CN115593613B - Light-weight bird strike-resistant airplane horizontal tail front edge - Google Patents
Light-weight bird strike-resistant airplane horizontal tail front edge Download PDFInfo
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- CN115593613B CN115593613B CN202211359553.7A CN202211359553A CN115593613B CN 115593613 B CN115593613 B CN 115593613B CN 202211359553 A CN202211359553 A CN 202211359553A CN 115593613 B CN115593613 B CN 115593613B
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- wedge
- shaped
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- arc
- bar
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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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
Abstract
The invention discloses a light bird strike resistant airplane horizontal tail front edge, which comprises a front skin component, wherein the front skin component consists of a honeycomb core and a bird divider, the honeycomb core is coated between an inner skin and an outer skin, the bird divider comprises an upper wedge-shaped strip, a lower wedge-shaped strip and a rear arc-shaped strip, the upper wedge-shaped strip and the lower wedge-shaped strip are of symmetrical structures, the upper wedge-shaped strip comprises a front section wedge-shaped part, an interruption supporting part and a rear section wedge-shaped part, an obtuse angle is formed between the front section wedge-shaped part and the interruption supporting part, the front section wedge-shaped part of the upper wedge-shaped strip is attached to the inner side of the front section wedge-shaped part of the lower wedge-shaped strip, the arc-shaped strip is attached to the rear section wedge-shaped part of the upper wedge-shaped strip, the rear section wedge-shaped part of the lower wedge-shaped strip, and the rear arc-shaped strip form a cavity.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft tail wing.
Background
The front edge of the horizontal tail of the airplane in the prior art adopts a traditional metal structure, so that the problem of heavy weight exists, and the airplane which is served in a marine environment for a long time, such as the airplane, has poor acid and alkali corrosion resistance of metal materials. Compared with a metal material, the composite material has high specific strength, high specific rigidity and high corrosion resistance, and has great advantages in the aspects of design, manufacturability, weight reduction of a structure and the like.
The prior art discloses an empennage that can improve aircraft bird strike resistance, and its publication number is: CN 102390520A, publication date: 2012-3-28, comprising a honeycomb core wrapped between an inner skin and an outer skin and a bird divider formed by bending an aluminum alloy rectangular plate, wherein the bird divider is made of a metal material.
In order to realize the design of reducing the front edge of the horizontal tail of the existing aircraft, on the basis of meeting the anti-bird strike requirement, a composite material structure is considered to replace an original metal structure; the front edge of the horizontal tail is mainly subjected to pneumatic load and inertial load and does not participate in the overall stress of the horizontal tail; the main function is to keep the aerodynamic profile, reduce aircraft resistance, protect main load structure and avoid receiving impact damage. The front edge of the horizontal tail is a dangerous area for bird strike of the airplane, and the flying safety of the airplane is directly affected. The metal structure of the horizontal tail front edge of the prototype is designed into a composite material structure, and under the condition that the aerodynamic appearance of an airplane is unchanged, the advantages of anisotropy and designability of the composite material are utilized, the design criteria such as structural strength, rigidity, damage tolerance, durability, environmental adaptability and the like are comprehensively considered, and the horizontal tail composite material front edge structure is designed around bird strike resistance.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the light bird strike resistant airplane horizontal tail front edge, which solves the problem of reducing weight on the premise of ensuring the protection of a main bearing structure when being damaged by impact, namely, the weight is reduced, and the bird strike resistant airplane horizontal tail front edge is also ensured to have enough strength to prevent bird strike.
The purpose of the invention is realized in the following way: the light bird strike resistant airplane horizontal tail front edge comprises a front skin assembly, wherein the front skin assembly consists of a honeycomb core and a bird divider, the honeycomb core is wrapped between an inner skin and an outer skin, the bird divider comprises a root auxiliary cutter, a middle wedge-shaped cutter and an end auxiliary cutter, the middle wedge-shaped cutter is formed by pulling from the root to the end of the front edge, and the root auxiliary cutter and the end auxiliary cutter are respectively connected with the root auxiliary cutter and the end auxiliary cutter at the root and the end;
the root auxiliary cutter comprises a root arc-shaped connecting part attached to the inner side of the inner skin, a root wedge-shaped decomposition part is arranged on the surface of the root arc-shaped connecting part close to the root, the root wedge-shaped decomposition part penetrates through the root arc-shaped connecting part, and a connecting end part is arranged on the side surface of the root arc-shaped connecting part close to the root;
the middle wedge cutter comprises an upper wedge bar, a lower wedge bar and a rear arc-shaped bar, wherein the upper wedge bar and the lower wedge bar are of symmetrical structures, the upper wedge bar comprises a front section wedge portion, an interruption supporting portion and a rear section wedge portion, an obtuse angle is formed between the front section wedge portion and the interruption supporting portion, the front section wedge portion of the upper wedge bar is attached to the inner side of the front section wedge portion of the lower wedge bar, the arc-shaped bar is attached to the rear section wedge portion of the upper wedge bar and the rear section wedge portion of the lower wedge bar, and a cavity is formed among the upper wedge bar, the lower wedge bar and the rear arc-shaped bar;
the end auxiliary cutter comprises an end arc-shaped connecting part, and an end wedge-shaped decomposition part is arranged on the surface of the end arc-shaped connecting part close to the end part.
The principle of the invention is as follows:
in the practical test process, if the metal material is simply changed into the composite material and the structure is not changed, the impact strength of the composite material is obviously weaker than that of the metal, in addition, the composite material is made into a triangular structure to be demolded with great difficulty, the composite material is made into a triangular tip to have an R angle, the body decomposition effect is not obvious enough, and the test finds that the bird strike prevention capability is obviously weakened and the whole main bearing structure is influenced; therefore, the applicant adjusts the structure, and adjusts the original triangle structure into a structure formed by integrally forming the arc-shaped strips after the upper wedge-shaped strip and the lower wedge-shaped strip which are symmetrical are matched, so that a good bird separating effect can be achieved, and the weight can be reduced.
The features of this structure are described below:
firstly, the front section wedge part of the upper wedge-shaped strip and the front section wedge part of the lower wedge-shaped strip are jointed to form a cutting part, the cutting part is sharp, when a bird strike is encountered, the bird body can be directly decomposed, the structure is different from a hollow tip structure in a triangle, the hollow tip structure is used as a solid triangle structure, and the anti-strike capability is stronger when the bird strike is encountered;
secondly, the middle section supporting part is used as a main stress part, and can bear a large amount of impact force earlier when birds collide under the cooperation of an obtuse angle, so that the overall strength of the bird divider is ensured, the thickness of the bird divider is not adjustable, the wedge-shaped structure design of the rear end is that the main receiving area is close to the inner side of the wedge-shaped strip when the force is transmitted from the front end to the rear end, the weight reduction design is considered, and the wedge-shaped surface treatment of materials can be reduced on the outer side; in addition, the stressed area of the wedge-shaped strip formed by the obtuse angle structure is larger than that of the triangular plane structure;
thirdly, the design of the rear arc-shaped strip structure forms an elastic stress area, namely when the impact force at the front end is transmitted to the rear, the middle section supporting part and the rear section wedge-shaped part can slightly elastically deform and reset after the external force is eliminated, so that a good buffering effect is achieved, and the rear arc-shaped strip structure has better toughness compared with a metal plane structure;
fourth, the middle part wedge cutterbar both ends need be fixed and just play and divide the bird effect, because structural design reason, root, tip rib can't fix the middle part wedge cutterbar, and root and tip auxiliary cutter can play the effect of middle part wedge cutterbar, and simultaneously, the middle part wedge cutterbar mainly depends on the honeycomb to support, and the honeycomb can not run through whole leading edge, so root and tip cutterbar continue and strengthen the effect that wedge structure divides the bird.
