CN204822056U - Combined material aileron structure - Google Patents
Combined material aileron structure Download PDFInfo
- Publication number
- CN204822056U CN204822056U CN201520344452.1U CN201520344452U CN204822056U CN 204822056 U CN204822056 U CN 204822056U CN 201520344452 U CN201520344452 U CN 201520344452U CN 204822056 U CN204822056 U CN 204822056U
- Authority
- CN
- China
- Prior art keywords
- trailing edge
- leading edge
- rib
- covering
- aileron
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model provides a combined material aileron structure, include: under covering (9), the trailing edge covering (10), trailing edge overall height degree foam (11), left side trailing edge tip rib (12) on left side leading edge tip rib (2), the ordinary rib of leading edge (3), spar (4), leading edge covering (5), right side leading edge tip rib (6), right side trailing edge tip rib (8), the trailing edge, aileron structure pass through the left side and connect support (1) and be connected with outside wing with right side connection support (7). The utility model provides a dismantlement problem of leading edge opening problem and aileron to realize the pure splicing connection of leading edge covering, guaranteed the integrality of aileron structure outward appearance, improved leading edge rigidity, and solved the adhesive strength problem that the normal atmospheric temperature secondary splices by a large scale.
Description
Technical field
The utility model relates to a kind of composite aileron structure, is specially adapted to big-and-middle-sized low-speed unmanned aerial vehicle aileron structure.
Background technology
, there is a large amount of full-height sandwich structure in aileron structure of the prior art, but is all realized the ability to dismantle of aileron by the connection between dismounting aileron and coercive mechanism; In order to provide the withdrawal space of aileron and coercive mechanism, skins front edges is hatch frame, must arrange again lid or arrange larger exposed gap, on the one hand at coercive mechanism place, destroy the complete appearance of aileron structure, on the other hand, skins front edges to be divided in leading edge covering two parts under covering and leading edge, in order to meet leading edge rigidity requirement by opening, skins front edges is thicker, must use a large amount of rivet interlacement again with spar, weight is comparatively large, and assembling is complicated.In addition, aileron trailing edge formations is all by complicated moulds of industrial equipment, and it is shaping to carry out co-curing, cost intensive.
Utility model content
Technical problem to be solved in the utility model is: for the deficiencies in the prior art, a kind of composite aileron structure is provided, solve the dismounting problem of leading edge opening problem and aileron, and the pure splicing realizing skins front edges connects, ensure that the integraty of aileron constructional appearance, improve leading edge rigidity.Meanwhile, the bind strength problem that normal temperature secondary large area is gluedd joint is solved.
The technical solution that the utility model adopts is as follows: a kind of composite aileron structure, comprising: covering, trailing edge full-height foam, left side trailing edge ends rib under covering, trailing edge on left side leading edge ends rib, the common rib of leading edge, spar, skins front edges, right side leading edge ends rib, right side trailing edge ends rib, trailing edge; Oscillating bearing is respectively charged in left side leading edge ends rib and right side leading edge ends rib, left side connection bearing is connected bearing and is arranged on left side leading edge ends rib and right side leading edge ends rib respectively by oscillating bearing with right side, aileron structure is connected bearing by left side connection bearing with right side and is connected with outer airfoil; Left side leading edge ends rib, right side leading edge ends rib, right side trailing edge ends rib, left side trailing edge ends rib and spar are mechanically connected, composition aileron structural backbone; Trailing edge full-height foam, trailing edge, under covering, trailing edge, covering has breather hole, bonding with spar on front side of trailing edge full-height foam, left side is bonding with left side trailing edge ends rib, right side is bonding with right side trailing edge ends rib, downside is bonding with covering under trailing edge, upside is bonding with covering on trailing edge, forms aileron main structure; The common rib of leading edge is bonding with spar, and skins front edges and the common rib of leading edge, spar, left side leading edge ends rib, right side leading edge ends rib are bonding, the common rib of parcel leading edge, spar, left side leading edge ends rib and right side leading edge ends rib.
Described trailing edge full-height foam adopts full-height PVC foamed sandwich structure.Described trailing edge under covering, trailing edge, covering and trailing edge full-height foam sets the position consistency of breather hole.On described skins front edges and trailing edge under covering intersection, skins front edges and trailing edge on covering intersection, trailing edge under covering and trailing edge covering intersection be bonded with two-layer carbon cloth respectively.
The utility model advantage is compared with prior art:
1, the utility model realizes the dismounting of aileron by dismounting left side connection bearing and the right side connection connected between bearing and wing, skins front edges is closing structure, avoid the skins front edges opening caused for meeting knocked down condition, do not need to arrange lid at connection bearing place or arrange larger exposed gap, ensure that the rigidity requirement of leading edge and the integraty of aileron structure.
2, the skins front edges closing structure that the utility model adopts uses the method for glueing joint to be connected with spar, the common rib of leading edge, left side leading edge ends rib, right side leading edge ends rib, and compared with opening stressed-skin construction, closing structure covering is thinner, and aileron structural weight is reduced, and assembling is simple.
