CN102963521B - Central wing of horizontal tail of civil airplane - Google Patents
Central wing of horizontal tail of civil airplane Download PDFInfo
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- CN102963521B CN102963521B CN201210447679.XA CN201210447679A CN102963521B CN 102963521 B CN102963521 B CN 102963521B CN 201210447679 A CN201210447679 A CN 201210447679A CN 102963521 B CN102963521 B CN 102963521B
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- central wing
- back rest
- rear body
- attachment lug
- body frame
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Abstract
The invention discloses a central wing of a horizontal tail of a civil airplane, which belongs to the technical field of airplane structures, and is capable of lightening the structural weight of the conventional central wing of the horizontal tail, prolonging structural safety life of the conventional central wing and improving the structure reliability of the conventional central wing. According to the central wing of the horizontal tail of the civil airplane, a W-shaped web plate is used for connecting a front beam and a rear beam of the central wing of the horizontal tail and is subjected to tape laying through composite materials to finish an integral processing process, and thus the structure weight is lightened; and rear beam connecting lugs and rear body reinforcing frame lugs are connected with one another by a pivot, the functions of the pivot of the rear beam is realized by virtue of an outer shaft and an inner shaft, endurance cracks of one shaft cannot expand to the other shaft, and when one shaft suffers from strength disruption due to load mutation, the other shaft still can be loaded, so that the safe service life of the pivot is prolonged, and the reliability of the pivot is improved.
Description
Technical field
The invention belongs to technical field of aircraft structure design, relate to one and can alleviate tailplane central wing structural weight, improve the constructional device of safe life and reliability.
Background technology
Large aircraft structures design is one of gordian technique in large aircraft development, and tail structure design is its important component part, and the airliner research-and-development activity of China needs to constantly bring forth new ideas in structure design and tail fin design, solves key technical problem.
For subsonic civil aircraft, tailplane design needs the most severe conditions considered to be take-off and landing, during take-off and landing, puts down wing flap and can produce larger nose-down pitching moment.Take off lift front-wheel and land time, be held stationary, horizontal tail must deflect into greatest extent, to provide enough nose-up pitching moments.Therefore, as long as ensure during design that the driving efficiency of horizontal tail can meet the balance requirement of take-off and landing, will meet the flight balance state under various possible lift coefficient usually automatically.
According to pertinent data introduction, after the nineties in last century, the trunkliner more than 70% is had all to have employed the adjustable tailplane of stagger angle in the world.Relative to the tailplane of other form, this form tailplane both can meet the trim requirement in take-off and landing stage, can reduce again trim resistance, horizontal tail area and aircraft weight.Tailplane central wing is connected with the stabilator of tailplane, be used for ensureing the balance in pitch of aircraft, important mechanism that is stable and that handle aircraft longitudinal (pitching), its driving efficiency and reliability are the key factors affecting aircraft safety, so the horizontal tool of detailed design of empennage central wing of improving the standard is of great significance.
The tailplane of adjustable stagger angle is connected with rear body with the pivot at back rest place by the screw brake be fixed on rear body bulkhead.The Adjusting Mechanism of stagger angle is as follows: when driver train (as electro-motor, steering wheel or hydraulic actuator) moves, and drives bolt rotary, is threaded between screw rod with lifting nut, and lifting nut is fixed by the support and horizontal tail central wing front-axle beam connecting leading screw.Screw flight motion produces the dipping and heaving of horizontal tail central wing front-axle beam, makes whole horizontal tail central wing generation rotation pivotally, thus drives horizontal tail to rotate.
The tailplane central wing of Boeing B737 type aircraft adopts version as shown in Figure 1, connects front-axle beam 2 and adopt 7075 aluminum alloy materials with two blocks, the centre X-type web 3 of the back rest 4 in this structure, with front-axle beam 2 and each 4 place's connecting bridges of the back rest 4, and totally 8 place's connecting bridges.The pivot 5 be connected with the back rest 4 adopts the Integral design extending to other end hinged place from hinged place, one end, and the fatigue property of structure is poor, cracks expansion and whole pivot 5 can be made to lose efficacy.
