CN202320773U - Bird collision prevention airplane empennage - Google Patents
Bird collision prevention airplane empennage Download PDFInfo
- Publication number
- CN202320773U CN202320773U CN2011203664699U CN201120366469U CN202320773U CN 202320773 U CN202320773 U CN 202320773U CN 2011203664699 U CN2011203664699 U CN 2011203664699U CN 201120366469 U CN201120366469 U CN 201120366469U CN 202320773 U CN202320773 U CN 202320773U
- Authority
- CN
- China
- Prior art keywords
- leading edge
- empennage
- front edge
- edge reinforcement
- bird
- 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.)
- Withdrawn - After Issue
Links
Images
Landscapes
- Vibration Dampers (AREA)
Abstract
The utility model relates to a bird collision prevention airplane empennage. A front edge reinforcing element with the appearance in an equicrural triangle shape is positioned in the front edge of the empennage, the spanwise part of the front edge reinforcing element is distributed between 0 and 100 percent of a wingspan, the chordwise part of the front edge reinforcing element is distributed between 0 and 30 percent of the empennage, the front edge reinforcing element is sectionally fixed among all spans along the spanwise part of the airplane empennage, and the spans consist of empennage ribs in the front edge of the empennage. The angle of a vertex angle of the front edge reinforcing element is identical to the angle of a vertex angle of a front edge skin of the empennage, in addition, the vertex angle adopts circular arc transition, the radius of the circular arc is 5mm, and the front edge reinforcing element is fixedly connected with a small front beam through a front edge reinforcing element fixing surface. The bird collision prevention airplane empennage has the advantages that the front edge reinforcing element is additionally arranged in the original airplane empennage, after the empennage is collided by a bird body, the front edge skin and a triangular support structure are pasted, the energy of the bird body is divided, and the front beam of the empennage is protected from being broken down, so the internal structure of the front edge of the empennage is further protected from being destroyed, the pneumatic appearance of the empennage is kept, and the goal of enhancing the bird collision prevention performance is realized.
Description
Technical field
The present invention relates to the aeroplane structure design field, specifically is a kind ofly can improve the anti-bird of aircraft and hit the empennage of performance.
Background technology
The bird accident of hitting is meant that the birds of aircraft such as the aircraft of airflight and flight bump against the accident that is taken place.Along with the develop rapidly of civil aviation industry, the civil aircraft bird accident of hitting becomes one of the most serious security threat of civil aviation.Show that according to the relevant report of U.S. United Airlines, Inc in the period of nineteen ninety to 2008, U.S. civil aviaton reports 89727 animals and aircarrier aircraft collision accident altogether, wherein 97.4% cause by flying bird.Relevant data shows that the windward side of aircraft comprises that aircraft windscreen, radome, driving engine, the leading edge of a wing and empennage leading edge are to be vulnerable to the position that bird is hit most.Leading edge structure is inner standing to be had oil piping system or control path, these inner facilities in a single day to receive bird to crash through badly, and catastrophic failure just is difficult to avoid.Therefore on, resolve the problem that the anti-bird of aircraft tail leading edge hits performance and count for much.Clearly stipulate in 631 sections of the 25th in " airplane in transportation category airworthiness standard " that CAAC formulates; The aircraft tail structure Design must guarantee at aircraft after bumping against with 3.6 kilograms (8 pounds) heavy bird; Still can continue safe flight and landing, the speed of aircraft equals the cruising speed of aircraft on selected sea level during collision.Research shows that under high-speed impact, the bird body surface reveals tangible fluid mechanics behavior.
Hit design high-intensity composite material and the simple sandwich constructions of adopting to the anti-bird of empennage leading edge at present more.Mostly its mentality of designing is the function profile of sacrificial structure, absorbs bird body Impact energy with its big as far as possible distortion.A kind of vertical fin leading edge structure of mentioning in pertinent literature like people such as Alessandro Airoldi in addition, its outside face adopts aluminum alloy materials, and is inner then adopt the carbon fiber composite material of being with cellular sandwich.With 4 pounds the bird body speed impact structure with 270 joints, structural failure is obvious in the test.People such as M.A.McCARTHY then propose the leading edge of a wing structure that a kind of skins front edges is the FML composite material.Structure has been born 4 pounds of bumps that the bird body carries out with the speed of 200m/s in the test, and leading edge is breakdown but produce huge distortion.People such as nearest Michele Guida have proposed a kind of sandwich leading edge structure again, and the sandwich construction two-layer panel adopts FML composite material and metallic material respectively, and sandwich layer is a honeycomb.Bird body with 8 pounds in the process of the test clashes into structure with the speed of 250 joints, and leading edge is not breakdown as a result, but total has produced very big distortion.Can find out that its manufacturing cost of existing structure design is very expensive, total or breakdown, or produce greatly distortion, it is unsatisfactory that its anti-bird is hit effect.
