Gemel connection is integrated, and the back segment of sleeve 4 is glued with the wall thickness inner chamber fit of fixed fin 2 to be connected firmly.Bag is carried out
Composite thin skin 5 on fixed fin 2, is fine with one layer of prepreg carbon that thickness is 0.3mm
Wei Bu is plated in co-curing formation on mould.Wherein, the piecemeal PMI processed according to fixed fin Varying-thickness
Foamed plastics sandwich, the inside that piecemeal is combined and integrally laminating is glued to composite thin skin 5.Positioned at vertical
The piecemeal PMI foamed plastics sandwiches foam 6 on the straight top of stabilization 2, is the PMI foamed plastics compared with low-density,
Piecemeal PMI foamed plastics sandwiches foam 7 positioned at the bottom of fixed fin 2, is the PMI bubbles of higher density
Foam plastics.Above-mentioned PMI foamed plastics sandwich is the made of one piece structure of digital control processing.Top foam 6 is with
Glued membrane is filled between portion's foam 7, using the matrix resin in covering by composite thin skin 5 and foam plastic
Material is glued together.When composite 5 solidified forming of thin skin, while completing top foam 6 and bottom
The solidification of glued membrane is filled between foam 7, is allowed to form complete fixed fin.That is, a work
Skill process completes the solidification of glued membrane between foam, and the solidification between foam, covering, and covering itself simultaneously
Solidification.
Refering to Fig. 2, the rudder 3 being movably connected with fixed fin 2 is with being axially inserted into rudder 3
The rotating shaft 8 in the hole of axis hole bushing 11, and the leaf of hinge 9 that upper end is connected firmly, 2 points connect fixed fin 2.
Leaf of hinge 9 is inserted in the groove part 10 of fixed fin trailing edge, and along groove slide downward, by above-mentioned turn
Axle 8 is inserted in the axis hole bushing 11 in the plane of fixed fin root turning.The rivet interlacement of leaf of hinge 9 in
On fixed fin trailing edge groove part, the flexible connection of detachable is formed.So, the leaf of hinge 9 of upper end is just
The translation freedoms of rudder 3 vertically and two rotational freedoms in addition to pivoting are limited, are made
Rudder 3 remains a rotational freedom around axle.It not only ensure that this small size rudder face of rudder is (long
300mm, mean breadth 50mm, average thickness 5mm) it is detachable, while also ensure that rudder with
Fixed fin connection without any object form for protruding from profile.
Claims (4)
1. a kind of high-strength light unmanned plane vertical fin, including fixed fin and rudder and tail supporting rod, its feature
It is, the PMI foamed plastics sandwich integral coating composite thin skin groups that fixed fin is combined by piecemeal
Into the tail supporting rod being made up of composite material thin wall pipe is by sleeve connection fixed fin, and sleeve (4) is same
Axle is assemblied in tail supporting rod (1) thin-wall circular tube, and tail supporting rod (1) is integrated by the leading portion gemel connection of sleeve,
The back segment of sleeve (4) is glued with the wall thickness inner chamber fit of fixed fin (2) to be connected firmly；With fixed fin
(2) rudder being movably connected, the conjunction connected firmly by the axial rotating shaft (8) without protrusion profile and upper end
Hinge (9), 2 points of connection fixed fins (2), leaf of hinge (9) is inserted in the recessed of fixed fin trailing edge
In slotware (10), and along groove slide downward, above-mentioned rotating shaft (8) is inserted in fixed fin root and turned
In axis hole bushing (11) on angle plane.
2. high-strength light unmanned plane vertical fin according to claim 1, it is characterised in that：Described is compound
Material thin skin (5), its laying is only 1 layer of carbon fibre fabric.
3. high-strength light unmanned plane vertical fin as claimed in claim 1, it is characterised in that：Positioned at vertical stable
The top foam (6) on face (2) top, is the PMI foamed plastics compared with low-density；Positioned at fixed fin (2)
The piecemeal bottom foam (7) of bottom, is the PMI foamed plastics of higher density.
4. high-strength light unmanned plane vertical fin as claimed in claim 3, it is characterised in that：Top foam (6)
It is to be glued by filling glued membrane between bottom foam (7), using the matrix resin in covering by composite
Thin skin is glued together with foamed plastics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910123679.2A CN106507756B (en) | 2009-11-13 | 2009-11-13 | High-strength light unmanned plane vertical fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910123679.2A CN106507756B (en) | 2009-11-13 | 2009-11-13 | High-strength light unmanned plane vertical fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106507756B true CN106507756B (en) | 2013-12-11 |
Family
ID=58358266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910123679.2A Active CN106507756B (en) | 2009-11-13 | 2009-11-13 | High-strength light unmanned plane vertical fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106507756B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110789708A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Helicopter rear horizontal tail wing structure with support rod |
| CN112572768A (en) * | 2020-12-18 | 2021-03-30 | 中国电子科技集团公司第三十八研究所 | Control mechanism of full-motion vertical fin of unmanned aerial vehicle |
| CN113830279A (en) * | 2021-11-09 | 2021-12-24 | 中国电子科技集团公司第三十八研究所 | Propeller electric propulsion device for adjusting posture of airship |
| CN114408155A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Horizontal tail fuselage butt-joint structure of small-sized general aircraft |
-
2009
- 2009-11-13 CN CN200910123679.2A patent/CN106507756B/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110203373B (en) * | 2019-05-24 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Structure is dismantled to unmanned aerial vehicle tail of hanging down |
| CN110789708A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Helicopter rear horizontal tail wing structure with support rod |
| CN110789708B (en) * | 2019-10-12 | 2023-06-23 | 哈尔滨飞机工业集团有限责任公司 | Rear horizontal tail structure of helicopter with stay bar |
| CN112572768A (en) * | 2020-12-18 | 2021-03-30 | 中国电子科技集团公司第三十八研究所 | Control mechanism of full-motion vertical fin of unmanned aerial vehicle |
| CN113830279A (en) * | 2021-11-09 | 2021-12-24 | 中国电子科技集团公司第三十八研究所 | Propeller electric propulsion device for adjusting posture of airship |
| CN114408155A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Horizontal tail fuselage butt-joint structure of small-sized general aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent |