CN115593613A - Light bird collision resistant aircraft horizontal tail front edge - Google Patents
Light bird collision resistant aircraft horizontal tail front edge Download PDFInfo
- Publication number
- CN115593613A CN115593613A CN202211359553.7A CN202211359553A CN115593613A CN 115593613 A CN115593613 A CN 115593613A CN 202211359553 A CN202211359553 A CN 202211359553A CN 115593613 A CN115593613 A CN 115593613A
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- 238000000354 decomposition reaction Methods 0.000 claims description 8
- 229920001821 foam rubber Polymers 0.000 claims 1
- 239000002131 composite material Substances 0.000 description 13
- 239000007769 metal material Substances 0.000 description 9
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 229920000049 Carbon (fiber) Polymers 0.000 description 5
- 239000004917 carbon fiber Substances 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 5
- 239000002585 base Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000005187 foaming Methods 0.000 description 4
- 239000003292 glue Substances 0.000 description 4
- 239000013585 weight reducing agent Substances 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 206010042255 Struck by lightning Diseases 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 210000003041 ligament Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a lightweight bird collision resistant aircraft horizontal tail leading edge in the technical field of airplanes, which comprises a front skin assembly, wherein the front skin assembly consists of a honeycomb core and a bird separating device, the honeycomb core and the bird separating device are coated between an inner skin and an outer skin, the bird separating device 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 and the rear section wedge-shaped part of the lower wedge-shaped strip, and a cavity is formed among the upper wedge-shaped strip, the lower wedge-shaped strip and the rear arc-shaped strip.
Description
Technical Field
The invention relates to the technical field of airplanes, in particular to an airplane empennage.
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 metal material of the airplane which is in service in a marine environment for a long time, such as an airplane, has poor acid-base corrosion resistance. Compared with metal materials, the composite material has high specific strength, large specific stiffness and strong corrosion resistance, and has great advantages in aspects of designability, manufacturability, structure weight reduction and the like.
The prior art discloses a tail fin capable of improving bird impact resistance of an airplane, and the publication number is as follows: CN 102390520A, published as: 2012-3-28, which comprises a honeycomb core wrapped between an inner skin and an outer skin and a bird separator, wherein the bird separator is formed by bending an aluminum alloy rectangular plate and is made of a metal material.
In order to realize the weight reduction design of the front edge of the horizontal tail of the existing airplane, on the basis of meeting the requirement of bird impact resistance, the composite material structure is considered to replace the 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 functions are to keep the aerodynamic shape, reduce the aircraft resistance and protect the main bearing structure from impact damage. The front edge of the horizontal tail is a dangerous area for the collision of birds and the airplane flying safety is directly affected. The metal structure of the front edge of the horizontal tail of the prototype is designed into a composite material structure, and the front edge structure of the horizontal tail composite material is designed mainly around bird impact resistance by comprehensively considering design criteria such as structural strength, rigidity, damage tolerance, durability, environmental adaptability and the like by utilizing the advantages of anisotropy and designability of the composite material under the condition of ensuring that the aerodynamic appearance of the airplane is not changed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a light-weight bird collision resistant aircraft horizontal tail front edge, which solves the problem of how to realize weight reduction on the premise of ensuring the protection of a main bearing structure when the front edge is subjected to impact damage, namely, the front edge needs to reduce weight and also needs to ensure that the front edge has enough strength to prevent bird collision.
