CN104477375A - Adjustable horizontal tail - Google Patents
Adjustable horizontal tail Download PDFInfo
- Publication number
- CN104477375A CN104477375A CN201410694080.5A CN201410694080A CN104477375A CN 104477375 A CN104477375 A CN 104477375A CN 201410694080 A CN201410694080 A CN 201410694080A CN 104477375 A CN104477375 A CN 104477375A
- Authority
- CN
- China
- Prior art keywords
- horizontal tail
- tail
- vertical fin
- beam splice
- rear beam
- 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.)
- Pending
Links
Abstract
The invention relates to an adjustable horizontal tail, and belongs to the technical field of the structure design of an airplane. The adjustable horizontal tail comprises a horizontal tail wallboard, a front beam, a middle beam, a wing rib, a front beam connector, a left side lifting rudder, a rear beam connector, a rear beam, a right side lifting rudder, a drive connector, a hinge connector, a deformable rectifying wrapper, a vertical tail, a vertical tail rear beam and a drive pull rod; a left horizontal tail and a right horizontal tail are of an integral part, a bending moment and a torque of a pneumatic load acting on the horizontal tail can be internally balanced, the requirement for the force transfer of a vertical tail connecting piece can be lowered, smoothness in force transfer can be realized, and the structural weight can be saved; the adjusting mechanism is simple, the control is stable, and the weight is small. The pneumatic appearance can be prevented from being damaged due to the motion requirement.
Description
Technical field
The present invention relates to a kind of adjustable horizontal tail, belong to the structure-design technique field of aircraft.
Background technology
Modern business airplane substantially all have employed the typical aerodynamic arrangement of lower single-blade, T-shaped empennage in aerodynamic arrangement.For pursuing economy of cruising, increasing aircraft can use 1ift-drag ratio, the aircraft longitudinally quiet permanence that normal employing is less, optimizes the trim resistance of reduction horizontal tail.But thing followed problem is the driving efficiency reducing elevating rudder, causing taking off, it is not enough to lift front-wheel nose-up pitching moment, has affected drop characteristic.
For this problem, horizontal tail setting angle should possess adjustable function, according to manipulation demand, horizontal tail adjustment can be used at several fixed angle under different flight profile, mission profiles.This horizontal tail setting angle regulating mechanism should ensure the intensity and toughness of horizontal tail, also will take into account and be connected with vertical fin, guarantees that horizontal tail aerodynamic force and bending square thereof can be delivered to fuselage by vertical fin joint smoothly, or Equilibrium.Good adjusting mechanism scheme and horizontal tail organization plan, can accomplish, when weight Least-cost, to meet the requirement that horizontal tail setting angle is adjustable.Therefore, be necessary to design the adjustable horizontal tail that a regulating mechanism is simple, power transmission is smooth and easy, structural weight is low, to realize the target that horizontal tail trim resistance is little, economy of cruising is high.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide that a kind of regulating mechanism is simple, power transmission is smooth and easy, structural weight is low and the adjustable horizontal tail of aerodynamic configuration can not be destroyed due to motion requirement.
To achieve these goals, the present invention adopts following technical scheme:
A kind of adjustable horizontal tail, it comprises horizontal tail wallboard, front-axle beam, central sill, rib, front beam splice, left side elevating rudder, rear beam splice, the back rest, right side elevating rudder, drive sub, articulated joint, deformable shoulder cowling, vertical fin, the vertical fin back rest and drives pull bar;
Described horizontal tail wallboard, front-axle beam, central sill, the back rest and rib are assembled into left and right horizontal tail box section by riveted joint; It is a global facility that left and right horizontal tail box section is spirally connected by front beam splice and rear beam splice, and wherein, beam splice is provided with drive sub, and rear beam splice is provided with articulated joint; Left and right elevating rudder is connected with horizontal tail by joint; Horizontal tail is fixed on the vertical fin back rest by the articulated joint on rear beam splice; Deformable shoulder cowling one end is fixed in horizontal tail, and the other end is overlapped on vertical fin; Driving pull bar is the start part of hydraulic actuator, and the other end is connected with drive sub.
Function one: be by articulated joint and the vertical fin back rest hinged, flexible can realize horizontal tail by what drive pull bar and rotate around articulated joint.Meet the adjustment requirement of horizontal tail by the fixed angles such as-4 °, 0 °, 4 °, 10 °, 14 °; And this link form only needs to transmit the Y-direction load such as horizontal tail lift, gravity, reduces the requirement of strength design to the vertical fin back rest, regulating mechanism is simple, and working stability, weight is little.
Function two: by being fixed on deformable shoulder cowling in horizontal tail and vertical fin topographies, can avoid rotating due to horizontal tail the aerodynamic configuration brought and destroy.