Hit the large deformation damage that exists in the prior art and the defective of high cost for overcoming the anti-bird of aircaft configuration, Northwestern Polytechnical University has proposed a kind ofly can strengthen the horizontal tail leading edge that the anti-bird of aircraft is hit performance in application number is 201010554079.4 application for a patent for invention.This horizontal tail leading edge comprises skins front edges 1, honeycomb sandwich layer 2, is positioned at the reinforcement 3 and the wing lining 4 of horizontal tail leading edge.Wherein, between honeycomb sandwich layer 2, leading edge reinforcement 3 and wing lining 4 are all respectively striden in being arranged in the leading edge of a wing along exhibition; Wherein, leading edge reinforcement 3 is tri-prismoid, and an angle of this leading edge reinforcement is positioned at the front end place of the leading edge of a wing; The last honeycomb sandwich layer of parallelogram and following honeycomb sandwich layer are separately fixed at the inside face up and down of skins front edges, and a hypotenuse of last honeycomb sandwich layer and following honeycomb sandwich layer all cooperates with a side surface of leading edge reinforcement; The wing lining is fixed on the surface of two honeycomb sandwich layers, leading edge reinforcement.Above-mentioned horizontal tail leading edge structure is after suffering bird body bump, though the bird body has played protective effect to the wing lining after cutting apart, the problem that this structure exists is: following honeycomb sandwich layer is a soft material; Under the effect of bird body strong wallop, produce very big conquassation distortion, make the support stiffness of skins front edges diminish, cause skins front edges to lose efficacy; It is thus clear that; The major cause that covering lost efficacy is that its support stiffness reduces, and the skins front edges inefficacy can have a strong impact on the aeroperformance of horizontal tail in the flight course, so; Take all factors into consideration anti-bird and hit performance and pneumatic performance design, this applicability that can strengthen the horizontal tail leading edge that the anti-bird of aircraft hits performance is not strong.
Summary of the invention
Be difficult in the aircraft tail structure design take into account the defective that anti-bird is hit performance and aerodynamic configuration for overcoming, the present invention proposes a kind of anti-bird and knock the tail wing away.
The present invention includes empennage skins front edges, little front-axle beam, rib, big front-axle beam, leading edge cabin covering and leading edge reinforcement.The leading edge reinforcement is positioned at the empennage leading edge, and it is opened up to being distributed between the span 0～100% its tangential being distributed between the empennage 0～30%; The leading edge reinforcement along aircraft tail exhibition in segmentation is fixed on the empennage leading edge by rib constitute respectively stride between.
The profile of described leading edge reinforcement is equicrural triangle.The angle of leading edge reinforcement drift angle is identical with the angle of empennage skins front edges drift angle, and this drift angle is arc transition, and the radius of circular arc is 5mm; The leading edge reinforcement is captiveed joint with little front-axle beam through leading edge reinforcement stationary plane.
Two sides of said leading edge reinforcement all have flanging, and this flanging is positioned at the same surface of said leading edge reinforcement, and all to the interior lateral buckling of leading edge reinforcement, have constituted leading edge reinforcement stationary plane.
The leading edge reinforcement has been installed in the present invention additional in aircraft tail, strengthen the purpose that the anti-bird of aircraft is hit performance thereby reach, and leading edge reinforcement profile is V-shaped.Structure is cut the bird body through the gusseted of self; After empennage receives bird body bump; Skins front edges and gusseted structure stick together, and cut apart the energy of bird body, not only protect the empennage front-axle beam not breakdown; Thereby further protect empennage leading edge inner structure not to be damaged, and well kept the aerodynamic configuration of empennage.
