阅读说明：本技术 一种全复合材料的尾翼结构及其成型方法 (Full-composite empennage structure and forming method thereof ) 是由 熊雅晴 党万腾 刘明辉 李宇飞 杨文� 方雄 刘忠 周子昀 于 2021-07-26 设计创作，主要内容包括：本发明涉及飞机结构设计技术领域,特别是涉及一种全复合材料的尾翼结构及其成型方法,尾翼结构包括尾翼蒙皮和多墙式的尾翼主体,所述尾翼蒙皮采用变厚度设计,厚度由尾翼根部到尾翼尖部递减,从尾翼前缘到后缘递减；所述多墙式的尾翼主体包括主承力部件,所述主承力部件为纵向传力件,与尾翼蒙皮刚度匹配,主承力部件的厚度从尾翼根部到尾翼尖部递减。通过本结构及其成型方法,能有效解决减重空间受限和内外部紧固件数量多的问题,并且表面质量好、重量轻和成本低。(The invention relates to the technical field of airplane structure design, in particular to a full-composite empennage structure and a forming method thereof, wherein the empennage structure comprises an empennage skin and a multi-wall empennage main body, the empennage skin adopts a variable thickness design, the thickness is gradually reduced from the root part of an empennage to the tip part of the empennage, and the thickness is gradually reduced from the front edge to the rear edge of the empennage; the multi-wall type empennage main body comprises a main force bearing part, the main force bearing part is a longitudinal force bearing part and is matched with the empennage skin in rigidity, and the thickness of the main force bearing part is gradually reduced from the empennage root to the empennage tip. By the structure and the forming method thereof, the problems of limited weight reduction space and large quantity of internal and external fasteners can be effectively solved, and the structure has good surface quality, light weight and low cost.)

1. The utility model provides an all combined material's fin structure which characterized in that: the multi-wall type empennage skin comprises an empennage skin (1) and a multi-wall type empennage main body, wherein the empennage skin (1) adopts a variable thickness design, the thickness is gradually reduced from the root part of the empennage to the tip part of the empennage, and the thickness is gradually reduced from the front edge to the rear edge of the empennage; the multi-wall type empennage main body comprises a main force bearing part, the main force bearing part is a longitudinal force bearing part and is in rigidity matching with an empennage skin (1), and the thickness of the main force bearing part is gradually reduced from the root part of the empennage to the tip part of the empennage.

2. A full composite tail structure according to claim 1, characterised in that: the thickness of the empennage skin (1) is gradually reduced by 10-15% from the root part of the empennage to the tip part of the empennage, and is gradually reduced by 10-20% from the front edge to the rear edge.

3. A full composite tail structure according to claim 2, characterised in that: the thickness of the main force bearing part is gradually reduced from the tail root to the tail tip by 10-15%.

4. A full composite tail structure according to claim 1, characterised in that: the main force bearing part comprises a tail wing wall and a tail wing beam, the tail wing skin (1), the tail wing wall and the tail wing beam are integrally formed by adopting composite materials, and the tail wing skin (1), the tail wing wall and the tail wing beam are bonded and cured by heated resin.

5. A full composite tail structure according to claim 4, characterised in that: the sections of the tail wing beam and the tail wing wall adopt [ ] and [ ] type sections, are mutually combined into [ ]' types, and are combined with the tail wing skin (1) into a box-shaped part.

6. A full composite tail structure according to claim 5, characterised in that: the tail wing beam comprises a tail wing front beam (3) and a tail wing rear beam (6), and the tail wing wall comprises a tail wing wall a (2), a tail wing wall b (4) and a tail wing wall c (5); the tail wing wall comprises a tail wing wall a (2), a tail wing front beam (3), a tail wing wall b (4), a tail wing wall c (5) and a tail wing rear beam (6) from front to back in sequence.

7. A full composite tail structure according to claim 1 or 6, characterised in that: the tail body further comprises a tail end rib (7), a tail root rib a (8), a tail root rib b (9), a tail root rib c (11), a tail root rib d (12) and a tail root rib e (13) for sealing the tail, and a tail front joint (10) and a tail rear joint (14) for transferring tail loads.

8. A full composite tail structure according to claim 7, wherein: the empennage main body further comprises a wing tip (17), the wing tip (17) is connected with the empennage end rib (7) in a sleeved mode, and the wing tip (17) can be detached.

9. A full composite tail structure according to claim 1, characterised in that: the empennage skin (1) is a whole skin, and butt joints do not exist between the upper skin and the lower skin.

10. A full composite tail structure according to claim 9, characterised in that: the upper surface and the lower surface of the empennage are designed to be film-facing surfaces.