Summary of the invention
Object of the present invention: adopt novel high-strength light material to alleviate the weight of tailplane central wing structure, by Curve guide impeller, the safe life of hinged place pivot and reliability in empennage central wing of improving the standard regulating mechanism.
A kind of civil aircraft tailplane central wing of the present invention, W type web between front-axle beam and the back rest adopts carbon fiber epoxy resin composite material, because tailplane central wing is positioned at the inside of rear body, the situation being subject to impact load is less, and composite material be subject to impact load after performance can sharply decline, therefore the application of composite material becomes possibility; Adopt novel W type web to connect front-axle beam and the back rest, use carbon fiber laying technology to manufacture, decrease the attaching parts between W type web and the front-axle beam back rest, thus decrease the quality of complicated attaching parts; Adopt the hub design of novel back rest junction, a pivot is arranged in hinged place, two ends, and the outer pivot of each layout and interior pivot.
Beneficial effect of the present invention:
1, the density of carbon fiber epoxy resin composite material is at 1.7g/cm
3left and right, modulus of elasticity 230GPa, tensile strength at more than 3500Mpa, compared to aluminum alloy materials density 2.7g/cm
3, modulus of elasticity 70GPa, pulling strengrth 400MPa, have lightweight, the advantages such as intensity is high, anticorrosive;
2, novel W type web is adopted to connect front-axle beam and the back rest, only have 5 place's connecting bridges, decrease the attaching parts (being such as connected with auricle, the rivet of riveting) of web end and the front-axle beam back rest, W type web can adopt carbon fiber laying from one end direct lay to the other end, and at the rational position lay of web perpendicular to the reinforced rib fabric belt in direction before, make the overall processing of web become possibility;
3, novel W type web design is adopted, the hypotenuse at its two ends is conducive to being connected with the strengthening rib of horizontal stabilizer root, compensate in Boeing B737 the connection only had between the front-axle beam of horizontal stabilizer and the back rest, thus make structure stress more reasonable, improve carrying effect;
4, civil aircraft whole 20 ~ 30 years during one's term of military service in, safety is vital.Two ends layout is changed into by making the unipivot that whole pivot lost efficacy by there is crackle, and hub design is become the outer pivot of hollow and interior pivot, outside there is crackle in outer pivot or generation is broken, interior pivot still can bearing load, improves pivot and the adjustable safe life of tailplane central wing stagger angle and reliability.
Accompanying drawing explanation
Fig. 1 Boeing B737 tailplane central wing schematic diagram;
Fig. 2 Boeing B737 tailplane regulates stagger angle structural scheme of mechanism;
Fig. 3 Novel horizontal empennage provided by the invention central wing W type web connection structure schematic diagram;
Fig. 4 is the connecting component structure schematic diagram in the present invention between rear body frame B and the back rest;
Fig. 5 is back rest attachment lug and rear body frame B attachment lug structural representation in the present invention;
Fig. 6 is the tailplane central wing back rest and rear body frame hinged place pivot section-drawing in the present invention.
In figure:
1, leading screw support, 2, front-axle beam, 3, X-type web, 4, the back rest, 5, pivot, 6, screw rod, 7, rear body frame A, 8, rear body frame B, 9, W type web, 10, back rest attachment lug, 11, rear body frame B attachment lug, 12, outer shaft, 13, interior axle, 14, mandrel, 15, card, 16, nut, 17, packing ring, 18, bearing.
Detailed description of the invention
Below in conjunction with accompanying drawing, a kind of civil aircraft tailplane central wing of the present invention is described in detail.
