阅读说明：本技术 一种直升机水平尾翼连接支撑结构 (Helicopter horizontal tail wing connection support structure ) 是由 张欢 高瑞睿 鹿文宝 李媛 荆天冬 刘永胜 林大威 郝刚勇 于 2020-10-30 设计创作，主要内容包括：本发明属于直升机水平尾翼连接技术领域,公开了一种直升机水平尾翼连接支撑结构,包括：水平尾翼接头和撑杆组件；水平尾翼接头分别连接水平尾翼和垂尾；撑杆组件分为左撑杆组件和右撑杆组件；左撑杆组件两端分别连接水平尾翼左侧气动压心处与垂尾底部；右撑杆组件两端分别连接水平尾翼右侧气动压心处与垂尾底部；撑杆组件长度可调节。可以将水平尾翼的部分载荷通过支撑结构传递至垂直尾翼结构,从而降低水平尾翼根部以及水平尾翼接头的应力水平,提高其使用寿命；可调节长度的支撑杆用以抵消水平尾翼和垂直尾翼零件装配制造过程中积累的公差,确保支撑杆的顺利安装。(The invention belongs to the technical field of helicopter horizontal tail wing connection, and discloses a helicopter horizontal tail wing connection supporting structure, which comprises: horizontal tail joint and strut assembly; the horizontal tail joint is respectively connected with a horizontal tail and a vertical tail; the stay bar component is divided into a left stay bar component and a right stay bar component; two ends of the left stay bar component are respectively connected with the left pneumatic pressure center of the horizontal tail and the bottom of the vertical tail; two ends of the right stay bar component are respectively connected with the pneumatic pressure center of the right side of the horizontal tail and the bottom of the vertical tail; the length of the stay bar component is adjustable. Partial load of the horizontal tail can be transferred to the vertical tail structure through the supporting structure, so that the stress level of the root of the horizontal tail and the horizontal tail joint is reduced, and the service life of the horizontal tail is prolonged; the supporting rod with adjustable length is used for offsetting tolerance accumulated in the assembly and manufacturing process of parts of the horizontal tail wing and the vertical tail wing, and ensures the smooth installation of the supporting rod.)

1. The utility model provides a helicopter horizontal tail wing connection support structure which characterized in that: the structure includes: horizontal tail joint and strut assembly;

the horizontal tail joint is respectively connected with a horizontal tail and a vertical tail;

the stay bar component is divided into a left stay bar component and a right stay bar component;

two ends of the left stay bar component are respectively connected with the left pneumatic pressure center of the horizontal tail and the bottom of the vertical tail;

two ends of the right stay bar component are respectively connected with the pneumatic pressure center of the right side of the horizontal tail and the bottom of the vertical tail;

the strut assembly is adjustable in length.

2. A helicopter tailplane attachment support structure as defined in claim 1, wherein: the brace bar assembly comprises: a circular tube, an upper joint, a lower joint and a rod joint;

two ends of the circular tube are respectively and fixedly connected with the upper joint and the lower joint;

the circular pipe is connected with the horizontal tail wing through an upper connector;

one end of the rod joint is a single lug, and the other end of the rod joint is a cylinder provided with external threads;

the lower joint is provided with a threaded hole matched with the external thread of the rod joint;

one end of the rod joint is connected with the vertical tail through the single lug, the other end of the rod joint is in threaded connection with the lower joint, and the rod joint rotates relative to the lower joint to adjust the length of the stay bar assembly.

3. A helicopter tailplane attachment support structure as defined in claim 2, wherein: the brace bar assembly further comprises: a nut; the nut is sleeved on the threaded section of the rod joint and tightly attached to the lower joint; the nut is used to lock the rod union in the lower union.

4. A helicopter tailplane attachment support structure as defined in claim 3, wherein: the brace bar assembly further comprises: a gasket; the gasket is arranged between the nut and the end face of the lower joint; the end face of the lower joint is provided with a groove, and one side of the gasket, which is close to the lower joint, is provided with a bulge matched with the groove; the protrusion cooperates with the groove to prevent rotation of the spacer.

