CN110789709B - Composite horizontal tail with leading edge slat - Google Patents
Composite horizontal tail with leading edge slat Download PDFInfo
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- CN110789709B CN110789709B CN201910971202.3A CN201910971202A CN110789709B CN 110789709 B CN110789709 B CN 110789709B CN 201910971202 A CN201910971202 A CN 201910971202A CN 110789709 B CN110789709 B CN 110789709B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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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 invention belongs to the structural design technology of helicopters, and relates to a composite horizontal tail wing with leading edge slats; the horizontal tail wing box assembly comprises a horizontal tail wing box assembly, a left leading edge slat assembly and a right leading edge slat assembly, wherein the left leading edge slat assembly and the right leading edge slat assembly are respectively connected to the left side and the right side of the front end of the horizontal tail wing box assembly; the left leading-edge slat assembly is formed by riveting a left leading-edge slat and a plurality of brackets; the right leading edge slat assembly is formed by riveting a right leading edge slat and a plurality of brackets; the cross section of the left leading-edge slat is inverted-drop-shaped, and the leading-edge contour of the left leading-edge slat is consistent with that of the co-curing box section; the right leading-edge slat has the same appearance as the left leading-edge slat; the horizontal tail wing box assembly is a main body structure of the horizontal tail wing, and comprises an integral co-curing box, a left rear edge, a right rear edge, a left front end rib, a right front end rib, a left rear end rib and a right rear end rib. The horizontal tail structure has obvious improvement effect on the aspects of improving the stability of pitching moment, resisting bird strike and resisting fatigue.
Description
Technical Field
The invention belongs to the structural design technology of helicopters, and relates to a composite horizontal tail wing with leading edge slats.
Background
At present, single-rotor helicopters are generally provided with a horizontal tail wing with small area and are used for improving the longitudinal stability and the attack angle stability of the helicopters. The installation angle of the horizontal tail of most helicopters is fixed. Because the mounting angle of the horizontal tail wing is fixed, the pitching moment stability of the helicopter in a gust or hovering state is affected. With the development of military and civil helicopters, the requirements of the helicopters on improving the aerodynamic performance and improving the safety of the horizontal tail are higher and higher, such as the stability of pitching moment and the bird strike resistance of the structure required by civil helicopters in airworthiness. In addition, because the horizontal tail is affected by high-frequency small-amplitude fatigue loads formed by rotor downwash airflow, fuselage side wash airflow and the like, the horizontal tail structure also needs to have certain fatigue resistance.
Chinese invention patent publication No. CN 107226197A discloses a rear suspension type horizontal tail of a helicopter. The invention adopts a structural form of a metal material beam-rib-skin glue rivet, and is connected to the rear part of a fuselage through a suspension point arranged at the front end. The main object of the invention is to facilitate disassembly.
Chinese patent No. CN106342053B discloses a horizontal tail connecting device and horizontal tail of helicopter. The invention relates to a fixed horizontal tail of a helicopter. The invention adopts a structural form of beam-rib-skin glue riveting, can realize the technical requirement of adjusting the horizontal tail wing by +/-10 degrees on the ground only through the connecting joint and the left and right connecting angle pieces, and is mainly used for determining the final installation angle of the horizontal tail wing in the scientific research and test flight stage of the helicopter.
The Chinese invention patent with the publication number CN 205239896U discloses an unmanned aerial vehicle horizontal tail, and provides a left and right two-piece horizontal tail structure, wherein the horizontal tail is connected with two insertion pipes. Because the horizontal tail wing of the unmanned aerial vehicle is low in overall layout, in order to avoid being damaged by sand and stones and the like of the unmanned aerial vehicle during taking off and landing to repair or replace the horizontal tail wing, the horizontal tail wing of the unmanned aerial vehicle adopts a left-right two-piece structure, has the same appearance and structure form, can be used interchangeably, reduces the quantity of equipment during maintenance and replacement, and improves the universality and the use efficiency of accessories. However, the horizontal tail wing has low load transmission efficiency, and needs to balance all bending moments borne by the horizontal tail through a tail structure.
The invention described above is deficient in the stability of pitching moment, resistance to bird strike and fatigue resistance of the horizontal rear wing structure.
Disclosure of Invention
The purpose of the invention is: the horizontal tail wing structure of the helicopter has the advantages of strong anti-fatigue capability, light structure weight, high bearing efficiency, simple and convenient assembly and maintenance process, and certain improvement on the stability characteristic of the longitudinal pitching moment of the helicopter and bird attack resistance.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a composite horizontal tail wing with leading-edge slats comprises a horizontal tail wing box assembly 3, a left leading-edge slat assembly 1 and a right leading-edge slat assembly 2 which are respectively connected to the left side and the right side of the front end of the horizontal tail wing box assembly;
the left leading-edge slat assembly 1 is formed by riveting a left leading-edge slat 4 and a plurality of brackets 5; the right leading-edge slat assembly 2 is formed by riveting a right leading-edge slat 6 and a plurality of brackets 5;
the cross section of the left leading-edge slat 4 is inverted-drop-shaped, and the leading-edge contour of the left leading-edge slat is consistent with that of the integral co-curing box section 7; the right leading-edge slat 6 has the same shape as the left leading-edge slat 4;
the bracket 5 extends out of a plurality of mounting lugs which are provided with connecting holes; one side is attached to the shape of the leading-edge slat, and the other side is attached to the leading edge of the integral co-curing box section 7;
the horizontal tail box assembly 3 is a main body structure of a horizontal tail, and the horizontal tail box assembly 3 comprises an integral co-curing box 7, a left rear edge 8, a right rear edge 9, a left front end rib 10, a right front end rib 11, a left rear end rib 12 and a right rear end rib 13.
The integral co-cured box section 7 is co-cured with two chopped fiber blocks 16 and a filler foam 17 from an epoxy carbon fiber composite.
Preferably, the left and right rear edges 8, 9 are each bolted to the integral co-curing box 7.
Preferably, the left front end rib 10, the right front end rib 11, the left rear end rib 12 and the right rear end rib 13 are connected with the integral co-curing box section 7 by glue riveting assembly.
Preferably, the left and right leading- edge slats 4 and 6 are made of composite material or aluminum alloy.
Preferably, the bracket 5 has four mounting tabs, two connected to the slat and two connected to the integral co-cured box section 7.
Preferably, the bracket 5 is made of aluminum alloy.
Preferably, the left leading-edge slat 4 is riveted to four brackets 5; the right leading-edge slat 6 is riveted to four brackets 5.
Preferably, the left leading-edge slat assembly 1 and the right leading-edge slat assembly 2 are respectively connected and fixed with a rivetless nut installed on the horizontal tail wing box assembly 3 through screws.
Preferably, a mounting interface 20 of a navigation light switch is reserved on the integral co-curing box section 7.
The invention has the beneficial effects that:
(1) the horizontal tail structure has the capability of improving the pitching moment stability of the helicopter. According to the invention, the leading edge slat is additionally arranged on the front edge of the horizontal tail wing, so that a gap is formed between the leading edge slat structure and the main structure of the horizontal tail wing, and airflow with higher pressure on the upper wing surface is accelerated through the gap to flow to the lower wing surface, so that the energy of the airflow in the boundary layer of the attachment surface of the lower wing surface is increased, the pressure difference of the upper surface and the lower surface of the horizontal tail wing is reduced, and the stability characteristic of the longitudinal pitching moment of the helicopter is further improved.
(2) The bird impact resistance of the horizontal tail structure is obviously enhanced. According to the invention, the front edge slat is additionally arranged at the front end of the horizontal tail wing, when the front edge part of the horizontal tail wing is impacted by a bird body, the front edge slat can firstly bear the impact of the bird body and further deform or even damage the structure, the impact kinetic energy of the bird body can be effectively absorbed and dissipated in the process, and further a front beam element in a main bearing structure integral co-curing box section in the horizontal tail wing structure is protected from being damaged, so that the horizontal tail wing can continuously exert the functions given by the design of the horizontal tail wing, and the safe flight and landing of a helicopter are ensured.