Function three: be that left and right horizontal tail runs through connection by front beam splice and rear beam splice, form a global facility, left and right horizontal tail at beam splice place Equilibrium, can reduce the rigidity requirement to vertical fin due to the moment of pneumatic generation.
The invention has the advantages that: left and right horizontal tail is global facility, moment of flexure in horizontal tail and moment of torsion can be acted at internal balance aerodynamic loading, reduce the power transmission requirement to vertical fin attaching parts, power transmission is smooth and easy, save structural weight; Regulating mechanism is simple, and control is stable, weight is little.And aerodynamic configuration can not be destroyed due to motion requirement.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
In Fig. 1: 1,6-horizontal tail wallboard, 2-front-axle beam, 3-central sill, 4-rib, 5-front beam splice, 7-left side elevating rudder, 8-rear beam splice, 9-back rest, 10-right side elevating rudder;
Fig. 2 is the cutaway view in Figure 1A-A face;
In Fig. 2: 11-drive sub, 12-articulated joint, 13-deformable shoulder cowling, 14-vertical fin, the 15-vertical fin back rest, 16-drives pull bar.
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing 1,2:
The adjustable horizontal tail (see Fig. 1, Fig. 2) that the present invention proposes it comprise: horizontal tail wallboard 1,6, front-axle beam 2, central sill 3, rib 4, front beam splice 5, left side elevating rudder 7, rear beam splice 8, the back rest 9, right side elevating rudder 10, drive sub 11, articulated joint 12, deformable shoulder cowling 13, vertical fin 14, the vertical fin back rest 15 and drive pull bar 16.
Horizontal tail wallboard 1,6, front-axle beam 2, central sill 3, the back rest 9 and rib 4 be assembled into left and right horizontal tail box section by riveted joint; It is a global facility that left and right horizontal tail box section is spirally connected by front beam splice 5 and rear beam splice 8, wherein, beam splice 5 is designed with drive sub 11, rear beam splice 8 is designed with articulated joint 12; Left and right elevating rudder 7,9 is connected with horizontal tail by joint; Horizontal tail is fixed on the vertical fin back rest 15 by the articulated joint 12 on rear beam splice 8; Deformable shoulder cowling 13 one end is fixed in horizontal tail, and the other end is overlapped on vertical fin; Driving pull bar 16 is the start part of hydraulic actuator, and the other end is connected with drive sub 11.
This invention rotates around articulated joint 12 by driving the flexible horizontal tail that realizes of pull bar 16, meets the adjustment requirement of horizontal tail by the fixed angles such as-4 °, 0 °, 4 °, 10 °, 14 °; And this link form only needs to transmit the Y-direction load such as horizontal tail lift, gravity, reduces the requirement of strength design to the vertical fin back rest, regulating mechanism is simple, and working stability, weight is little.By being fixed on deformable shoulder cowling in horizontal tail 13 and vertical fin topographies, can avoid because horizontal tail rotates the aerodynamic configuration destruction of bringing.And by front beam splice 5 and rear beam splice 8, left and right horizontal tail is run through connection, form a global facility, realize the bending square that the inner self-balancing aerodynamic loading of horizontal tail produces, reduce the rigidity requirement to vertical fin.
The horizontal tail that this invention relates to is global facility, can act on moment of flexure and moment of torsion that horizontal tail is formed, reduce the power transmission requirement to vertical fin attaching parts at internal balance aerodynamic loading, and power transmission is smooth and easy, saving structural weight; Regulating mechanism is simple, and control is stable, weight is little.And aerodynamic configuration can not be destroyed due to motion requirement.