Said empennage leading edge structure is made up of skins front edges, little front-axle beam and leading edge reinforcement, and said structure spare is processed by aluminum alloy materials.Wherein empennage leading edge leading edge reinforcement spare is the dull and stereotyped isoceles triangle shape that forms that bends, and triangular apex is that radius is the circular arc of 5mm, and leading edge reinforcement spare right ends and little front-axle beam carry out bolted connection or rivet.Except that skins front edges, all parts of structure are all inner at empennage, open up to arrangement along whole empennage leading edge is inner.
The present invention has taken into full account the characteristics that bird is hit problem, and promptly the bird body shows the fluid mechanics behavior in knockout process, have very high energy; To this energy, if " hard stifled " certainly will be caused very large deformation or damage to structure; So, preferably adopt the way of dredging, with the energy dispersion of bird body; The present invention has been cut apart the bird body through the built-in leading edge reinforcement spare of empennage, becomes positive bump into tiltedly clashing into, and has reasonably disperseed the energy of bird body bump.Thin skins front edges has absorbed the energy that the bird body is cut apart trailing portion through deformation failure, and the leading edge reinforcement has then guaranteed the safety of vertical fin leading edge inner structure, and because its distortion is less, has stoped subsiding of covering, guaranteed the aerodynamic configuration of empennage.
The present invention changes energy dispersive into by original absorption energy, has cut apart the bird body through the built-in leading edge reinforcement of leading edge, becomes positive bump into tiltedly clashing into, and has reasonably disperseed the energy of bird body bump, has effectively improved the anti-bird of structure and has hit performance.
Because the bird body is cut apart; Remaining bird body after cutting apart slips along two sides, the empennage covering layer left and right sides; The built-in leading edge reinforcement of leading edge has stoped subsiding of covering; Make leading edge structure can not produce the very big distortion that occurs in the design before, kept the aerodynamic configuration of empennage leading edge as much as possible, be applicable to any beam edge structure that possibly suffer bird strike on the leading edge of a wing and the aircraft.
Among the present invention; It is inner that the leading edge reinforcement that on empennage, increases is installed in the empennage leading edge; Can not impact, and making is simple, cost is low, is applicable to any Liang Yuan position that possibly suffer bird strike on empennage, the leading edge of a wing and the aircraft to the aircraft aeroperformance.
The present invention on principle, taken into full account application number be exist in 201010554079.4 the invention owing to support the honeycomb sandwich layer insufficient strength of covering; Cause skins front edges in the bird body knockout process that the weak point of tear failure has taken place, the present invention adopts rigidity preferred metal three-legged structure as reinforcing member.The technical scheme of being taked makes the empennage leading edge not only produce cutting action to the bird body, and the rigidity of the reinforcing member of empennage covering below is enough good, otherwise can produce the situation that covering subsides and lost efficacy.
In the technical scheme that the present invention takes, should consider the rigidity requirement of reinforcement, also need take the requirement of airplane design into account to weight.The present invention has taken into full account the structure of leading edge reinforcement and the relation of rigidity when the structure of confirming the leading edge reinforcement and shock resistance, when guaranteeing required rigidity, make the structural weight of leading edge reinforcement minimum.
The present invention has taken into full account after the reinforcement of empennage leading edge, the relation between wing impact resistant capability and the wing weight, and for this reason, the applicant has done number of research projects.When being 3mm such as the thickness when the leading edge reinforcement, rigidity is fine, and behind the bird body bump, whole empennage leading edge distortion is very little, but this moment the leading edge reinforcement weight reach 8.1kg, it is unfavorable that the loss of weight of whole aircraft is brought.When through after repeatedly calculating and testing, when electing leading edge reinforcement thickness as 2.5mm, the weight of empennage is reduced, and behind bird body bump, whole empennage leading edge distortion is very little, has both satisfied anti-bird and has hit designing requirement, has satisfied the pneumatic property requirement of empennage again.