The purpose of the invention is realized as follows: a light-weight bird collision resistant aircraft horizontal tail leading edge comprises a front skin assembly, wherein the front skin assembly consists of a honeycomb core and a bird dividing device, the honeycomb core is coated between an inner skin and an outer skin, the bird dividing device comprises a root auxiliary cutter, a middle wedge-shaped cutter and an end auxiliary cutter, the middle wedge-shaped cutter is formed by pulling through from the root of the leading edge to the end, and the root auxiliary cutter and the end auxiliary cutter are respectively connected to the root and the end;
the auxiliary root 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-shaped cutter 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 and the rear section wedge-shaped part of the lower wedge-shaped strip, and a cavity is formed among the upper wedge-shaped strip, the lower wedge-shaped strip and the rear arc-shaped strip;
the end auxiliary cutter comprises an end arc-shaped connecting part, and an end wedge-shaped decomposing 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 actual test process, if the metal material is simply changed into the composite material without changing the structure, the impact strength of the composite material is obviously weaker than that of the metal, in addition, the demoulding of the composite material in a triangular structure has higher difficulty, and the R angle exists at the tip of the triangular structure made by the composite material, so that the body decomposition effect is not obvious enough, and the bird collision prevention capability is obviously weakened through tests, and the integral main bearing structure can be influenced; therefore, the applicant adjusts the structure, and adjusts the original triangular structure into a structure which is formed by integrally forming the arc-shaped strips after the symmetrical upper wedge-shaped strips and the symmetrical lower wedge-shaped strips are matched, so that the bird separating effect is good, and the weight can be reduced.
The features of the structure are explained below:
firstly, a front section wedge-shaped part of an upper wedge-shaped strip and a front section wedge-shaped part of a lower wedge-shaped strip are jointed to form a splitting part, the part is sharp and can directly decompose the body of a bird when the bird is collided, and the structure of the part is different from a hollow tip structure in a triangle and is used as a solid triangle structure, so that the anti-collision capacity is stronger when the bird is collided;
secondly, the middle section supporting part is used as a main stress part, and can bear a large amount of impact force earlier in bird collision under the matching of an obtuse angle, so that the overall strength of the bird separating device is ensured, the thickness of the bird separating device cannot be adjusted, and the design of the wedge-shaped structure at the rear end is that when the force is transmitted from the front end to the rear end, a main acceptance area is close to the inner side of the wedge-shaped strip, so that the weight reduction design is considered, and the material can be reduced at the outer side for wedge-shaped surface treatment; in addition, the stress area of the wedge-shaped strip formed by the obtuse angle structure is larger relative to the triangular plane structure;
thirdly, an elastic stress area is formed by the design of the rear arc-shaped strip structure, namely when the impact force of the front end is transmitted to the rear and 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 compared with a metal plane structure, the rear arc-shaped strip structure has better toughness;
fourthly, the two ends of the middle wedge-shaped cutter need to be fixed to play a role in bird separation, the middle wedge-shaped cutter cannot be fixed by the root ribs and the end ribs due to structural design reasons, the middle wedge-shaped cutter can play a role in the middle wedge-shaped cutter by the root ribs and the end auxiliary cutters, meanwhile, the middle wedge-shaped cutter is mainly supported by the honeycomb, the honeycomb cannot penetrate through the whole front edge, and therefore the root cutters and the end cutters continue and strengthen the role in bird separation of the wedge-shaped structure.
Compared with the prior art, the invention has the beneficial effects that:
by the structural design, the weight of the front edge of the horizontal tail of the airplane is reduced on the premise that the main bearing structure can be reliably protected when the airplane is damaged by impact.
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 shock resistance effect of the bird separating device, and the foaming glue is used.
In order to further enhance the overall strength, a plurality of rib boxes are arranged on the inner side of the front skin assembly.
In order to further reduce the weight, the rib box is provided with lightening holes.
As a further limitation of the invention, the outer skin is of a laminate construction.
As a further limitation of the invention, the outer surface of the outer skin is covered with a lightning strike 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 used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic perspective view of the first embodiment of the present invention.
Fig. 2 is a schematic perspective view of the second embodiment of the present invention.
Figure 3 is a side view of a front skin assembly according to the present invention.
FIG. 4 is a schematic end view of a wedge-shaped cutter according to the present invention.
FIG. 5 is a schematic view of the installation of the base auxiliary cutter according to the present invention.
FIG. 6 is a perspective view of the base auxiliary cutter according to the present invention.
FIG. 7 is a schematic view of the installation of an end assist cutter according to the present invention.
Fig. 8 is a perspective view of the end auxiliary cutter according to the present invention.