5. A helicopter tailplane attachment support structure as defined in claim 4, wherein: the brace bar assembly further comprises: locking the wire;

the gasket is provided with a lock wire hole; the nut is provided with a safety hole; the lockwire passes through the lockwire hole and the safety hole and is used for preventing the nut from loosening.

6. A helicopter tailplane attachment support structure as defined in claim 5, wherein: the brace bar assembly further comprises: a knuckle bearing;

the joint bearing is arranged in a single lug of the rod joint; the rod joint is connected with the bottom of the vertical tail through a joint bearing.

7. A helicopter tailplane attachment support structure as defined in claim 5, wherein: the upper joint is provided with a bonding wire connecting hole; and the bond strap connecting hole is electrically connected with the horizontal tail wing through a bolt.

8. A helicopter tailplane attachment support structure as defined in claim 5, wherein: the upper end of the horizontal tail joint is provided with five course through holes; the course through hole is connected with the vertical tail through a bolt; two groups of lugs are respectively arranged on the left side and the right side of the horizontal tail joint, and each group of lugs comprises an upper lug and a lower lug which are horizontally arranged; the two groups of lug plates are connected with the horizontal tail wing through bolts.

Technical Field

The invention belongs to the technical field of connection of horizontal tail wings of helicopters. In particular to a connecting and supporting structure of a horizontal tail wing of a helicopter.

Background

The connection form and the details of the horizontal tail of the helicopter have great influence on the service life of the horizontal tail and the connecting pieces thereof, and the structure of using the cantilever beam structure to transmit the load of the horizontal tail in a single way causes poor balance stability of the horizontal tail, large bending moment at the root and easy generation of fatigue problem. It is desirable to design a length-adjustable support structure for supporting the horizontal rear wing while reinforcing and improving the connection of the root and the connection details.

The utility model patent "an adjustable device that replaces folding vaulting pole mechanism" that the utility model discloses in 2018, 04, 06 (publication number CN207191482U) mentions a folding supporting mechanism of undercarriage, and the purpose of this patent is in main undercarriage test, in order to realize the adjustment to the undercarriage gesture in static strength and fatigue test, designs a brand-new adjustable device, is used for replacing true folding vaulting pole mechanism in the test.

The invention patent of a helicopter horizontal tail connecting device (publication number CN105109670A) published on 12/02/2015 mentions a helicopter horizontal tail connecting device, and the purpose of the patent is to provide a connecting device capable of quickly disassembling and assembling a helicopter horizontal tail. However, the connecting device is used for transmitting the load of the horizontal tail in a single way, the fatigue resistance performance is poor, the service life of the horizontal tail is short, and the replacement and maintenance cost is extremely high.

An invention patent of a horizontal tail connecting device and a horizontal tail of a helicopter (publication number CN106342053B) disclosed in 11/27/2013 relates to a horizontal tail of a helicopter, which can adjust the installation angle on the ground and is generally used in the scientific research and trial flight stage of the helicopter.

The problems of the prior horizontal tail connecting technology are as follows:

the horizontal tail connection form of the prior art is a cantilever beam structure, a force transmission path is a single path for transmitting load, the load transmission efficiency is low, the stress of the root part of the horizontal tail and the joint of the horizontal tail is large, and the service life of the joint of the horizontal tail is short.

Secondly, the horizontal tail joint of the prior invention is an aluminum alloy machined part, and has low material strength, poor joint fatigue resistance, redundant materials in low stress areas and poor joint material utilization rate.

The diameter of the threaded area of the connecting bolt of the horizontal tail wing is small, the threaded part of the bolt is easy to generate fatigue fracture under the action of dynamic load, and the connecting pieces and the structure are isolated by adopting an anti-corrosion sealing mixture, and a protective layer of the connecting bolt is easy to fall off under the action of rotational wear in installation and use, so that the bolt is in direct contact with the outside air and generates electrochemical corrosion.