Description of drawings
Fig. 1 knocks the structural representation of machine horizontal tail leading edge away for anti-bird in the prior art;
Fig. 2 hits numerical simulation result deformation failure figure for the anti-bird of the present invention;
Fig. 3 is a structural representation of the present invention;
Fig. 4 is that the A of Fig. 3 is to scheme drawing;
Certain strides the structural representation of empennage to Fig. 5 among the embodiment;
Fig. 6 is that the A of Fig. 5 is to scheme drawing.Wherein:
1. skins front edges 2. honeycomb sandwich layers 3. reinforcements 4. wing linings 5. empennage skins front edges
6. leading edge reinforcement 7. little front-axle beam 8. ribs 9. big front-axle beam 10. leading edge cabin coverings
11. leading edge reinforcement stationary plane
The specific embodiment
Present embodiment is that the anti-bird that is used for certain type machine knocks the tail wing away.
As shown in Figure 6, present embodiment is that aircraft tail of the prior art is improved, to realize the object of the invention.Present embodiment comprises empennage skins front edges 5, leading edge reinforcement 6, little front-axle beam 7, rib 8, big front-axle beam 9 and leading edge cabin covering 10.Empennage skins front edges 5 all adopts the 2024-T3 aluminum alloy materials with leading edge cabin covering 10, and thickness is identical, is 1.62mm.All the other each parts all adopt the 7075-T6 aluminum alloy materials, and little front-axle beam 7 thickness are 3.5mm, and the thickness of rib 8 is 2.54mm, and big front-axle beam 9 thickness are 3.5mm.
The inside face of the drift angle of leading edge reinforcement 6 and empennage leading edge top covering 5 is in the nature contact condition, and two leading edge reinforcement stationary planes 11 and little front-axle beam 7 are connected through rivet.It is the high-strength rivet of 4mm that described rivet adopts diameter, and rivet is arranged and is spaced apart 20mm.
During assembling, at first skins front edges 5 is fixing with little front-axle beam 7 with double rivet, leading edge cabin covering 10 and little front-axle beam 7, greatly front-axle beam 9, being connected of rib 8 all adopt double rivet, rib 8 is with little front-axle beam 7, adopt single rivet greatly being connected of front-axle beam 9.Make the drift angle and the empennage skins front edges 5 of leading edge reinforcement 6 be in the nature contact condition, two leading edge reinforcement stationary planes 11 and little front-axle beam 7 are connected through rivet.
Claims (2)
1. an anti-bird knocks the tail wing away, comprises empennage skins front edges, little front-axle beam, rib, big front-axle beam and leading edge cabin covering; It is characterized in that, also comprise the leading edge reinforcement; The leading edge reinforcement is positioned at the empennage leading edge, and it is opened up to being distributed between the span 0～100% its tangential being distributed between the empennage 0～30%; The leading edge reinforcement along aircraft tail exhibition in segmentation is fixed on the empennage leading edge by rib constitute respectively stride between;
The profile of described leading edge reinforcement is equicrural triangle; The angle of leading edge reinforcement drift angle is identical with the angle of empennage skins front edges drift angle, and this drift angle is arc transition, and the radius of circular arc is 5mm;
The leading edge reinforcement is captiveed joint with little front-axle beam through leading edge reinforcement stationary plane.
2. a kind of according to claim 1 anti-bird knocks the tail wing away; It is characterized in that two sides of said leading edge reinforcement all have flanging, this flanging is positioned at the same surface of said leading edge reinforcement; And, constituted leading edge reinforcement stationary plane all to the interior lateral buckling of leading edge reinforcement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203664699U CN202320773U (en) | 2011-09-29 | 2011-09-29 | Bird collision prevention airplane empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203664699U CN202320773U (en) | 2011-09-29 | 2011-09-29 | Bird collision prevention airplane empennage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202320773U true CN202320773U (en) | 2012-07-11 |
Family
ID=46432763
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203664699U Withdrawn - After Issue CN202320773U (en) | 2011-09-29 | 2011-09-29 | Bird collision prevention airplane empennage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202320773U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN104015936A (en) * | 2012-11-28 | 2014-09-03 | 空中客车西班牙运营有限责任公司 | Aircraft lifting surface and manufacturing method of main supporting structure thereof |