(3) The anti-fatigue capability of the horizontal tail structure is obviously improved, in addition, the weight of the horizontal tail structure is reduced by 30 percent compared with that of the same type of metal structure, the bearing efficiency is improved, and the number of parts and the number of drill holes required by mechanical assembly are reduced by 80 percent. All parts except the connecting piece in the horizontal tail structure are made of epoxy resin and carbon fiber composite materials. The horizontal tail main structure adopts the whole co-curing box section to reduce the number of parts and fasteners and the number of holes required by mechanical connection, so that the bearing efficiency of the structure is improved, the workload of machining and manufacturing is reduced, the adverse effect that the bearing performance of the structure is reduced due to the more holes in the mechanical connection such as riveting process is avoided, and the probability that damage is introduced by a drilling process is reduced. In addition, the integral co-curing box section can be self-balanced when bearing the bending moment borne by the horizontal tail wing structure, and the bearing efficiency of the structure is improved.
(4) The size of the through hole reserved in the horizontal tail structure during installation is reduced by 20%, and the reliability and the safety of the structure are improved. The leading edge slat and the trailing edge in the horizontal tail wing structure adopt a left-right split detachable structure. When the horizontal tail wing is installed, only an opening with a slightly larger cross section than the whole co-curing box section structure is reserved for the installation. After the integral co-curing box section and the fuselage are installed, the left leading edge slat, the right leading edge slat, the left trailing edge and the right trailing edge structure can be installed in a screwing mode.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is an isometric view of a composite integrated tailplane structure of the present invention having a leading edge slat;
FIG. 2 is an isometric view of a left leading-edge slat assembly according to the present invention;
FIG. 3 is an isometric view of a right front edge slat assembly according to the invention;
FIG. 4 is a left top isometric view of the horizontal tail section assembly of the present invention;
FIG. 5 is a bottom right isometric view of the horizontal tail box assembly of the present invention;
FIG. 6 is an isometric view of an integral co-curing block of the present invention;
FIG. 7 is a cross-sectional view of the attachment to the airframe structure of the present invention in an integral co-curing cartridge;
FIG. 8 is an exploded view of a composite integrated tailplane structure with slats according to the present invention;
FIG. 9 is a sequence chart illustrating the breakdown of a bird striking the horizontal tail structure according to one embodiment;
in the figure: 1-left leading edge slat assembly, 2-right leading edge slat assembly, 3-horizontal tail wing box section assembly, 4-left leading edge slat, 5-bracket, 6-right leading edge slat, 7-integral co-curing box section, 8-left trailing edge, 9-right trailing edge, 10-left front end rib, 11-right front end rib, 12-left rear end rib, 13-right rear end rib, 14-upper bushing, 15-lower bushing, 16-chopped fiber block, 17-filling foam, 18-closed chamber partition rib, 19-bird body and 20-interface.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all 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.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention. The specific embodiments of the present invention are described below:
1. the composite horizontal tail wing structure with leading-edge slats is formed by assembling a left leading-edge slat assembly 1, a right leading-edge slat assembly 2 and a horizontal tail wing box section assembly 3 in a screwing mode, and the details are shown in figure 1. The composite horizontal tail structure with leading edge slats is connected with the helicopter body structure through bolts.
2. The left leading-edge slat assembly 1 is connected by rivets by a left leading-edge slat 4 and four brackets 5, see in detail fig. 2. The left leading-edge slat 4 is of a composite material laminated plate structure, is formed by paving and solidifying three layers of epoxy resin carbon fiber fabrics, and is used for maintaining the overall aerodynamic shape of the leading-edge slat. The supports 5 are aluminum alloy machined structures and are arranged in the span direction of the horizontal tail, and the number of the supports is four in order to improve the rigidity of the leading-edge slat structure and consider possible failure behaviors of the supports 5. The bracket 5 is provided with four lugs and a web plate in total, the lugs are used for connecting and transmitting the structure, and the web plate is used for transmitting force and ensuring that the airflow between the leading edge slat assembly and the horizontal tail wing box assembly 3 passes through the gap.
3. The right-leading-edge slat assembly 2 is connected by rivets by a right-leading-edge slat 6 and four brackets 5, see in detail fig. 3. The right leading-edge slat 6 is of a composite material laminated plate structure, is formed by paving and curing three layers of epoxy resin carbon fiber fabrics, and is used for maintaining the overall aerodynamic appearance of the leading-edge slat.
4. The horizontal tail wing box assembly 3 is a main body structure of the horizontal tail wing, bears main bending moment and torsion of the horizontal tail structure, plays an important role in improving the longitudinal stability and the attack angle stability of the helicopter, and is positioned at the rear parts of the leading edge slat assemblies 1 and 2. The horizontal tail wing box assembly 3 is connected by an integral co-curing box 7, a left front end rib 10, a right front end rib 11, a left rear end rib 12 and a right rear end rib 13 by adopting an adhesive and a rivet, and is connected with the left rear edge 8 and the right rear edge 9 by adopting the matching of a screw and a supporting plate nut, and the screw adopts a countersunk head screw for ensuring the smooth structural surface of the horizontal tail wing box assembly 3 so as to obtain a good pneumatic effect. Two upper bushings 14 and two lower bushings 15 are drilled and glued at the bolted connection of the horizontal rear wing to the fuselage structure for the installation of the connecting bolts and to withstand the compressive stresses caused by the above-mentioned loads when the horizontal rear wing is subjected to bending moments and torques. The horizontal tail wing box assembly is shown in detail in fig. 4 and 5.
5. Further, the integral co-curing box section 7 is of a double closed-chamber composite material structure, and the constituent elements include a skin, a front beam, a rear wall and a reinforcing structure arranged behind a web of the front beam and used for a connection area between the horizontal tail wing and the body structure, which are shown in detail in fig. 6 and 7. The integral co-curing box section 7 is integrally co-cured and formed by epoxy carbon fiber fabric, unidirectional cloth and two chopped fiber blocks 16 and filling foam 17 placed between the two chopped fiber blocks 16. The epoxy carbon fiber fabric is mainly paved on the skin, the front beam and the rear wall area, and the unidirectional fabric is mainly paved on the front beam edge strip area and used for bearing the tensile and compressive stress caused by bending of the horizontal tail wing, so that the structure bearing efficiency is improved. The integral co-curing box section 7 is used for reinforcing the inner surface of the front edge skin part of the bracket 5 for connecting the left and right front edge slats, and the reinforced paving layers are 3 layers and used for diffusing the concentrated force at the connecting point and reducing the stress level of the connecting part of the bracket. The chopped strand blocks 16 are primarily used to secure the upper and lower bushings 14, 15 and to withstand and diffuse the compressive stresses imparted by the bushings to the chopped strand blocks. The filling foam 17 primarily serves to fill and flatten the area between the two chopped fiber blocks 16, while the arrangement of the closed cell partition rib 18 in the helicopter's center of symmetry allows for easy shaping of the closed cell structure of the integral co-cured box section 7 and extraction of the silica gel core mold. In addition, the upper surface of the middle part of the integral co-curing box section 7 is provided with a square opening, so that an installation space is provided for a placing box of a control switch of a course lamp on the side vertical stabilizer on the left side and the right side of the horizontal tail wing.
6. To make the detailed composition of the horizontal rear wing of the invention more apparent and clear, please refer to fig. 8.
The specific embodiment of the horizontal tail structure of the AC332 helicopter with the anti-bird-strike capability is described as follows:
according to the consistent design of the bird strike terms specified by airworthiness, only the frontal impact on the windward part, namely the front edge part of the horizontal tail wing in the forward flying process of the helicopter is generally considered. In order to improve the bird strike resistance of the horizontal tail structure, the energy absorption characteristic and the energy dissipation characteristic of the structure are mainly increased during design, so that the impact energy of a bird body can be fully absorbed or dissipated.
The main measures adopted in the design of the horizontal tail structure of the AC332 helicopter are as follows:
the horizontal tail structure is made of epoxy carbon fiber composite materials, and the number and the proportion of +/-45-degree layers of a leading edge slat and a horizontal tail main wing-shaped leading edge skin are increased, so that structural damping is increased, and impact energy is absorbed and dissipated;
secondly, designing the leading-edge slat into a cavity structure by utilizing the overall layout advantage of the leading-edge slat positioned at the front section of the main wing profile of the horizontal tail, thereby realizing a multi-layer protection energy dissipation structure;
and thirdly, end ribs are added at two ends of the main wing shape of the horizontal tail to improve the strength of the end parts for bearing the impact energy of the bird body 19 after being dissipated by the leading edge slat, thereby ensuring the structural integrity of the main wing shape.