11. A molding method of a tail wing structure made of full composite materials is characterized in that: the method comprises the following steps:

the fiber of the upper skin and the lower skin of the empennage is continuous, and the carbon fiber cloth of the lower skin of the empennage is laid in the die in the direction;

II, independently laying carbon fiber cloth of a tail wing wall a (2), a tail wing front beam (3), a tail wing wall b (4), a tail wing wall c (5) and a tail wing rear beam (6) on a special die;

thirdly, laying carbon fiber cloth of the upper skin of the empennage according to the design direction;

injecting resin into the empennage mold combination, heating the mold after the resin soaks the carbon fiber cloth, and curing the resin after heating to generate bonding force to integrally cure the empennage skin (1), the empennage wall a (2), the empennage front beam (3), the empennage wall b (4), the empennage wall c (5) and the empennage rear beam (6) into one part to form an empennage main body part;

v, a tail end rib (7), a tail root rib a (8), a tail root rib b (9), a tail root rib c (11), a tail root rib d (12), a tail root rib e (13), a tail front connector (10), a tail rear connector (14) and a wing tip (17) are respectively formed independently, and are installed on a tail main body in a mechanical connection or bonding mode after being formed independently;

and vi, positioning through a tool, mechanically connecting the front tail joint (10) and the rear tail joint (14) with the main body part of the tail wing, and finally installing a wing tip (17) to finish assembly.

Technical Field

The invention relates to the technical field of airplane structure design, in particular to an empennage structure made of full composite materials and a forming method of the empennage structure.

Background

Along with the rapid development of the unmanned aerial vehicle design technology, modern aviation has raised higher requirements for the unmanned aerial vehicle technology, and high strength, light weight and high aerodynamic performance also become one of the difficult problems faced by modern unmanned aerial vehicle design. Along with unmanned aerial vehicle because the user demand is continuous to be improved, low-cost also becomes the trend of unmanned aerial vehicle design, and high performance and low-cost design demand have brought more challenges for unmanned aerial vehicle design. The tail fin serves as one of the main components of the aircraft, serving to stabilize and operate the aircraft. Besides the requirement of strength and rigidity, the design requirements of weight, surface quality and the like also need to be met. The tail wing generally comprises a tail wing rib, a tail wing beam, a tail wing upper skin, a tail wing lower skin, a tail wing joint and the like. The tail wing has large bearing load and complex structural form and connection relationship, so the weight reduction space of the tail wing is very limited, and meanwhile, the connection and involution relationship of the tail wing is complex, the number of fasteners inside and outside the tail wing is large, the surface is in butt joint, the flight resistance is increased, and the flight performance of the airplane is influenced. In addition, the empennage has more parts and complex assembly, which causes higher production cost. In the using process, the empennage wingtip is easy to be damaged, and the whole replacement cost is high.

Disclosure of Invention

In order to solve the technical problems, the invention provides the empennage structure made of the full composite material and the forming method thereof, which can effectively solve the problems of limited weight reduction space and large quantity of internal and external fasteners, have good surface quality, light weight and low cost, and can effectively improve the production efficiency.

The invention is realized by adopting the following technical scheme:

the utility model provides an all combined material's fin structure which characterized in that: the multi-wall type empennage skin comprises an empennage skin and a multi-wall type empennage main body, wherein the empennage skin adopts a variable thickness design, the thickness is gradually reduced from the root part of the empennage to the tip part of the empennage, and the thickness is gradually reduced from the front edge to the rear edge of the empennage; the multi-wall type empennage main body comprises a main force bearing part, the main force bearing part is a longitudinal force bearing part and is matched with the empennage skin in rigidity, and the thickness of the main force bearing part is gradually reduced from the empennage root to the empennage tip.

The thickness of the empennage skin is gradually reduced from the root of the empennage to the tip of the empennage by 10-15%, and is gradually reduced from the front edge to the rear edge by 10-20%.

The thickness of the main force bearing part is gradually reduced from the tail root to the tail tip by 10-15%.

The main force bearing part comprises a tail wing wall and a tail wing beam, the tail wing skin, the tail wing wall and the tail wing beam are integrally formed by adopting composite materials, and the tail wing skin, the tail wing wall and the tail wing beam are bonded and cured by heated resin.

The sections of the tail wing beam and the tail wing wall adopt [ ] and [ ] type sections, are mutually combined into [ ]' types, and are combined with the tail wing skin into a box-shaped part.

The tail wing beam comprises a tail wing front beam and a tail wing rear beam, and the tail wing wall comprises a tail wing wall a, a tail wing wall b and a tail wing wall c; the tail wing wall comprises a tail wing wall a, a tail wing front beam, a tail wing wall b, a tail wing wall c and a tail wing rear beam in sequence from front to back.

