CN102963521A - Central wing of horizontal tail of civil airplane - Google Patents
Central wing of horizontal tail of civil airplane Download PDFInfo
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- CN102963521A CN102963521A CN201210447679XA CN201210447679A CN102963521A CN 102963521 A CN102963521 A CN 102963521A CN 201210447679X A CN201210447679X A CN 201210447679XA CN 201210447679 A CN201210447679 A CN 201210447679A CN 102963521 A CN102963521 A CN 102963521A
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- central wing
- back rest
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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 the aeroplane structure design technical field, relate to and a kind ofly can alleviate tailplane central wing structural weight, improve the constructional device of safe life and reliability.
Background technology
The airliner structure design is one of gordian technique in the large aircraft development, and the tail structure design is its important component part, and the airliner research-and-development activity of China need to constantly brought forth new ideas aspect structure design and tail fin design, solves key technical problem.
For the subsonic civil aircraft, the most serious state that the tailplane design needs to consider is take-off and landing, during take-off and landing, puts down wing flap and can produce larger nose-down pitching moment.Lift front-wheel and when landing, be held stationary taking off, horizontal tail must deflect into to greatest extent, so that enough nose-up pitching moments to be provided.Therefore, as long as guarantee that the driving efficiency of horizontal tail can satisfy the balance requirement of take-off and landing, usually will automatically satisfy the flight balance state under various possible lift coefficient during design.
According to the pertinent data introduction, after the nineties in last century, there is in the world the trunkliner over 70% all to adopt the adjustable tailplane of stagger angle.With respect to the tailplane of other form, this form tailplane both can satisfy the trim requirement in take-off and landing stage, can reduce trim resistance, horizontal tail area and aircraft weight again.The tailplane central wing is to be connected with the stabilator of tailplane, be used for guaranteeing the balance in pitch of aircraft, important mechanism stable and that vertical (pitching) handled to aircraft, its driving efficiency and reliability are the key factors that affects aircraft safety, so the horizontal tool of detailed design of the empennage central wing of improving the standard is of great significance.
The tailplane of adjustable stagger angle is to be connected pivot with back rest place and to be connected with rear body by being fixed on screw brake on the rear body bulkhead.The Adjusting Mechanism of stagger angle is as follows: driver train (as electro-motor, steering wheel or hydraulic actuator) when motion, drive bolt rotary, and be threaded between screw rod and lifting nut, lifting nut is fixed by the support and the horizontal tail central wing front-axle beam that connect leading screw.The dipping and heaving that the screw flight motion produces horizontal tail central wing front-axle beam makes whole horizontal tail central wing generation around the rotation of pivot, rotates thereby drive horizontal tail.
The tailplane central wing of Boeing B737 type aircraft adopts version as shown in Figure 1, and two blocks of the centres X-type web 3 that connects front-axle beam 2 and the back rest 4 in this structure adopts 7075 aluminum alloy materials, with front-axle beam 2 and the back rest 4 each 4 place's connecting bridges, totally 8 place's connecting bridges.The pivot 5 that is connected with the back rest 4 adopts the Integral design that extends to other end hinged place from an end hinged place, and the fatigue property of structure is relatively poor, cracks expansion whole pivot 5 was lost efficacy.
Summary of the invention
Purpose of the present invention: adopt the novel high-strength light material to alleviate the weight of tailplane central wing structure, design safe life and the reliability of hinged place pivot in the empennage central wing of improving the standard regulating mechanism by improvement.
A kind of civil aircraft tailplane central wing of the present invention, W type web between front-axle beam and the back rest adopts the carbon fiber ring epoxy resin composite material, be positioned at the inside of rear body due to the tailplane central wing, the situation that is subject to impact load is less, and composite material be subject to impact load after performance can sharply descend, so 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 make, reduced the attaching parts between W type web and the front-axle beam back rest, thereby reduced the quality of complicated attaching parts; Adopt the pivot design of novel back rest junction, a pivot is arranged in the hinged place, two ends, and each arranges outer pivot and interior pivot.