The horizontal tail wing of the prior invention is matched with a hole of a horizontal tail wing joint lug through a through hole installation sleeve reserved on a front beam, special bolts at two sides are in through connection, a gap needs to be reserved between the lug and the front beam so as to ensure the successful installation of the horizontal tail, and a gasket is used for filling the gap between the lug and the front beam. The original structure uses a gasket with fixed thickness, and paint layer tolerance, part tolerance and sealant tolerance are not considered, so that a gap exists between a horizontal tail connecting rear joint lug and a horizontal tail front beam, the horizontal tail is slightly displaced in the flight process, and the fatigue damage of the structure is easily caused.

Disclosure of Invention

The invention aims to provide a connecting and supporting structure of a horizontal tail wing of a helicopter, which has strong anti-fatigue capability, high bearing efficiency and excellent anti-corrosion performance.

In order to solve the technical problems, the technical scheme adopted by the invention is as follows:

a helicopter tailplane attachment support structure comprising: horizontal tail joint and strut assembly;

the horizontal tail joint is respectively connected with a horizontal tail and a vertical tail;

the stay bar component is divided into a left stay bar component and a right stay bar component;

two ends of the left stay bar component are respectively connected with the left pneumatic pressure center of the horizontal tail and the bottom of the vertical tail;

two ends of the right stay bar component are respectively connected with the pneumatic pressure center of the right side of the horizontal tail and the bottom of the vertical tail;

the strut assembly is adjustable in length.

Further, the brace bar assembly comprises: a circular tube, an upper joint, a lower joint and a rod joint;

two ends of the circular tube are respectively and fixedly connected with the upper joint and the lower joint;

the circular pipe is connected with the horizontal tail wing through an upper connector;

one end of the rod joint is a single lug, and the other end of the rod joint is a cylinder provided with external threads;

the lower joint is provided with a threaded hole matched with the external thread of the rod joint;

one end of the rod joint is connected with the vertical tail through the single lug, the other end of the rod joint is in threaded connection with the lower joint, and the rod joint rotates relative to the lower joint to adjust the length of the stay bar assembly.

Further, the brace bar assembly further comprises: a nut; the nut is sleeved on the threaded section of the rod joint and tightly attached to the lower joint; the nut is used to lock the rod union in the lower union.

Further, the brace bar assembly further comprises: a gasket; the gasket is arranged between the nut and the end face of the lower joint; the end face of the lower joint is provided with a groove, and one side of the gasket, which is close to the lower joint, is provided with a bulge matched with the groove; the protrusion cooperates with the groove to prevent rotation of the spacer.

Further, the brace bar assembly further comprises: locking the wire;

the gasket is provided with a lock wire hole; the nut is provided with a safety hole; the lockwire passes through the lockwire hole and the safety hole and is used for preventing the nut from loosening.

Further, the brace bar assembly further comprises: a knuckle bearing;

the joint bearing is arranged in a single lug of the rod joint; the rod joint is connected with the bottom of the vertical tail through a joint bearing.

Further, the upper joint is provided with a bonding wire connecting hole; and the bond strap connecting hole is electrically connected with the horizontal tail wing through a bolt.

Furthermore, five course through holes are formed in the upper end of the horizontal tail joint; the course through hole is connected with the vertical tail through a bolt; two groups of lugs are respectively arranged on the left side and the right side of the horizontal tail joint, and each group of lugs comprises an upper lug and a lower lug which are horizontally arranged; the two groups of lug plates are connected with the horizontal tail wing through bolts.