The tail body further comprises tail end ribs, a tail root rib a, a tail root rib b, a tail root rib c, a tail root rib d and a tail root rib e for sealing the tail, and a tail front joint and a tail rear joint for transferring tail load.

The empennage main body further comprises a wing tip, the wing tip is connected with the empennage end rib in a sleeved mode, and the wing tip can be detached.

The empennage skin is a whole skin, and butt joints do not exist between the upper skin and the lower skin.

The upper surface and the lower surface of the empennage are designed to be film-facing surfaces.

A molding method of a tail wing structure made of full composite materials is characterized in that: the method comprises the following steps:

the fiber of the upper skin and the lower skin of the empennage is continuous, and the carbon fiber cloth of the lower skin of the empennage is laid in the die in the direction;

II, independently laying carbon fiber cloth of a tail wing wall a, a tail wing front beam, a tail wing wall b, a tail wing wall c and a tail wing rear beam on the special die;

thirdly, laying carbon fiber cloth of the upper skin of the empennage according to the design direction;

injecting resin into the empennage mold combination, heating the mold after the resin soaks the carbon fiber cloth, and curing the resin after heating to generate bonding force to integrally cure the empennage skin, the empennage front beam, the empennage wall b, the empennage wall c and the empennage rear beam into one part to form an empennage main body part;

v, tail end ribs, tail root ribs a, b, c, d, e, front joints, rear joints and wingtips are respectively formed independently and are installed on a tail body in a mechanical connection or bonding mode after being formed independently;

vi., positioning the front and rear joints of the empennage, mechanically connecting the rear joint with the main body of the empennage, and installing the wingtips to complete the assembly.

Compared with the prior art, the invention has the beneficial effects that:

1. the tail wing structure provided by the invention has the advantages of light overall weight, high structural strength, high rigidity, convenience in demoulding, simple and reliable structure, high dimensional precision and good surface quality. The invention can reduce the structure weight, improve the production efficiency and reduce the cost while ensuring the requirements of the empennage structure such as strength, rigidity and the like.

The integrally formed multi-wall type composite material empennage has the advantages that the skin and the main bearing part are designed in variable-thickness equal rigidity, the structural efficiency is improved, the empennage is high in strength and rigidity and small in overall deformation, the weight of the empennage is reduced by more than one third, the voyage and the endurance are increased, and the energy consumption is reduced.

2. In the invention, the integrally formed multi-wall type composite material empennage structure is adopted, so that the production efficiency is greatly improved, and the assembly workload of the empennage is greatly reduced because secondary assembly is not needed and about 80 percent of fasteners are reduced.

3. The main bearing part comprises a tail wing wall and a tail wing beam, the sections of the tail wing beam and the tail wing wall adopt [ ] and [ ] 'sections which are mutually combined into [ ]' shapes, and the sections and the tail wing skin are combined into a box-shaped part, so that the tail wing wall is mainly used as a longitudinal force transmission part, the tail wing beam is used as a longitudinal force transmission part and is also a main bearing part of a tail wing, the load of the tail wing is transmitted to a machine body, the weight is reduced, the load can be effectively transmitted, and the deformation is resisted.

4. The tail wing wall a, the tail wing front beam, the tail wing wall b, the tail wing wall c and the tail wing rear beam form a main force bearing part of the tail wing, the tail wing is in a multi-wall type in layout mode, staggered tail wing ribs are not arranged inside the tail wing, the tail wing is integrally formed and cured at one time, and demolding is convenient.

5. The empennage skin and the main bearing part are manufactured by adopting a composite material integral molding technology, the skin, the empennage wall and the empennage beam do not need to be mechanically connected, and fasteners do not exist on the surface.

6. The empennage skin adopts the whole skin, no butt joint exists between the upper skin and the lower skin, the conventional mode of mechanically connecting the upper skin and the lower skin is replaced, and the overall aerodynamic performance of the empennage is good.

7. The upper surface and the lower surface of the empennage are designed to be film-pasted surfaces, the surface quality of the molded empennage is good, the appearance precision is high, the overall performance is good, the symmetry degree of the airplane is guaranteed, and the control plane trim loss caused by asymmetry is reduced.