3, the utility model aileron trailing edge by setting air extractor vent on the upper and lower covering of trailing edge and trailing edge full-height foam, air between effective eliminating bonding interface also forms glue nail, ensure that bind strength, solve the bind strength problem that normal temperature secondary large area is gluedd joint, aileron structure manufacturing cost is significantly reduced.
Accompanying drawing explanation
Fig. 1 is overall schematic of the present utility model;
Fig. 2 is the utility model aileron structural backbone schematic diagram;
Fig. 3 is the utility model aileron main structure schematic diagram;
Fig. 4 is the utility model aileron main structure cross sectional representation;
Fig. 5 is the utility model aileron main structure and the bonding schematic diagram of the common rib of leading edge;
Fig. 6 is the bonding schematic diagram of the utility model skins front edges;
Fig. 7 is that the utility model strengthens carbon cloth schematic diagram;
Fig. 8 installs oscillating bearing schematic diagram in leading edge ends rib on the left of the utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in more detail.
As shown in Figure 1, a kind of composite aileron structure, to comprise on left side leading edge ends rib 2, the common rib 3 of leading edge, spar 4, skins front edges 5, right side leading edge ends rib 6, right side trailing edge ends rib 8, trailing edge covering 10, trailing edge full-height foam 11, left side trailing edge ends rib 12 under covering 9, trailing edge.
Two oscillating bearings 14 load in left side leading edge ends rib 2 and right side leading edge ends rib 6, and left side connection bearing 1 is connected bearing 7 and is arranged on left side leading edge ends rib 2 and right side leading edge ends rib 6 respectively by oscillating bearing 14 with right side, as shown in Figure 8; Aileron structure is connected bearing 7 by left side connection bearing 1 with right side and is connected with wing; Left side leading edge ends rib 2, right side leading edge ends rib 6, right side trailing edge ends rib 8, left side trailing edge ends rib 12 are mechanically connected with spar 4, and composition aileron structural backbone, as Fig. 2; Aileron structural backbone to be bonded under trailing edge on covering 10 together with trailing edge full-height foam 11, and covering 9 on bonding trailing edge, bonding with spar 4 on front side of trailing edge full-height foam 11, left side is bonding with left side trailing edge ends rib 8, right side is bonding with right side trailing edge ends rib 12, and downside is bonding with covering under trailing edge 10, and upside is bonding with covering on trailing edge 9, form aileron main structure, as Fig. 3; Before bonding, trailing edge full-height foam 11, trailing edge, under covering 9, trailing edge, covering 10 sets breather hole, as Fig. 4, effectively can get rid of the air between bonding interface, and form glue nail, ensure large-area bind strength; The common rib of leading edge 3 is bonding with spar 4, and cross-sectional plane is as Fig. 5; Skins front edges 5 and the common rib of leading edge 3, spar 4, left side leading edge ends rib 2, right side leading edge ends rib 6 are bonding, the common rib 3 of parcel leading edge, spar 4, left side leading edge ends rib 2 and right side leading edge ends rib 6, and cross-sectional plane is as Fig. 6; Skins front edges 5 respectively increases two-layer carbon cloth 15 (T300) with covering 9 on covering 10 intersection, trailing edge under trailing edge with covering 10 intersection under trailing edge with covering 9 intersection, skins front edges 5 on trailing edge, can effectively avoid intersection to come unglued, as Fig. 7.
The unexposed technology of the utility model belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. a composite aileron structure, it is characterized in that, comprising: covering (10), trailing edge full-height foam (11), left side trailing edge ends rib (12) under covering (9), trailing edge on left side leading edge ends rib (2), the common rib of leading edge (3), spar (4), skins front edges (5), right side leading edge ends rib (6), right side trailing edge ends rib (8), trailing edge; Oscillating bearing (14) is respectively charged in left side leading edge ends rib (2) and right side leading edge ends rib (6), left side connect bearing (1) be connected with right side bearing (7) be arranged on respectively by oscillating bearing (14) on the left of on leading edge ends rib (2) and right side leading edge ends rib (6), aileron structure connects bearing (1) by left side and is connected bearing (7) with right side and is connected with outer airfoil; Left side leading edge ends rib (2), right side leading edge ends rib (6), right side trailing edge ends rib (8), left side trailing edge ends rib (12) are mechanically connected with spar (4), composition aileron structural backbone; Trailing edge full-height foam (11), trailing edge, under covering (9), trailing edge, covering (10) has breather hole, trailing edge full-height foam (11) front side is bonding with spar (4), left side is bonding with left side trailing edge ends rib (8), right side is bonding with right side trailing edge ends rib (12), downside is bonding with covering under trailing edge (10), upside is bonding with covering on trailing edge (9), forms aileron main structure; The common rib of leading edge (3) is bonding with spar (4), skins front edges (5) and the common rib of leading edge (3), spar (4), left side leading edge ends rib (2), right side leading edge ends rib (6) are bonding, the parcel common rib of leading edge (3), spar (4), left side leading edge ends rib (2) and right side leading edge ends rib (6).