Compared with the prior art, the invention has the beneficial effects that:
through the structural design, the invention can reliably protect the main bearing structure when being damaged by impact, and lighten the weight of the front edge of the horizontal tail of the aircraft.
As a further limitation of the present invention, the cavity is filled with a foaming glue. The design of the foaming glue further enhances the impact resistance effect of the bird distributor, and the foaming glue.
In order to further enhance the overall strength, a plurality of rib boxes are further arranged on the inner side of the front skin assembly.
In order to further reduce the weight, the rib box is provided with a weight reducing hole.
As a further definition of the invention, the outer skin adopts a laminate structure.
As a further definition of the invention, the outer surface of the outer skin is covered with a lightning protection surface film. The design can improve the lightning protection effect of the invention.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a schematic perspective view of a second embodiment of the present invention.
Figure 3 is a side view of the front skin assembly of the present invention.
FIG. 4 is a schematic diagram of the end face structure of the middle wedge cutter according to the present invention.
FIG. 5 is a schematic view of the root assist cutter of the present invention.
Fig. 6 is a schematic perspective view of a root auxiliary cutter according to the present invention.
FIG. 7 is a schematic view of an end assist cutter assembly according to the present invention.
Fig. 8 is a schematic perspective view of an end auxiliary cutter according to the present invention.
The novel lightning protection device comprises an inner skin 1, an outer skin 2, a 3 honeycomb core, a 4 middle wedge-shaped cutter, a 4a upper wedge-shaped strip, a 4b lower wedge-shaped strip, a 4c rear arc-shaped strip, a 4d front section wedge-shaped part, a 4e interrupt supporting part, a 4f rear section wedge-shaped part, a 5 root auxiliary cutter, a 5a arc-shaped connecting part, a 5b wedge-shaped decomposing part, a 5c connecting end part, a 6 end auxiliary cutter, a 6a end arc-shaped connecting part, a 6b end wedge-shaped decomposing part, a 7 rib box, an 8 lightning protection surface film and 9 foaming glue.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The light bird strike resistant airplane horizontal tail front edge comprises a front skin assembly and a rib box 7, wherein the front skin assembly is formed by gluing a honeycomb core 3 and a bird divider, wherein the honeycomb core 3 is wrapped between an inner skin 1 and an outer skin 2, the honeycomb core 3 is divided into an upper honeycomb core 3 and a lower honeycomb core 3 by the bird divider, the rib box 7 is arranged on the inner side of the inner skin 1 and is connected with the inner skin 1 through a drawing pin, the rib box 7 is processed into a shape matched with the inner surface of the inner skin 1 and is tightly attached to the inner surface of the inner skin 1, a lightening hole is formed in the rib box 7, the outer skin 2 is of a laminated plate structure, the outer surface of the outer skin 2 covers a lightning protection surface film 8, and the thicknesses of the inner skin 1 and the outer skin 2 are 1mm;
the bird divider comprises a root auxiliary cutter 5, a middle wedge-shaped cutter 4 and an end auxiliary cutter 6;
the root auxiliary cutter 5 is made of metal materials and is arranged at the root of the front skin assembly, the root auxiliary cutter 5 comprises a root arc-shaped connecting part 5a, the root arc-shaped connecting part 5a is attached to the inner side of the inner skin 1, a root wedge-shaped decomposition part 5b is arranged on the surface of the root arc-shaped connecting part 5a near the root, a connecting end part 5c is further arranged on the side surface of the root arc-shaped connecting part 5a at the root, and the root arc-shaped connecting part 5a is connected with the inner skin 1 and the bird distributor by using drawing nails;
the middle wedge cutter 4 comprises an upper wedge-shaped strip 4a, a lower wedge-shaped strip 4b and a rear arc-shaped strip 4c, wherein the upper wedge-shaped strip 4a and the lower wedge-shaped strip 4b are of symmetrical structures, the upper wedge-shaped strip 4a comprises a front section wedge-shaped part 4d, an interruption supporting part 4e and a rear section wedge-shaped part 4f, an obtuse angle is formed between the front section wedge-shaped part 4d and the interruption supporting part 4e, the embodiment is about 150 ℃, the front section wedge-shaped part 4d is divided into a front half equal-thickness part and a rear half-section wedge-shaped part, the front section wedge-shaped part 4d of the upper wedge-shaped strip 4a and the inner side of the front section wedge-shaped part 4d of the lower wedge-shaped strip 4b are bonded together to form a solid triangle structure with a spike at the front end, the arc-shaped strip and the rear section wedge-shaped part 4f of the upper wedge-shaped strip 4a and the rear section wedge-shaped part 4f of the lower wedge-shaped strip 4b are bonded together to form a tough part, the arc-shaped strip at the moment can be used as a ligament to be understood, a cavity is formed between the upper wedge-shaped strip 4a, the lower wedge-shaped strip 4b and the rear arc-shaped strip 4c, the rear arc-shaped strip 4c and the cavity is filled with foaming glue 9, the cavity is formed between the front section and the arc-shaped strip 4c, the front section 4c and the arc-shaped 4c, the front section 4c, and the front section has the thickness is 5mm and the thickness and the arc-shaped 4 c.