| CN104129496A (en) * | 2013-05-03 | 2014-11-05 | 波音公司 | Protective finish for wing tip devices |
| CN108099281A (en) * | 2017-12-27 | 2018-06-01 | 山东非金属材料研究所 | A kind of plane nose hits baffle with the anti-bird of composite material |
| CN108216568A (en) * | 2018-01-10 | 2018-06-29 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
| CN108248814A (en) * | 2018-01-10 | 2018-07-06 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
| CN110341935A (en) * | 2019-07-26 | 2019-10-18 | 哈尔滨工业大学 | It is a kind of to open up to telescopic morphing wing |
| CN114771804A (en) * | 2022-06-17 | 2022-07-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Asymmetric groove liquid film directional splashing pneumatic structure |
-
2011
- 2011-09-29 CN CN2011203664699U patent/CN202320773U/en not_active Withdrawn - After Issue
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390520B (en) * | 2011-09-29 | 2014-06-18 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN104015936A (en) * | 2012-11-28 | 2014-09-03 | 空中客车西班牙运营有限责任公司 | Aircraft lifting surface and manufacturing method of main supporting structure thereof |
| CN104015936B (en) * | 2012-11-28 | 2017-03-29 | 空中客车西班牙运营有限责任公司 | Aircraft lift face and its manufacture method of main supporting structure |
| CN104129496B (en) * | 2013-05-03 | 2021-08-10 | 波音公司 | Protective overcoat for wingtip devices |
| CN104129496A (en) * | 2013-05-03 | 2014-11-05 | 波音公司 | Protective finish for wing tip devices |
| CN108099281A (en) * | 2017-12-27 | 2018-06-01 | 山东非金属材料研究所 | A kind of plane nose hits baffle with the anti-bird of composite material |
| CN108216568A (en) * | 2018-01-10 | 2018-06-29 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
| CN108216568B (en) * | 2018-01-10 | 2021-04-23 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
| CN108248814A (en) * | 2018-01-10 | 2018-07-06 | 中国商用飞机有限责任公司 | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge |
| CN110341935A (en) * | 2019-07-26 | 2019-10-18 | 哈尔滨工业大学 | It is a kind of to open up to telescopic morphing wing |
| CN110341935B (en) * | 2019-07-26 | 2022-07-15 | 哈尔滨工业大学 | Expansion-direction telescopic type morphing wing |
| CN114771804A (en) * | 2022-06-17 | 2022-07-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Asymmetric groove liquid film directional splashing pneumatic structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102390520B (en) | Empennage capable of improving bird strike resistance of airplane | |
| CN202320773U (en) | Bird collision prevention airplane empennage | |
| CN102030102B (en) | Horizontal tail front edge for bird strike-resisting airplane | |
| US7866605B2 (en) | Energy absorbing impact band and method | |
| CN106697258B (en) | A kind of leading edge of a wing that can be improved bird strike resistance of airplane and hit performance | |
| US8678314B2 (en) | Impact resistant and damage tolerant aircraft fuselage | |
| US8123167B2 (en) | Impact resistant aircraft leading edge structures and aircraft including the same | |
| CN106986003B (en) | A kind of anti-bird having monocline plate knocks tail nose of wing away | |
| CN108016600B (en) | Panel structure for an aircraft and method for the production thereof | |
| US9187170B2 (en) | Aircraft airfoil, and an aircraft provided with such an airfoil | |
| US10131415B2 (en) | Airframe leading edge | |
| CN112407244B (en) | Aircraft leading edge assembly | |
| CN201971150U (en) | Aircraft tailplane with front edge reinforced element | |
| US11597497B2 (en) | Leading edge structure for an aerodynamic surface of an aircraft | |
| CN108216568B (en) | Aircraft bird strike resistant front edge and support for aircraft bird strike resistant front edge | |
| US20130056582A1 (en) | Landing gear mounted under an aircraft wing | |
| CN216332809U (en) | Helicopter tail servo fairing capable of resisting bird collision | |
| CN104386239B (en) | A kind of anti-rollover airframe steel framework structure | |
| CN206939049U (en) | A kind of leading edge of a wing structure | |
| CA2764340C (en) | Optimization of structures subjected to hot gas streams | |
| EP4124565A1 (en) | A reinforced leading edge section for an aircraft | |
| CN115783239A (en) | Anti-bird-collision reinforcement for front edge of A-shaped airplane tail wing | |
| CN113772108B (en) | Tail wing front edge bird divider structure | |
| CN114084358A (en) | Bird collision resisting structure of airplane | |
| CZ32880U1 (en) | Airplane wing leading edge |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20120711 Effective date of abandoning: 20140618 |
|
| RGAV | Abandon patent right to avoid regrant |