8. By the forming method, the empennage is integrally formed, the upper skin and the lower skin of the empennage skin are combined into one integral skin, and the upper surface and the lower surface are seamless; the empennage skin, the empennage beam and the empennage wall are integrally formed and cured at one time, independent forming and assembling are not needed, the surface of the empennage main body part is seamless, fasteners are not needed, the aerodynamic resistance is reduced, and the aerodynamic performance is improved. Because the empennage is integrally formed and cured at one time, the empennage is not required to be assembled after separately forming parts, the production period is shortened by nearly two thirds, the production efficiency is improved, and the production cost is greatly saved

The upper surface and the lower surface of the tail wing skin are both designed to be film-pasted surfaces by adopting a composite material integral forming technology, and the tail wing skin, the tail wing beam and the tail wing wall are integrally cured and formed at one time, so that secondary assembly is not needed, the appearance precision of the tail wing is high after forming, the appearance precision error is reduced by 50%, the surface quality is good, the symmetry degree of an airplane is ensured, and the control plane trim loss caused by asymmetry is reduced.

9. The wing tip adopts the form of can dismantling, and the wing tip is connected after the wing tip registrates with fin end rib, and the wing tip is removable, realizes nimble dismantlement.

Drawings

The invention will be described in further detail with reference to the following description taken in conjunction with the accompanying drawings and detailed description, in which:

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic illustration of a lay-up of a tail section according to the invention;

FIG. 3 is a schematic view of a variable thickness tail skin design of the present invention;

FIG. 4 is a schematic view of the design of the main bearing part for varying thickness in the present invention;

FIG. 5 is a schematic view of the installation of the tail joint of the present invention;

the labels in the figure are:

1. tail skin, 2, tail walls a, 3, front beams, 4, tail walls b, 5, tail walls c, 6, rear beams, 7, tail end ribs, 8, tail root ribs a, 9, tail root ribs b, 10, front connectors, 11, tail root ribs c, 12, tail root ribs d, 13, tail root ribs e, 14, rear connectors, 15, rear connector connecting holes, 16, front connector connecting holes, 17 and wing tips.

Detailed Description

Example 1

The invention comprises, as a basic embodiment thereof, a full-composite tail structure comprising a tail skin 1 and a multi-walled tail body. The empennage skin 1 is designed to be variable in thickness, the thickness of the empennage skin decreases progressively from the root of the empennage to the tip of the empennage, and the thickness of the empennage skin decreases progressively from the front edge to the rear edge of the empennage. The multi-wall type empennage main body comprises a main force bearing part, the main force bearing part is a longitudinal force bearing part and is in rigidity matching with the empennage skin 1, and the thickness of the main force bearing part is gradually reduced from the empennage root to the empennage tip.

Example 2

The invention comprises, as a preferred embodiment, a full composite tail structure comprising a tail skin 1 and a multi-walled tail body. The empennage skin 1 is a whole skin, and butt joints do not exist between the upper skin and the lower skin. The empennage skin 1 adopts a variable thickness design, the thickness of the empennage skin decreases progressively from the root part of the empennage to the tip part of the empennage, and the thickness of the empennage skin decreases progressively from the front edge to the rear edge of the empennage; the multi-wall type empennage main body comprises a main force bearing part, the main force bearing part is a longitudinal force bearing part and is in rigidity matching with the empennage skin 1, and the thickness of the main force bearing part is gradually reduced from the empennage root to the empennage tip.

The main bearing part comprises a tail wing wall and a tail wing beam. The tail beam comprises a tail front beam 3 and a tail rear beam 6, and the tail walls comprise a tail wall a2, a tail wall b4 and a tail wall c 5; from front to back, the tail wing wall a2, the tail wing front beam 3, the tail wing wall b4, the tail wing wall c5 and the tail wing rear beam 6 are sequentially included. The empennage skin 1, the empennage wall and the empennage beam are used as main bearing parts of the empennage and integrally formed by adopting composite materials, and the empennage skin 1, the empennage beam and the empennage wall are not required to be connected through fasteners.

The tail body further includes a tail end rib 7 for closing the tail, a tail root rib a8, a tail root rib b9, a tail root rib c11, a tail root rib d12 and a tail root rib e13, and a front tail joint 10 and a rear tail joint 14 for transferring tail loads.

The empennage main body also comprises a wing tip 17, and the wing tip 17 is sleeved with the empennage end rib 7 and then connected with the empennage end rib, so that the empennage main body can be flexibly disassembled.

Example 3

As another preferred embodiment of the present invention, referring to fig. 1 of the specification, the present invention includes a full composite tail structure, which includes a tail skin 1, a tail wall a2, a tail front beam 3, a tail wall b4, a tail wall c5, a tail rear beam 6, a tail end rib 7, a tail root rib a8, a tail root rib b9, a tail root rib c11, a tail root rib d12, a tail root rib e13, a tail front joint 10, a tail rear joint 14 and a wing tip 17, and is a full composite structure as a whole, so that the overall weight is light.