The sequence of impacts when the bird strikes the horizontal tail structure is schematically shown in fig. 9, where the arrows indicate the sequence of frontal impacts and the resulting damage caused by the impacts. The energy absorption and consumption of the damage of the leading edge slat structure, the integral co-curing box section skin and the leading edge end rib ensure that the residual kinetic energy of the bird body 19 is not enough to damage the main bearing front beam structure of the integral co-curing box section, so that the horizontal tail wing structure can continuously exert the functions of the horizontal tail wing structure, and the safe flight and landing of the helicopter are ensured. The effectiveness of the above structure in terms of bird strike resistance has been demonstrated.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. A composite tailplane having a leading-edge slat, characterized by: the composite horizontal tail wing comprises a horizontal tail wing box assembly (3), a left leading edge slat assembly (1) and a right leading edge slat assembly (2) which are respectively connected to the left side and the right side of the front end of the horizontal tail wing box assembly;
the left leading-edge slat assembly (1) is formed by riveting a left leading-edge slat (4) and a plurality of brackets (5); the right leading edge slat assembly (2) is formed by riveting a right leading edge slat (6) and a plurality of brackets (5);
the cross section of the left leading-edge slat (4) is inverted-drop-shaped, and the leading-edge contour outline of the left leading-edge slat is consistent with that of the integral co-curing box section (7); the right leading-edge slat (6) has the same shape as the left leading-edge slat (4);
the bracket (5) extends out of a plurality of mounting lugs, and the mounting lugs are provided with connecting holes; one side is attached to the appearance of the leading-edge slat, and the other side is attached to the leading edge of the integral co-curing box section (7);
the horizontal tail wing box assembly (3) is of a main structure of a horizontal tail wing, and the horizontal tail wing box assembly (3) comprises an integral co-curing box (7), a left rear edge (8), a right rear edge (9), a left front end rib (10), a right front end rib (11), a left rear end rib (12) and a right rear end rib (13).
2. The composite tailplane with a leading-edge slat according to claim 1, characterized in that: the integral co-curing box section (7) is formed by co-curing epoxy carbon fiber composite material, two chopped fiber blocks (16) and a filling foam (17).
3. The composite tailplane with a leading-edge slat according to claim 1, wherein: the left rear edge (8) and the right rear edge (9) are respectively in threaded connection with the integral co-curing box section (7).
4. The composite tailplane with a leading-edge slat according to claim 1, wherein: and the left front end rib (10), the right front end rib (11), the left rear end rib (12), the right rear end rib (13) and the integral co-curing box section (7) are assembled in a glue riveting mode.
5. The composite tailplane with a leading-edge slat according to claim 1, wherein: the left leading edge slat (4) and the right leading edge slat (6) are made of aluminum alloy or composite materials.
6. The composite tailplane with a leading-edge slat according to claim 1, wherein: the bracket (5) has four mounting lugs, two of which are connected to the leading edge slat and two of which are connected to the integral co-curing box section (7).
7. The composite tailplane with a leading-edge slat according to claim 1, wherein: the bracket (5) is made of aluminum alloy.
8. The composite tailplane with a leading-edge slat according to claim 1, wherein: the left leading-edge slat (4) is riveted with the four brackets (5); the right leading-edge slat (6) is riveted with the four brackets (5).
9. The composite tailplane with a leading-edge slat according to claim 1, wherein: and the left leading edge slat assembly (1) and the right leading edge slat assembly (2) are respectively connected and fixed with a rivetless nut arranged on the horizontal tail wing box assembly (3) through screws.
10. A composite tailplane with a leading-edge slat according to any one of claims 1 to 9, characterized in that: and an installation interface (20) of a navigation light switch is reserved on the integral co-curing box section (7).
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| CN201910971202.3A CN110789709B (en) | 2019-10-12 | 2019-10-12 | Composite horizontal tail with leading edge slat |
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| CN201910971202.3A CN110789709B (en) | 2019-10-12 | 2019-10-12 | Composite horizontal tail with leading edge slat |
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| CN110789709B true CN110789709B (en) | 2022-10-11 |
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