(a), to regulate stagger angle mechanism its principle of work to be for the tailplane of Boeing B737 shown in accompanying drawing 2: rear body frame A is connected with screw rod lower seat, generally before horizontal stabilizer front-axle beam a bit, obtain after the coordination of particular location needs.Screw rod 6 is produced by servomotor torque constant or fluid motor-driven and rotates, leading screw support 1 vertical direction be connected with screw rod 6 is driven to move, because the back rest 4 and rear body frame B 8 are hinged by pivot 5, thus the motion of tailplane central wing reality is exactly the change of angle, and the movement mechanism that Tail Plane Incidence is adjustable;
(b), the structure installment schematic diagram for a kind of Novel horizontal empennage central wing provided by the invention for shown in accompanying drawing 3: the W type web 9 between front-axle beam 2 and the back rest 4 adopts carbon fiber epoxy resin composite material, adopt carbon fiber laying technology, along the continuous lay in one end of W type web 9 to the other end, layering type is [0/+45/-45/90/-45/+45/0], then strengthening rib strip direction and vertical lay carbon fiber is pressed, one-step solidification is adopted to be shaped after completing, W type web 9 adopts the method for integral processing to prepare, three are had with the connecting portion of front-axle beam 2, 2 are had with the connecting portion of the back rest 4, 5 connecting portions altogether, alleviate the weight of complicated attaching parts, can be connected with the root rib end frame of horizontal stabilizer at the both sides panel of W type web 9 simultaneously, compensate for two blocks of X-type webs 3 and differ larger deficiency with horizontal stabilizer root ridged surface,
(c), for the tailplane central wing back rest shown in accompanying drawing 4 ~ Fig. 6 and rear body frame hinged place pivot schematic diagram: the back rest 4 is made up of back rest attachment lug 10 and rear body frame B attachment lug 11 with the connecting bridge of rear body frame B 8, as shown in Figure 5A, described back rest attachment lug 10 is provided with lightening hole 10-1, there is through hole 10-2, after back rest attachment lug 10 is riveted by rivet and the back rest 4, in the through hole 10-2 of beam attachment lug 10, bearing 18 is installed, inside the through hole 10-2 of back rest attachment lug 10, adopts interference fit to contact with bearing 18 outside face; Rear body frame B attachment lug 11 is riveted by rivet and rear body frame B 8, rear body frame B attachment lug 11 is provided with lightening grooves 11-2, its through hole 11-1 installs packing ring 17 in inside, and as shown in Figure 6, rear body frame B attachment lug 11 adopts interference fit to contact with packing ring 17; Bearing 18 installs outer shaft 12 with packing ring 17 inside, and bearing 18 is inner and packing ring 17 is inner adopts interference fit with outer shaft 12 outside; Interior axle 13 is installed in the through hole inside of outer shaft 12, and outer shaft 12 and interior axle 13 adopt interference fit; Mandrel 14 is installed in interior axle 13 through hole inside, has space between interior axle 13 and mandrel 14, and mandrel 14 two ends are fixed by nut 16 and card 15, make mandrel 14, interior axle 13, outer shaft 12 not produce axial slippage.
For traditional single shaft hub design, once this root pivot produces endurance crack under the flight load function of complicated alternation, or outside producing brokenly due to sudden change load such as gust loads, will cause the structural failure of tailplane central wing, stagger angle cannot adjust.Adopt novel outer shaft 12 provided by the invention and interior axle 13, mandrel 14 is installed at middle part, and outer shaft 12, interior axle 13 and mandrel 14 cannot be slid axially, can't expand to another root axle on when an axle produces endurance crack wherein, and when due to sudden change load, an axle occurs that intensity is broken outer, another root axle still can stand under load, and this method can improve the safe handling cycle of pivot, the safe life of empennage central wing of simultaneously improving the standard and reliability.