The tail wing skin 1, the tail wing wall a2, the tail wing front beam 3, the tail wing wall b4, the tail wing wall c5 and the tail wing rear beam 6 form a main force-bearing part of the tail wing, the layout form of the tail wing adopts a multi-wall type, the interior of the tail wing does not have staggered tail wing ribs, the integral forming one-step curing is adopted, and the demoulding is convenient. Wherein, tail wing wall and tail wing roof beam are vertical biography power piece, and the difference lies in: the main function of the tail wing wall is as a longitudinal force transfer piece, the tail wing beam is not only as a longitudinal force transfer piece, but also as a main force transfer part of the tail wing, and the tail wing load is transferred to the fuselage through the joint on the tail wing beam. The empennage skin 1, the empennage wall and the empennage beam are manufactured by adopting a composite material integral molding technology, the skin, the empennage wall and the empennage beam are bonded and cured by heated resin, mechanical connection is not needed, and fasteners are not needed on the surface of the empennage. Referring to the attached figure 2 of the specification, the tail wing beam and the tail wing wall are designed to have variable thicknesses and equal rigidity, the sections of the tail wing beam and the tail wing wall are mutually combined into [ ] type with [ ] type sections, and the tail wing beam and the tail wing wall are combined with the tail wing skin 1 into a box-shaped part, so that the weight is reduced, and the load can be effectively transferred and the deformation is resisted.

The empennage skin 1 adopts a whole skin, the upper skin and the lower skin are not in butt joint, the conventional mode that the upper skin and the lower skin are mechanically connected is replaced, and the overall aerodynamic performance of the empennage is good. The upper surface and the lower surface of the empennage are designed to be film-pasted surfaces, the surface quality of the molded empennage is good, the appearance precision is high, the overall performance is good, the symmetry degree of the airplane is ensured, and the control plane trim loss caused by asymmetry is reduced.

Wherein, the wingtip 17 adopts the detachable form, and the wingtip 17 is connected after the body portion registrates to make the wingtip 17 removable.

The tail front joint 10 and the tail rear joint 14 are used for positioning the tail through a tool and mechanically connected with the tail through bolts.

Example 4

The invention comprises, as a preferred embodiment of the invention, a method for the shaping of a full-composite tail structure, wherein the full-composite tail structure is as described in example 3. The method specifically comprises the following steps:

and i, continuously paving the fibers of the upper skin and the lower skin of the empennage in the mould according to the direction.

And ii, independently laying carbon fiber cloth of the tail wall a2, the tail front beam 3, the tail wall b4, the tail wall c5 and the tail back beam 6 on a special die. Referring to the attached figure 4 of the specification, the tail wing beam, the tail wing wall and the tail wing skin 1 are designed to have equal rigidity, the thickness is gradually reduced from the root to the tip according to 10% -15%, the specific percentage can be adjusted according to the finite element simulation calculation result, and the weight of the tail wing is reduced while the strength and the rigidity of the tail wing are ensured.

And iii, laying the carbon fiber cloth of the upper skin of the empennage according to the design direction. Referring to the attached figure 3 of the specification, the thickness of the empennage skin 1 is gradually reduced by 10-15% from the root part of the empennage to the tip part of the empennage, and is gradually reduced by 10-20% from the front edge to the rear edge, and the specific percentage can be adjusted according to the finite element simulation calculation result.

Injecting resin into the empennage mold combination, heating the mold after the resin soaks the carbon fiber cloth, and curing the resin after heating to generate bonding force to integrally cure the empennage skin 1, the empennage wall a2, the empennage front beam 3, the empennage wall b4, the empennage wall c5 and the empennage rear beam 6 into one part to form an empennage main body part;

v. the tail end rib 7, the tail root rib a8, the tail root rib b9, the tail root rib c11, the tail root rib d12, the tail root rib e13, the front tail joint 10, the rear tail joint 14 and the wing tip 17 are respectively and independently molded and then installed on the tail body in a mechanical connection or bonding mode;

and vi, referring to the attached drawing 5 of the specification, positioning the tail through a tool, arranging a rear joint connecting hole 15 on the tail rear joint 14, arranging a front joint connecting hole 16 on the tail front joint 10, mechanically connecting the tail front joint 10 and the tail rear joint 14 with the tail body part through the front joint connecting hole 16 and the rear joint connecting hole 15, and finally installing a wing tip 17 to finish assembly.

In summary, after reading the present disclosure, those skilled in the art should make various other modifications without creative efforts according to the technical solutions and concepts of the present disclosure, which are within the protection scope of the present disclosure.