Wherein, 1 interior skin, 2 outer skins, 3 honeycomb cores, 4 middle part wedge cutterbars, 4a goes up the wedge strip, 4b wedge strip down, 4c back arc strip, 4d anterior segment wedge portion, 4e interruption supporting part, 4f back end wedge portion, 5 supplementary cutterbars in root, 5a arc connecting portion, 5b wedge decomposition portion, 5c connecting end portion, 6 tip supplementary cutterbars, 6a end arc connecting portion, 6b end wedge decomposition portion, 7 rib boxes, 8 lightning protection surface membranes, 9 foamed rubber.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The front edge of the flat tail of the lightweight bird-strike-resistant aircraft shown in the figures 1-8 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, which are coated between an inner skin 1 and an outer skin 2, into a whole, 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 by a nail, 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, lightening holes are formed in the rib box 7, the outer skin 2 adopts a laminated plate structure, the outer surface of the outer skin 2 is covered with a lightning-strike-proof surface film 8, and the thicknesses of the inner skin 1 and the outer skin 2 are 1mm;
the bird divider comprises a base sub-cutter 5, a middle wedge cutter 4 and an end sub-cutter 6;
the auxiliary root cutter 5 is made of metal materials and arranged at the root of the front skin assembly, the auxiliary root cutter 5 comprises an arc-shaped connecting part 5a, the arc-shaped connecting part 5a is attached to the inner side of the inner skin 1, a wedge-shaped root decomposing part 5b is arranged at a position, close to the root, on the surface of the arc-shaped connecting part 5a, a connecting end part 5c is further arranged at the position, close to the root, of the side surface of the arc-shaped connecting part 5a, and the arc-shaped root connecting part 5a is connected with the inner skin 1 and the bird separating device through a nail;
middle part wedge cutterbar 4 includes wedge strip 4a, lower wedge strip 4b and back arc strip 4c, it is symmetrical structure to go up wedge strip 4a and lower wedge strip 4b, it includes anterior segment wedge portion 4d to go up wedge strip 4a, break supporting part 4e and back end wedge portion 4f, form the obtuse angle between anterior segment wedge portion 4d and the break supporting part 4e, this embodiment is about 150, anterior segment wedge portion 4d is preceding half section isobaric thickness and back half section wedge portion, the anterior segment wedge portion 4d of going up wedge strip 4a bonds together with anterior segment wedge portion 4d inboard of lower wedge strip 4b, form the real triangle-shaped structure of front end area spine, arc strip and last wedge strip 4a back end wedge portion 4f, the back end wedge portion 4f of lower wedge strip 4b bonds together, form the toughness portion, the arc strip at this moment can understand as the ligament, go up wedge strip 4a, lower wedge strip 4b, form the cavity between the back arc strip 4c, the intussuseption is filled with foaming glue 9 in the cavity, this embodiment is 0.6mm, the transition back end arc strip is 0.6mm, the back end arc strip thickness is 0.6mm.
The tip auxiliary cutter 6 adopts metal material to make, sets up the tip at preceding skin subassembly, and tip auxiliary cutter 6 includes end arc connecting portion 6a, and the laminating of end arc connecting portion 6a is including 1 inboard settings of skin, and the position that the tip is close to on the surface of end arc connecting portion 6a is equipped with end wedge decomposition portion 6b, and end arc connecting portion 6a adopts the nail of taking out to be connected with interior skin 1, branch bird ware.
The invention adopts a honeycomb sandwich structure, a middle wedge-shaped cutter 4 is formed by pulling through from the root of the front edge to the end, and the root auxiliary cutter 5 and the end auxiliary cutter 6 are respectively connected at the root and the end, and the front edge of the horizontal tail adopts a design scheme that three structures absorb the energy of a bird body layer by layer: the first layer is a front edge outer skin 2 which adopts a laminated plate structure and only absorbs partial energy; the second layer is 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, the honeycomb core 3 has light weight, and the middle and rear parts of the rear bird distributing device have good buffering and energy absorbing performance.