2. a kind of composite aileron structure according to claim 1, is characterized in that: described trailing edge full-height foam (11) adopts full-height PVC foamed sandwich structure.
3. a kind of composite aileron structure according to claim 1 and 2, is characterized in that: the position consistency described trailing edge under covering (9), trailing edge, covering (10) and trailing edge full-height foam (11) setting breather hole.
4. a kind of composite aileron structure according to claim 3, is characterized in that: described skins front edges (5) is respectively bonded with two-layer carbon cloth (13) with covering (9) on covering (10) intersection, trailing edge under trailing edge with covering (10) intersection under trailing edge with covering (9) intersection, skins front edges (5) on trailing edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520344452.1U CN204822056U (en) | 2015-05-25 | 2015-05-25 | Combined material aileron structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520344452.1U CN204822056U (en) | 2015-05-25 | 2015-05-25 | Combined material aileron structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204822056U true CN204822056U (en) | 2015-12-02 |
Family
ID=54679682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520344452.1U Active CN204822056U (en) | 2015-05-25 | 2015-05-25 | Combined material aileron structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204822056U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107697270A (en) * | 2017-09-29 | 2018-02-16 | 南京航空航天大学 | Dismantled and assembled aileron mounting structure |
| CN108248824A (en) * | 2017-12-29 | 2018-07-06 | 南京航空航天大学 | A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof |
| CN111745985A (en) * | 2020-07-09 | 2020-10-09 | 中航通飞华南飞机工业有限公司 | Full-composite material aileron glue joint method and full-composite material aileron |
| CN111762336A (en) * | 2020-07-09 | 2020-10-13 | 中航通飞华南飞机工业有限公司 | Full-composite material flap and gluing method thereof |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
| CN114368469A (en) * | 2020-10-16 | 2022-04-19 | 中航西飞民用飞机有限责任公司 | Airplane airfoil composite material wing tip structure and manufacturing method |
-
2015
- 2015-05-25 CN CN201520344452.1U patent/CN204822056U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107697270A (en) * | 2017-09-29 | 2018-02-16 | 南京航空航天大学 | Dismantled and assembled aileron mounting structure |
| CN108248824A (en) * | 2017-12-29 | 2018-07-06 | 南京航空航天大学 | A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof |
| CN111745985A (en) * | 2020-07-09 | 2020-10-09 | 中航通飞华南飞机工业有限公司 | Full-composite material aileron glue joint method and full-composite material aileron |
| CN111762336A (en) * | 2020-07-09 | 2020-10-13 | 中航通飞华南飞机工业有限公司 | Full-composite material flap and gluing method thereof |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
| CN114368469A (en) * | 2020-10-16 | 2022-04-19 | 中航西飞民用飞机有限责任公司 | Airplane airfoil composite material wing tip structure and manufacturing method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204822056U (en) | Combined material aileron structure | |
| CN108216570B (en) | Main wing surface structure of high aspect ratio wing | |
| CN204368409U (en) | A kind of composite material hat Material Stiffened Panel being applicable to high aspect ratio wing | |
| CN206417437U (en) | A kind of advanced composite material (ACM) shelter | |
| CN105398563A (en) | Wing of membrane structure | |
| CN108100230A (en) | A kind of helicopter horizontal tail wing box | |
| CN105539812A (en) | Aircraft wing spar butting joint | |
| CN201745741U (en) | Overall thin-walled structure of composite machine body | |
| CN101417705A (en) | Shape preserving high-altitude balloon | |
| CN208530832U (en) | Built-in steering engine formula composite material unmanned plane wing | |
| CN205203353U (en) | Combined material primary load bearing honeycomb sandwich structure | |
| CN203958600U (en) | A kind of unmanned plane | |
| CN204750551U (en) | Transportation class aircraft of all -wing aircraft overall arrangement | |
| CN203666969U (en) | Bonded aerofoil architecture | |
| CN214397193U (en) | Low-height light airfoil leading edge structure | |
| CN109229373A (en) | A kind of connection structure of full composite material ground effect ship | |
| CN214986058U (en) | Flexible wing of flapping wing | |
| CN104015916A (en) | Unmanned plane | |
| CN203567832U (en) | Novel electromagnetic shielding shelter with radar stealth function | |
| CN207292369U (en) | A kind of aircraft conversion deckle board | |
| CN207631345U (en) | Closed structure and its body mechanism is applied before and after a kind of motor bus | |
| CN212890897U (en) | Composite material flap of general-purpose aircraft | |
| CN207187114U (en) | The plane toy that a kind of double vertical type tails are formed | |
| CN207187115U (en) | A kind of spliced fuselage toy structure | |
| CN207187112U (en) | A kind of horizontal tail prefix type plane toy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |