CN202213713U - Horizontal tail adjusting mechanism - Google Patents
Horizontal tail adjusting mechanism Download PDFInfo
- Publication number
- CN202213713U CN202213713U CN2011203280006U CN201120328000U CN202213713U CN 202213713 U CN202213713 U CN 202213713U CN 2011203280006 U CN2011203280006 U CN 2011203280006U CN 201120328000 U CN201120328000 U CN 201120328000U CN 202213713 U CN202213713 U CN 202213713U
- Authority
- CN
- China
- Prior art keywords
- central wing
- wing box
- screw rod
- tailplane
- box
- 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.)
- Expired - Fee Related
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses a horizontal tail adjusting mechanism which is positioned in an aircraft body at the rear part and comprises a central wing box, a screw rod lifer, an actuating mechanism and a change speed gear box, wherein the aircraft body end of the actuating mechanism is coupled on a connecting piece which is fixed on a front reinforcing frame. The output end of the actuating mechanism is fixedly connected with one end of a screw rod in the screw rod lifer through the change speed gear box. A front beam connector of the central wing box is fixedly connected with a lifting piece in the screw rod lifter through a universal joint. The central wing box is sheathed on a pivot on a rear reinforcing frame of the aircraft body at the rear part through a bearing. The horizontal tail adjusting mechanism has the advantages that the energy consumed by the actuating mechanism is reduced through halving the motor travel distance, and the operating efficiency is obviously improved; and the load carrying capability of the two reinforcing frames of the central wing box and the aircraft body at the rear part is improved, so that the weight of the adjusting mechanism is reduced, the whole weight of an aircraft is reduced, and the safety and the reliability of the aircraft are improved.
Description
Technical field
The utility model belongs to the aeronautic structure technical field, specifically, is a kind of novel tailplane regulating mechanism of stroke that reduces the tailplane regulating mechanism.
Background technology
Along with starting of China's large-sized civil aircraft project; Improve the civil aircraft design level in order to design and produce the performance imagination that must move heaven and earth of the large-sized civil aircraft with international competitiveness; And detailed design is the important embodiment of civil aircraft design level, so the attention details of must doing everything possible.
For the tailplane design of subsonic aircraft, the most serious state of consideration is a take-off and landing, can produce bigger nose-down pitching moment because put down the wing flap aircraft.For guaranteeing the aircraft landing balance and take off and lift front-wheel that tailplane must be biased to greatest extent, for aircraft provides enough nose-up pitching moments.Therefore, as long as the driving efficiency of tailplane can guarantee to satisfy the balance requirement of taking off and landing, will satisfy the flight balance of getting off the plane automatically during design at various possible lift coefficient.
According to the pertinent data introduction, after the nineties in last century, there is trunkliner all to adopt the adjustable tailplane of stagger angle in the world above 70%.With respect to the tailplane of other form, this form horizontal tail both can satisfy the trim requirement in take-off and landing stage, can reduce trim resistance, horizontal tail area and weight again.Tailplane regulating mechanism in the adjustable tailplane of this stagger angle is to be used for guaranteeing aircraft balance in pitch and stability and the enforcement important mechanism that vertical (pitching) handled to aircraft; Its driving efficiency and reliability are the principal elements that influences aircraft safety, so it is very urgent to improve the detailed design level of horizontal tail central wing box.
The adjustable tailplane of the stagger angle that existing civil aircraft generally adopts, the horizontal stabilizer of adjustable stagger angle docks with the rear portion fuselage through screw brake on the back reinforced bulkhead that is fixed on the rear portion fuselage and pivot.Tailplane regulating mechanism 2 is installed in rear portion fuselage 1; Constitute by central wing box 201, screw elevator 202, actuation mechanism 203; As shown in Figure 1, wherein, screw elevator 202, actuation mechanism 203 are installed on the preceding reinforced bulkhead 101 in the rear portion fuselage 1; The front-axle beam joint screw thread of central wing box 201 is socketed on the screw rod in the screw elevator 202, and the back rest adaptor cup jointing of central wing box 201 is on the pivot 103 on the back reinforced bulkhead 102 of rear portion fuselage 1.Thus; Actuation mechanism 203 with transmission of power to screw elevator 202; The screw rod that drives in the screw elevator 202 rotates; Rotation through screw rod moves up and down the preceding beam splice of central wing box 201 on screw rod thus, and the rotation that whole central wing box 201 is produced around pivot rotates thereby drive tailplane.
Yet also there is certain defective in this mechanism, and that is exactly; The central wing box is with after tailplane is connected, and total will produce with the back reinforced bulkhead and interfere during adjusting, for this reason in horizontal tail and central wing box bonded assembly place; Need stay certain opening; But because the angle very little (generally about 10 °) that tailplane is regulated, thus opening urine can meet the demands, can not influence the intensity of whole tailplane and central wing box.Also having a kind of method is that the back reinforced bulkhead is broken off, and the central wing box is passed from gap, but need structure be strengthened at gap.
Summary of the invention
In order to address the above problem; The utility model provides a kind of novel tailplane regulating mechanism; Through change tailplane central wing box and the interaxle level attitude of pivot, thus the driving efficiency of raising regulating mechanism, depowering consumption; Improve the stressing conditions of horizontal tail central wing box simultaneously, increase the safety and the reliability of connection structure.
A kind of tailplane regulating mechanism is positioned at the rear portion fuselage interior, comprises that central wing box, screw elevator, actuation mechanism, speed-change gear box constitute.Wherein, the body end of actuation mechanism is coupling on attaching parts, and attaching parts is fixed on the preceding reinforced bulkhead.Said screw elevator is made up of screw rod and lifters, and the lifters screw collar is connected on the screw rod, and lifters can be at the screw shaft upward movement.The mouth of actuation mechanism is connected through one end of the leading screw in speed-change gear box and the screw elevator.The preceding beam splice of central wing box is connected through the lifters in Hooke's coupling and the screw elevator.The central wing box is connected on through bearing carrier ring on the pivot on the back reinforced bulkhead of rear portion fuselage.
Thus, actuation mechanism drives the speed-change gear box motion, after slowing down through speed-change gear box; With the screw rod of transmission of power in the screw elevator; The drive screw rod rotates, and the rotation through screw rod makes lifters on screw rod, carry out dipping and heaving thus, thereby drives the preceding beam splice dipping and heaving of central wing box through Hooke's coupling; Make whole central wing box produce rotation, finally drive tailplane and rotate around pivot.
The advantage of the utility model is:
1, the actuating motor stroke reduces by half in the utility model regulating mechanism, and driving efficiency obviously improves;
2, the utility model regulating mechanism has improved the stressed of central wing box and two reinforced bulkheads of rear portion fuselage, thereby alleviates the weight of regulating mechanism, has also just alleviated the weight of whole aircraft, improves the safety and the reliability of aircraft;
3, the utility model regulating mechanism is because reducing and wing box and two stressed improvement of reinforced bulkhead of rear portion fuselage of actuator makes the energy that actuation mechanism consumed reduce.
Description of drawings
The horizontal tail central wing box regulating mechanism connection schematic side view of Fig. 1 for generally adopting in the existing adjustable tailplane of stagger angle;
Fig. 2 is the utility model tailplane regulating mechanism connection schematic side view;
Fig. 3 is a tailplane regulating mechanism johning knot composition in the utility model;
Fig. 4 is central wing box path of motion contrast scheme drawing in existing horizontal tail central wing box and the utility model.
Among the figure:
Reinforced bulkhead 103-pivot behind the reinforced bulkhead 102-before the fuselage 101-of 1-rear portion
2-tailplane regulating mechanism 201-central wing box 202-screw elevator 203-actuation mechanism
The 204-speed-change gear box constitutes 205-attaching parts 201a-Hooke's coupling 202a-screw rod
The 202b-lifters
The specific embodiment
Come the utility model is described further below in conjunction with accompanying drawing.
A kind of novel tailplane regulating mechanism of the utility model; Like Fig. 2, rear portion fuselage 1 inside that is positioned at shown in Figure 3; Comprise that central wing box 201, screw elevator 202, actuation mechanism 203, speed-change gear box constitute 204, screw elevator 202, actuation mechanism 203 are installed on the preceding reinforced bulkhead 101 in the rear portion fuselage 1 with speed-change gear box 204.Wherein, Actuation mechanism 203 is electro-motor, steering wheel or hydraulic actuator; The body end of actuation mechanism 203 is coupling on attaching parts 205, before attaching parts 205 is fixed on the reinforced bulkhead 101, realizes the relative positioning of 101 of actuation mechanism 203 and preceding reinforced bulkheads through attaching parts 205.Said screw elevator 202 is made up of screw rod 202a and lifters 202b, and lifters 202b screw collar is connected on the screw rod 202a, and lifters 202b can motion on screw rod 202a is axial.The mouth of actuation mechanism 203 is connected through screw rod 202a one end among speed-change gear box 204 and the screw elevator 202b.The preceding beam splice of central wing box 201 is connected through the lifters 202b in Hooke's coupling 201a and the screw elevator 202.Central wing box 201 is connected on through bearing carrier ring on the pivot 103 on the back reinforced bulkhead 102 of rear portion fuselage 1, and the axis of pivot 103 is in the center of central wing box 201 opposite flanks.Thus, actuation mechanism 203 drives speed-change gear box 204 motions, after slowing down through speed-change gear box 204; With transmission of power screw rod 202a of 202 in the screw elevator; Drive screw rod 202a and rotate, the rotation through screw rod 202a makes lifters 202b on screw rod 202a, carry out dipping and heaving thus, thereby drives the preceding beam splice dipping and heaving of central wing box 201 through Hooke's coupling 201a; The rotation that whole central wing box 201 is produced around pivot 103 finally drives tailplane and rotates.Because central wing box 201 is socketed on the pivot 103.
As shown in Figure 4, establish the rotation pivot of O point for existing horizontal tail central wing box, A is the point of connection of lifting screw mechanism and central wing box, then AO is its moving radius; If the central wing box has been regulated angle [alpha] and arrived the BO position, then the move distance of existing horizontal tail central wing is the length of arc AB.And in the utility model, the pivot of establishing central wing box 201 is similarly the O point, and the point of action of screw elevator is the C point, can know that central wing box 201 moving radius are CO, and AO should be 2 times of CO length; Arrive the D point if central wing box 201 is regulated identical angle [alpha], then the length of arc CD is the distance of central wing box 201 motions, and the length of arc CD should be length half the of arc AB.Therefore, when central wing box 201 in the utility model was regulated identical angle with existing horizontal tail central wing box, the move distance of the utility model central wing box 201 was the half the of common central wing box move distance.
Establish in addition in the existing horizontal tail central wing box and be full of fuel oil, then the center of gravity of existing common central wing box is positioned at the C point, and the center of gravity of central wing box 201 is positioned at the O point in the utility model.Behind regulating mechanism movement angle α, the center of gravity of existing common central wing box arrives the D point, and the center of gravity of the novel middle central wing box 201 of this reality still is positioned at the O point.
To sum up can know; When tailplane needed the identical angle of deflection, the half the of actuation mechanism 203 strokes in the existing regulating mechanism that only need move of the actuation mechanism 203 in the utility model regulating mechanism just can reach identical regulating effect; Therefore, with the driving efficiency of the empennage of improving the standard greatly.Can know by the power transmission analysis; Reinforced bulkhead 101 got on back reinforced bulkhead 102 before power that tailplane is suffered and moment all will pass to through central wing box 201; Therefore the regulating mechanism of the utility model can be optimized the stressed of rear portion fuselage 1 preceding reinforced bulkhead 101 and back reinforced bulkhead 102 central wing boxes 201; Thereby can alleviate structural weight, improve the safety and the reliability of aircraft.In addition, present generation aircraft is arranged fuel tank, to make full use of the space usually in order to increase voyage at central wing box 201 places; But central wing box 201 drives the fuel tank motion and will produce huge energy dissipation when motion simultaneously, and the utility model central wing box 201 can reduce this energy dissipation to greatest extent, thereby reduces oil consumption.
Claims (3)
1. a tailplane regulating mechanism is positioned at the rear portion fuselage interior, it is characterized in that: comprise that central wing box, screw elevator, actuation mechanism, speed-change gear box constitute;
Wherein, the body end of actuation mechanism is coupling on attaching parts, and attaching parts is fixed on the preceding reinforced bulkhead; The mouth of actuation mechanism is connected through one end of the screw rod in speed-change gear box and the screw elevator; The preceding beam splice of central wing box is connected through the lifters in Hooke's coupling and the screw elevator; The central wing box is connected on through bearing carrier ring on the pivot on the back reinforced bulkhead of rear portion fuselage.
2. a kind of according to claim 1 tailplane regulating mechanism is characterized in that: said actuation mechanism is electro-motor, steering wheel or hydraulic actuator.
3. a kind of according to claim 1 tailplane regulating mechanism, it is characterized in that: the axis of said pivot is in the center of central wing box opposite flank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203280006U CN202213713U (en) | 2011-09-02 | 2011-09-02 | Horizontal tail adjusting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203280006U CN202213713U (en) | 2011-09-02 | 2011-09-02 | Horizontal tail adjusting mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202213713U true CN202213713U (en) | 2012-05-09 |
Family
ID=46012980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203280006U Expired - Fee Related CN202213713U (en) | 2011-09-02 | 2011-09-02 | Horizontal tail adjusting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202213713U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963521A (en) * | 2012-11-09 | 2013-03-13 | 北京航空航天大学 | Central wing of horizontal tail of civil airplane |
| CN108100230A (en) * | 2017-12-01 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter horizontal tail wing box |
-
2011
- 2011-09-02 CN CN2011203280006U patent/CN202213713U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963521A (en) * | 2012-11-09 | 2013-03-13 | 北京航空航天大学 | Central wing of horizontal tail of civil airplane |
| CN102963521B (en) * | 2012-11-09 | 2015-04-22 | 北京航空航天大学 | Central wing of horizontal tail of civil airplane |
| CN108100230A (en) * | 2017-12-01 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter horizontal tail wing box |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120509 Termination date: 20120902 |