Beneficial effect of the present invention:
1, the density of carbon fiber ring epoxy resin composite material is at 1.7g/cm
3Left and right, modulus of elasticity 230GPa, tensile strength are more than 3500Mpa, than aluminum alloy materials density 2.7g/cm
3, modulus of elasticity 70GPa, pulling strengrth 400MPa, have lightweight, the advantage such as intensity is high, and is anticorrosive;
2, adopt novel W type web to connect front-axle beam and the back rest, only have 5 place's connecting bridges, reduced the attaching parts (for example being connected the rivet with auricle, riveted joint use) of web end and the front-axle beam back rest, W type web can adopt the carbon fiber laying from a direct lay of end to the other end, and at the rational position lay of web perpendicular to the reinforced rib fabric belt of direction before, make the integral body of web be processed into possibility;
3, adopt novel W type web design, the hypotenuse at its two ends is conducive to be connected with the strengthening rib of horizontal stabilizer root, make up being connected between the front-axle beam that only has horizontal stabilizer in Boeing B737 and the back rest, thereby made structure stress more reasonable, improved carrying effect;
4, civil aircraft whole 20 ~ 30 years during one's term of military service in, safety is vital.Make the unipivot that whole pivot lost efficacy change into the two ends layout by crackle occurring, and pivot is designed to outer pivot and the interior pivot of hollow, when outer pivot crackle appears or produce broken outside, interior pivot still can bearing load, has improved pivot and tailplane central wing stagger angle adjustable safe life and reliability.
Description of drawings
Fig. 1 Boeing B737 tailplane central wing schematic diagram;
Fig. 2 Boeing B737 tailplane is regulated the 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 between rear body frame B and the back rest in the present invention;
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, the 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.
The specific embodiment
Below in conjunction with accompanying drawing, a kind of civil aircraft tailplane central wing of the present invention is elaborated.
(a), regulate its principle of work of stagger angle mechanism for the tailplane of Boeing B737 shown in accompanying drawing 2 and be: rear body frame A is connected with the screw rod lower seat, general in the front of horizontal stabilizer front-axle beam a bit, particular location obtains after need to coordinating.Screw rod 6 produces rotation by servomotor torque constant or fluid motor-driven, drive the leading screw support 1 vertical direction motion that is connected with screw rod 6, because the back rest 4 is hinged by pivot 5 with rear body frame B 8, thereby the motion of tailplane central wing reality is exactly the variation of angle, and the adjustable movement mechanism of Tail Plane Incidence;
(b), for shown in accompanying drawing 3 being the structure scheme of installation of a kind of Novel horizontal empennage central wing provided by the invention: the W type web 9 between front-axle beam 2 and the back rest 4 adopts the carbon fiber ring epoxy resin composite materials, adopt carbon fiber laying technology, along a continuous lay of end of W type web 9 to the other end, layering type is [0/+45/-45/90/-45/+45/0], then be vertical lay carbon fiber by the strengthening rib strip direction, adopt one-step solidification to be shaped after completing, W type web 9 adopts the method preparation of integral processing, there are three with the connecting portion of front-axle beam 2, there are 2 with the connecting portion of the back rest 4, have 5 connecting portions altogether, alleviated the weight of complicated attaching parts, can be connected with the root rib end frame of horizontal stabilizer simultaneously at the both sides of W type web 9 panel, make up two blocks of X-type webs 3 and horizontal stabilizer root ridged surface and differed larger deficiency,
(c), for accompanying drawing 4～tailplane central wing back rest shown in Figure 6 and rear body frame hinged place pivot schematic diagram: the back rest 4 is comprised 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 Fig. 5 A, be provided with lightening hole 10-1 on described back rest attachment lug 10, has through hole 10-2, back rest attachment lug 10 by 4 riveted joints of rivet and the back rest after, in the through hole 10-2 of beam attachment lug 10, bearing 18 is installed, the through hole 10-2 of back rest attachment lug 10 is inboard adopts interference fit to contact with bearing 18 outside faces; Rear body frame B attachment lug 11 is by rivet and rear body frame B 8 riveted joints, be provided with lightening grooves 11-2 on rear body frame B attachment lug 11, the inner packing ring 17 of installing of its through hole 11-1, as shown in Figure 6, rear body frame B attachment lug 11 adopts interference fit to contact with packing ring 17; The inner outer shafts 12 of installing of bearing 18 and packing ring 17, bearing 18 is inner and packing ring 17 is inner and the outside interference fit that adopt of outer shaft 12; Inner interior axle 13, outer shaft 12 and the interior axle 13 employing interference fit of installing of the through hole of outer shaft 12; The inner mandrel 14 of installing of interior axle 13 through holes has the space between interior axle 13 and mandrel 14, and mandrel 14 two ends are fixing by nut 16 and card 15, make mandrel 14, interior axle 13, outer shaft 12 not produce axial slippage.