Claims (1)
1. an adjustable horizontal tail, is characterized in that: it comprises horizontal tail wallboard (1,6), front-axle beam (2), central sill (3), rib (4), front beam splice (5), left side elevating rudder (7), rear beam splice (8), the back rest (9), right side elevating rudder (10), drive sub (11), articulated joint (12), deformable shoulder cowling (13), vertical fin (14), the vertical fin back rest (15) and drives pull bar (16);
Described horizontal tail wallboard (1,6), front-axle beam (2), central sill (3), the back rest (9) and rib (4) are assembled into left and right horizontal tail box section by riveted joint; It is a global facility that left and right horizontal tail box section is spirally connected by front beam splice (5) and rear beam splice (8), and wherein, beam splice (5) is provided with drive sub (11), and rear beam splice (8) is provided with articulated joint (12); Left and right elevating rudder (7,9) is connected with horizontal tail by joint; Horizontal tail is fixed on the vertical fin back rest (15) by the articulated joint (12) on rear beam splice (8); Deformable shoulder cowling (13) one end is fixed in horizontal tail, and the other end is overlapped on vertical fin; Drive the start part that pull bar (16) is hydraulic actuator, the other end is connected with drive sub (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410694080.5A CN104477375A (en) | 2014-11-27 | 2014-11-27 | Adjustable horizontal tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410694080.5A CN104477375A (en) | 2014-11-27 | 2014-11-27 | Adjustable horizontal tail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104477375A true CN104477375A (en) | 2015-04-01 |
Family
ID=52752032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410694080.5A Pending CN104477375A (en) | 2014-11-27 | 2014-11-27 | Adjustable horizontal tail |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104477375A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
| 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 |
| CN113955080A (en) * | 2021-11-29 | 2022-01-21 | 中国商用飞机有限责任公司 | Balance type horizontal tail connecting structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090184208A1 (en) * | 2008-01-17 | 2009-07-23 | Airbus Uk Limited | Aerodynamic sealing member for aircraft |
| CN102229357A (en) * | 2011-05-12 | 2011-11-02 | 北京航空航天大学 | Empennage with installing angle and adjustable horizontal tail |
| CN203528806U (en) * | 2013-08-14 | 2014-04-09 | 天津三爻航空航天科技发展有限公司 | Fixed wing type unmanned aerial vehicle |
| CN203889055U (en) * | 2014-05-16 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Horizontal tail structure of helicopter |
| CN203937863U (en) * | 2014-06-13 | 2014-11-12 | 陕西飞机工业（集团）有限公司 | A kind of non-metal unique construction transition piece |
| CN204279916U (en) * | 2014-11-27 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of adjustable horizontal tail |
-
2014
- 2014-11-27 CN CN201410694080.5A patent/CN104477375A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090184208A1 (en) * | 2008-01-17 | 2009-07-23 | Airbus Uk Limited | Aerodynamic sealing member for aircraft |
| CN102229357A (en) * | 2011-05-12 | 2011-11-02 | 北京航空航天大学 | Empennage with installing angle and adjustable horizontal tail |
| CN203528806U (en) * | 2013-08-14 | 2014-04-09 | 天津三爻航空航天科技发展有限公司 | Fixed wing type unmanned aerial vehicle |
| CN203889055U (en) * | 2014-05-16 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Horizontal tail structure of helicopter |
| CN203937863U (en) * | 2014-06-13 | 2014-11-12 | 陕西飞机工业（集团）有限公司 | A kind of non-metal unique construction transition piece |
| CN204279916U (en) * | 2014-11-27 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of adjustable horizontal tail |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109823514A (en) * | 2019-02-02 | 2019-05-31 | 北京航空航天大学 | A kind of quick detachable tail structure of adjustable established angle |
| CN109823514B (en) * | 2019-02-02 | 2021-01-12 | 北京航空航天大学 | Quick detachable fin structure of adjustable installation angle |
| 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 |
| CN113955080A (en) * | 2021-11-29 | 2022-01-21 | 中国商用飞机有限责任公司 | Balance type horizontal tail connecting structure |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2731787C (en) | Control surface of aircraft | |
| US9856013B2 (en) | Deformable wing including a mobile upper surface | |
| WO2009102739A3 (en) | Rotorcraft with variable incident wing | |
| MX2020011096A (en) | Electric vertical takeoff and landing aircraft. | |
| CN204433041U (en) | Vehicle rudder drive mechanism | |
| US9079655B2 (en) | System for increasing controllability for an aircraft | |
| CN107972847B (en) | Aircraft wing folding mechanism and flap mechanism based on same | |
| CN204279916U (en) | A kind of adjustable horizontal tail | |
| WO2019085148A1 (en) | Unmanned aerial vehicle and lifting and landing gear thereof | |
| CN104477375A (en) | Adjustable horizontal tail | |
| US20210237849A1 (en) | Folding beam for swinging wing | |
| CN204937478U (en) | A kind of Supersonic Cruise Aircraft with scalable canard | |
| CN112550664A (en) | Variable camber wing structure based on shape memory alloy drive | |
| CN105173062A (en) | Slideable divergent trailing edge device | |
| CN104943850A (en) | Main wing retractable type fixed wing airplane | |
| US7717370B2 (en) | L-tail (featuring parabrakes) | |
| CN102849210A (en) | Spherical small unmanned aircraft | |
| CN209108609U (en) | A kind of fixed-wing model plane structure based on carbon beam | |
| CN202526908U (en) | Double-leaf propeller of model plane | |
| US11338907B2 (en) | Actuation assemblies for flight control surfaces | |
| CN209441604U (en) | A kind of small-sized fixed wing aircraft wing | |
| US2373365A (en) | Aircraft structure | |
| CN109353489B (en) | Multifunctional flap structure of unmanned aerial vehicle | |
| CN106110674A (en) | The flight guiding mechanism of the model of an airplane | |
| US8474747B2 (en) | Pivoting stabilising surface for aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150401 |
|
| RJ01 | Rejection of invention patent application after publication |