The end auxiliary cutter 6 is made of metal materials and is arranged at the end part of the front skin assembly, the end auxiliary cutter 6 comprises an end arc-shaped connecting part 6a, the end arc-shaped connecting part 6a is attached to the inner side of the inner skin 1, an end wedge-shaped decomposing part 6b is arranged at the position, close to the end part, of the surface of the end arc-shaped connecting part 6a, and the end arc-shaped connecting part 6a is connected with the inner skin 1 and the bird distributor by drawing nails.
The invention adopts a honeycomb sandwich structure, a middle wedge-shaped cutter 4 is formed from the root to the end of the front edge in a pulling way, the root and the end are respectively connected with a root auxiliary cutter 5 and an end auxiliary cutter 6, and the front edge of the horizontal tail adopts a design scheme that three structures absorb bird energy layer by layer: the first layer is a front edge outer skin 2, adopts a laminated plate structure and only absorbs part of energy; the second layer is of a wedge-shaped structure, so that the bird body can be effectively divided into two halves, energy is well dispersed, and the loss of the structure is reduced. The third layer is a honeycomb sandwich structure, and the honeycomb core 3 has light weight and good buffering and energy absorbing performance at the middle and rear parts of the matched bird distributor.
Compared with the existing metal structure, the invention has the following advantages:
1) The carbon fiber composite material structure can reduce weight, and the carbon fiber composite material has high specific strength and specific rigidity, and is superior to metal materials in performance and light weight;
2) The corrosion resistance is strong; the front edge of the carbon fiber composite material has strong acid and alkali corrosion resistance, and the aircraft needs to have long-term service capacity in marine environment, so that compared with a metal material, the carbon fiber has enough guarantee on corrosion resistance;
3) The fatigue resistance is strong; the carbon fiber composite material has excellent fatigue resistance compared with a metal material;
4) The bird strike resistance is good; the wedge-shaped structure can well disperse energy, and the loss of the structure is reduced; the honeycomb sandwich structure has light weight and can better buffer and absorb energy.
The front beam was not allowed to penetrate after a bird with a weight of 3.6 kg (8 lbs) at a speed of 520km/h was required for the test, and the present invention meets the above requirements.
The above description of the embodiments is only for aiding in the understanding of the method of the present invention and its core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.