Compared with the existing metal structure, the invention has the following advantages:
1) The carbon fiber composite material structure can reduce the weight, and the carbon fiber composite material has high specific strength and specific rigidity, and is superior to a metal material in the aspects of 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 the capability of being in service in a marine environment for a long time, so that the carbon fiber has enough guarantee on the aspect of corrosion resistance compared with a metal material;
3) The fatigue resistance is strong; the carbon fiber composite material has excellent fatigue resistance relative to a metal material;
4) The bird impact resistance is good; the wedge-shaped structure can well disperse energy and reduce the loss of the structure; the honeycomb sandwich structure has light weight and can better buffer and absorb energy.
The test condition requires that after a bird with the weight of 3.6 kilograms (8 pounds) at the speed of about 520km/h collides, the front beam is not allowed to penetrate, and the invention meets the above requirements through tests.
The above description of the embodiments is only intended to facilitate the understanding of the method of the invention and its core idea. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (6)
1. A light-weight bird collision resistant aircraft horizontal tail leading edge comprises a front skin assembly, wherein the front skin assembly consists of a honeycomb core and a bird dividing device, the honeycomb core and the bird dividing device are coated between an inner skin and an outer skin, the bird dividing device is characterized by comprising a root auxiliary cutter, a middle wedge-shaped cutter and an end auxiliary cutter, the middle wedge-shaped cutter is formed by pulling through from the root of the leading edge to the end, and the root auxiliary cutter and the end auxiliary cutter are respectively connected to the root and the end;
the auxiliary root 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, and penetrates through the root wedge-shaped decomposition part, and a connecting end part is arranged on the side surface, close to the root, of the root arc-shaped connecting part;
the middle wedge-shaped cutter 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 and the rear section wedge-shaped part of the lower wedge-shaped strip, and a cavity is formed among the upper wedge-shaped strip, the lower wedge-shaped strip and the rear arc-shaped strip;
the end auxiliary cutter comprises an end arc-shaped connecting part, and an end wedge-shaped decomposing part is arranged on the surface of the end arc-shaped connecting part close to the end part.
2. The front edge of the horizontal tail of the lightweight bird strike resistant aircraft according to claim 1, wherein the cavity is filled with foam rubber.
3. The front edge of the horizontal tail of the lightweight bird strike resistant aircraft according to claim 1 or 2, wherein a plurality of rib boxes are further arranged on the inner side of the front skin assembly.
4. The front edge of the horizontal tail of the light-weight bird strike resistant aircraft according to claim 3, wherein the rib box is provided with lightening holes.
5. The front edge of the horizontal tail of the lightweight bird strike resistant aircraft according to claim 1 or 2, wherein the outer skin is of a laminated plate structure.
6. The front edge of the horizontal tail of the lightweight bird strike resistant aircraft according to claim 1 or 2, wherein the outer surface of the outer skin is covered with a lightning strike protection 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 true CN115593613A (en) | 2023-01-13 |
| CN115593613B 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 (5)
| 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 |
| US20080237401A1 (en) * | 2004-01-22 | 2008-10-02 | Sonaca S.A. | Mobile Leading Edge Flap for a Main Wing of the Aerofoils of an Aircraft and Main Wing Provided with Such a Flap |
| 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 |
| US20170259902A1 (en) * | 2016-03-10 | 2017-09-14 | 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 (5)
| 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 |
| US20080237401A1 (en) * | 2004-01-22 | 2008-10-02 | Sonaca S.A. | Mobile Leading Edge Flap for a Main Wing of the Aerofoils of an Aircraft and Main Wing Provided with Such a Flap |
| 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 |
| US20170259902A1 (en) * | 2016-03-10 | 2017-09-14 | Airbus Operations, S.L. | Aircraft Aerodynamic Surface With A Detachable Leading Edge |
Non-Patent Citations (4)
| Title |
|---|
| 张柱国;郝一鸣;: "运输类飞机鸟撞及符合性验证综述", 航空科学技术, no. 06 * |
| 王迪;张正礼;: "浅谈民用飞机尾翼前缘结构设计", 科技视界, no. 12 * |
| 赵长辉;焦亦彬;: "C系列飞机先进技术和发展分析", 飞机设计, no. 06 * |
| 邱韬: "运输机鸟撞损伤的适航要求和试验", 国际航空, no. 10 * |
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| CN115593613B (en) | 2023-08-15 |
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