Claims (3)
1. a civil aircraft tailplane central wing, is characterized in that: be connected W type web between front-axle beam with the back rest, W type web and front-axle beam three point of connection, and with the back rest two point of connection, the both sides panel of W type web is connected with the root rib end frame of horizontal stabilizer simultaneously;
The connecting bridge of the back rest and rear body frame B is made up of back rest attachment lug and rear body frame B attachment lug, in the through hole of the back rest attachment lug of being riveted by rivet and the back rest, bearing is installed, inside the through hole of back rest attachment lug, adopts interference fit to contact with bearing outside surface; Rear body frame B attachment lug is riveted by rivet and rear body frame B, and packing ring is installed in the through hole inside of rear body frame B attachment lug, and rear body frame B attachment lug adopts interference fit to contact with packing ring; Bearing and bead interior install outer shaft, and Bearing inner and bead interior and outer shaft outer end adopt interference fit; Interior axle is installed in outer shaft through-hole inside, and outer shaft and interior axle adopt interference fit; Mandrel is installed in interior shaft through-hole inside, and have space between interior axle and mandrel, mandrel two ends are fixed by nut and card, make mandrel, inner shaft, outer shaft not produce axial slippage.
2. a kind of civil aircraft tailplane central wing according to claim 1, it is characterized in that: W type web adopts carbon fiber laying technology, along the continuous lay in one end of W type web to the other end, layering type is [0/+45/-45/90/-45/+45/0], then strengthening rib strip direction and vertical lay carbon fiber is pressed, adopt one-step solidification to be shaped after completing, W type web adopts the method preparation of integral processing.
3. a kind of civil aircraft tailplane central wing according to claim 1, is characterized in that: described back rest attachment lug is provided with lightening hole, and rear body frame B attachment lug is provided with lightening grooves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210447679.XA CN102963521B (en) | 2012-11-09 | 2012-11-09 | Central wing of horizontal tail of civil airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210447679.XA CN102963521B (en) | 2012-11-09 | 2012-11-09 | Central wing of horizontal tail of civil airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102963521A CN102963521A (en) | 2013-03-13 |
| CN102963521B true CN102963521B (en) | 2015-04-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210447679.XA Expired - Fee Related CN102963521B (en) | 2012-11-09 | 2012-11-09 | Central wing of horizontal tail of civil airplane |
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| CN (1) | CN102963521B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103895856A (en) * | 2014-04-24 | 2014-07-02 | 哈尔滨工业大学 | Composite-material I beam connecting device of aerofoils and aeroplane body |
| CN103895855A (en) * | 2014-04-24 | 2014-07-02 | 哈尔滨工业大学 | Mouth-shaped beam connecting device of composite wing and fuselage |
| EP3604120B1 (en) * | 2018-08-01 | 2022-01-26 | Airbus Operations, S.L.U. | Fitting for attaching the horizontal tail stabilizer of an aircraft |
| CN109131824B (en) * | 2018-09-21 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane reinforcing frame and vertical tail beam structure |
| CN110920867B (en) * | 2019-12-09 | 2023-04-14 | 中航沈飞民用飞机有限责任公司 | Horizontal tail side inertial load bearing hinge joint of civil passenger plane |
| CN113955080B (en) * | 2021-11-29 | 2023-10-20 | 中国商用飞机有限责任公司 | Trimming type horizontal tail connecting structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4043523A (en) * | 1976-03-11 | 1977-08-23 | Ball Brothers Research Corporation | Apparatus for aircraft pitch trim |
| US6109415A (en) * | 1998-05-29 | 2000-08-29 | The Boeing Company | Bi-directional ballscrew no-back device |
| CN202213713U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Horizontal tail adjusting mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102010010168B4 (en) * | 2010-03-03 | 2013-09-19 | Airbus Operations Gmbh | Bracing arrangement for stabilizing the outer skin of an aerodynamic aircraft part in a commercial aircraft |
-
2012
- 2012-11-09 CN CN201210447679.XA patent/CN102963521B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4043523A (en) * | 1976-03-11 | 1977-08-23 | Ball Brothers Research Corporation | Apparatus for aircraft pitch trim |
| US6109415A (en) * | 1998-05-29 | 2000-08-29 | The Boeing Company | Bi-directional ballscrew no-back device |
| CN202213713U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Horizontal tail adjusting mechanism |
Non-Patent Citations (1)
| Title |
|---|
| CJ818可调式平尾调节机构的初步分析与设计;叶明伟;《民用飞机设计与研究》;20090730(第S1期);第2页以及附图3-5 * |
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| CN102963521A (en) | 2013-03-13 |
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