Claims (6)
1. The light bird strike resistant airplane horizontal tail front edge comprises a front skin assembly, wherein the front skin assembly consists of a honeycomb core and a bird divider, wherein the honeycomb core is wrapped between an inner skin and an outer skin, and the bird divider comprises a root auxiliary cutter, a middle wedge-shaped cutter and an end auxiliary cutter;
the root auxiliary cutter comprises a root arc-shaped connecting part attached to the inner side of the inner skin, a root wedge-shaped decomposition part is arranged on the surface of the root arc-shaped connecting part close to the root, the root wedge-shaped decomposition part penetrates through the root arc-shaped connecting part, and a connecting end part is arranged on the side surface of the root arc-shaped connecting part close to the root;
the middle wedge cutter comprises an upper wedge bar, a lower wedge bar and a rear arc-shaped bar, wherein the upper wedge bar and the lower wedge bar are of symmetrical structures, the upper wedge bar comprises a front section wedge portion, an interruption supporting portion and a rear section wedge portion, an obtuse angle is formed between the front section wedge portion and the interruption supporting portion, the front section wedge portion of the upper wedge bar is attached to the inner side of the front section wedge portion of the lower wedge bar, the arc-shaped bar is attached to the rear section wedge portion of the upper wedge bar and the rear section wedge portion of the lower wedge bar, and a cavity is formed among the upper wedge bar, the lower wedge bar and the rear arc-shaped bar;
the end auxiliary cutter comprises an end arc-shaped connecting part, and an end wedge-shaped decomposition part is arranged on the surface of the end arc-shaped connecting part close to the end part.
2. The light bird strike resistant aircraft horizontal tail leading edge of claim 1, wherein the cavity is filled with a foam.
3. A lightweight bird strike resistant aircraft horizontal tail leading edge according to claim 1 or 2 wherein a plurality of rib boxes are also provided inboard of the front skin assembly.
4. A lightweight bird strike resistant aircraft horizontal tail leading edge according to claim 3 wherein said rib cage is provided with lightening holes.
5. A lightweight bird strike resistant aircraft horizontal tail leading edge according to claim 1 or claim 2 wherein the outer skin is of laminated construction.
6. A lightweight bird strike resistant aircraft horizontal tail leading edge according to claim 1 or claim 2 wherein the outer surface of the outer skin is covered with a lightning strike resistant surface film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211359553.7A CN115593613B (en) | 2022-11-02 | 2022-11-02 | Light-weight bird strike-resistant airplane horizontal tail front edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211359553.7A CN115593613B (en) | 2022-11-02 | 2022-11-02 | Light-weight bird strike-resistant airplane horizontal tail front edge |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115593613A CN115593613A (en) | 2023-01-13 |
| CN115593613B true CN115593613B (en) | 2023-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211359553.7A Active CN115593613B (en) | 2022-11-02 | 2022-11-02 | Light-weight bird strike-resistant airplane horizontal tail front edge |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6116539A (en) * | 1999-03-19 | 2000-09-12 | Williams International Co. L.L.C. | Aeroelastically stable forward swept wing |
| WO2010023253A1 (en) * | 2008-08-28 | 2010-03-04 | Sa Speir Aviation Limited | A bird collision avoidance system |
| CN102030102A (en) * | 2010-11-18 | 2011-04-27 | 西北工业大学 | Horizontal tail front edge for bird strike-resisting airplane |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE1015867A3 (en) * | 2004-01-22 | 2005-10-04 | Sonaca Sa | Together leading edge of a wing element element wing aircraft and equipped at least such an assembly. |
| EP3216693A1 (en) * | 2016-03-10 | 2017-09-13 | Airbus Operations, S.L. | Aircraft aerodynamic surface with a detachable leading edge |
-
2022
- 2022-11-02 CN CN202211359553.7A patent/CN115593613B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6116539A (en) * | 1999-03-19 | 2000-09-12 | Williams International Co. L.L.C. | Aeroelastically stable forward swept wing |
| WO2010023253A1 (en) * | 2008-08-28 | 2010-03-04 | Sa Speir Aviation Limited | A bird collision avoidance system |
| CN102030102A (en) * | 2010-11-18 | 2011-04-27 | 西北工业大学 | Horizontal tail front edge for bird strike-resisting airplane |
Non-Patent Citations (1)
| Title |
|---|
| C系列飞机先进技术和发展分析;赵长辉;焦亦彬;;飞机设计(06);全文 * |
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| CN115593613A (en) | 2023-01-13 |
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