For the design of traditional single shaft pivot, in case this root pivot produces endurance crack under the flight load function of complicated alternation, or due to outside the sudden change load such as gust load produce brokenly, will cause the structural failure of tailplane central wing, stagger angle can't be adjusted etc.Adopt novel outer shaft 12 provided by the invention and interior axle 13, mandrel 14 is installed at the middle part, and make outer shaft 12, interior axle 13 and mandrel 14 to endwisely slip, can't expand on another root axle when an axle produces endurance crack therein, and occur due to sudden change load at an axle intensity broken outside the time, another root axle still can stand under load, and this method can improve the safe handling cycle of pivot, safe life and the reliability of the empennage central wing of improving the standard simultaneously.
Claims (4)
1. civil aircraft tailplane central wing is characterized in that: be connected W type web between front-axle beam and the back rest, and three point of connection of W type web and front-axle beam, with two point of connection of the back rest, the both sides panel of W type web is connected with the root rib end frame of horizontal stabilizer simultaneously.
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 a continuous lay of end of W type web to the other end, layering type is [0/+45/-45/90/-45/+45/0], then be vertical lay carbon fiber by the strengthening rib strip direction, 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, it is characterized in that: the connecting bridge of the back rest and rear body frame B is comprised of back rest attachment lug and rear body frame B attachment lug, in the through hole of the back rest attachment lug by the riveted joint of rivet and the back rest, bearing is installed, the through hole of back rest attachment lug is inboard to be contacted with bearing outside surface employing interference fit; Rear body frame B attachment lug is riveted by rivet and rear body frame B, the inner packing ring of installing of the through hole 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 are installed outer shaft, bearing inside and bead interior and outer shaft outer end employing interference fit; Inner interior axle, outer shaft and the interior axle employing interference fit of installing of outer shaft through-hole; The inner mandrel of installing of interior shaft through-hole has the space between interior axle and mandrel, and mandrel two ends are fixed by nut and card, make mandrel, inner shaft, outer shaft not produce axial slippage.
4. a kind of civil aircraft tailplane central wing according to claim 1, is characterized in that: be provided with lightening hole on described back rest attachment lug, be provided with lightening grooves on rear body frame B attachment lug.
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 |
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| Publication Number | Publication Date |
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| CN102963521A true CN102963521A (en) | 2013-03-13 |
| CN102963521B CN102963521B (en) | 2015-04-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN109131824A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft reinforcing frame and vertical fin girder construction |
| EP3604120A1 (en) * | 2018-08-01 | 2020-02-05 | Airbus Operations, S.L.U. | Fitting for attaching the horizontal tail stabilizer of an aircraft |
| CN110920867A (en) * | 2019-12-09 | 2020-03-27 | 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 |
| WO2023093803A1 (en) * | 2021-11-29 | 2023-06-01 | 中国商用飞机有限责任公司 | Trimming-type tailplane connection structure |
Citations (4)
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| 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 |
| US20110215201A1 (en) * | 2010-03-03 | 2011-09-08 | Airbus Operations Gmbh | Strut system for the stabilization of the shell of an aerodynamic aircraft component for a commercial aircraft |
| CN202213713U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Horizontal tail adjusting mechanism |
-
2012
- 2012-11-09 CN CN201210447679.XA patent/CN102963521B/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| US20110215201A1 (en) * | 2010-03-03 | 2011-09-08 | Airbus Operations Gmbh | Strut system for the stabilization of the shell of an aerodynamic aircraft component for a commercial aircraft |
| 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 |
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| 叶明伟: "CJ818可调式平尾调节机构的初步分析与设计", 《民用飞机设计与研究》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| EP3604120A1 (en) * | 2018-08-01 | 2020-02-05 | Airbus Operations, S.L.U. | Fitting for attaching the horizontal tail stabilizer of an aircraft |
| CN109131824A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft reinforcing frame and vertical fin girder construction |
| 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 |
| CN110920867A (en) * | 2019-12-09 | 2020-03-27 | 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 |
| WO2023093803A1 (en) * | 2021-11-29 | 2023-06-01 | 中国商用飞机有限责任公司 | Trimming-type tailplane connection structure |
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| Publication number | Publication date |
|---|---|
| CN102963521B (en) | 2015-04-22 |
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