The horizontal tail connecting and supporting structure has the advantages of lower stress level of the root part of the horizontal tail and the joint of the horizontal tail and long service life. The connecting joint has the advantages of high strength, good corrosion resistance and fatigue performance, and has the characteristics of light weight, repeated iteration and removal of redundant materials by performing topology optimization design on the structure by using CAE analysis software. The supporting structure has the function of adjusting the length, can offset tolerance accumulation in the manufacturing process of parts and components, and is installed smoothly. The optional washer accurately adjusts the gap between the horizontal tail and the horizontal tail joint to avoid structural fatigue caused by micro-vibration during flight. Reasonable surface protection prevents the corrosion of the structure caused by the falling of the protector in the dismounting process.

Drawings

FIG. 1 is a schematic view of a horizontal tail connection support structure of a helicopter;

FIG. 2 is an isometric view of a horizontal tail joint;

FIG. 3 is a schematic view of a strut;

FIG. 4 is an exploded view of the strut at one side for adjusting length;

FIG. 5 is a schematic view of the connection at the horizontal tail joint;

wherein 1-horizontal tail wing, 2-vertical tail, 3-horizontal tail wing joint, 4-brace rod component, 5-joint, 6-joint, 7-shoulder bush, 8-bolt, 9-nut, 10-washer, 11-adjusting washer, 12-split pin, 13-round tube, 14-upper joint, 15-lower joint, 16-bush, 17-rod joint, 18-knuckle bearing, 19-nut and 20-gasket.

Detailed Description

The technical solution of the present invention is further explained with reference to the drawings and the detailed description.

A horizontal tail connection supporting structure of a helicopter is characterized in that a horizontal tail 1 and a vertical tail 2 are connected in the middle of the horizontal tail 1 through a horizontal tail joint 3, the horizontal tail 1 is matched with holes of lugs of the horizontal tail joint 3 after passing through a through hole installation sleeve reserved in a front beam, special bolts are used on two sides of the horizontal tail 1 for penetrating connection, and the horizontal tail joint 3 is connected with the vertical tail 2 through 5 bolts. Meanwhile, a stay bar assembly 4 is used for supporting between the left and right pneumatic pressure centers of the horizontal tail wing 1 and the rear beam of the vertical tail 2, the stay bar assembly 4 is connected with the horizontal tail wing 1 through a joint 5 through a bolt, and the stay bar assembly 4 and the vertical tail 2 are installed through a joint 6 through a bolt.

As shown in figure 2, the horizontal tail joint 3 is machined and manufactured by using 15-5PH stainless steel with high strength, good corrosion resistance and good fatigue performance, and the structure is subjected to topology optimization design by using CAE analysis software, repeated iteration is carried out, redundant materials are removed, and weight reduction design is carried out. The joint lug is provided with the shoulder bush 7 in an interference fit mode to prevent the abrasion of the front beam by the bolt and improve the fatigue performance of the joint of the front beam. The horizontal tail joint 3 is connected to the vertical fin 2 by 5 bolts.

The stay bar assembly is shown in fig. 3 and 4, the round tube 13 is connected with the upper joint 14 and the lower joint 15 by welding, 2 bushings 16 are installed with two fork lugs on the upper joint 14 by interference fit, and the bushings 16 are used for preventing bolts from wearing the hole wall of the upper joint 14.

The rod joint 17 is provided with a through long external thread on the shaft, the lower joint 15 is provided with an internal thread matched with the rod joint 17, when the rod joint 17 is screwed into the lower joint 15 to a proper length, the protrusion on the gasket 20 is clamped into the groove of the lower joint 15, then the nut 19 is screwed, the pretightening force generated by the screwed nut 19 can prevent the rod joint 17 from rotating, and then the nut 19 and the gasket 20 are further locked by using a locking line.

The rod joint 17 is provided with a joint bearing 18 for adjusting the slight difference of the central line of the stay bar assembly 4 and the vertical tail joint 5 which are not coaxial.

Fig. 5 is a schematic view of the connection of the horizontal rear wing joint, and as shown in fig. 1, the connection of the horizontal rear wing 1 and the horizontal rear wing joint 3 is realized through bolts 8, nuts 9, washers 10, adjusting washers 11 and cotters 12, wherein the adjusting washers 11 are selected from 6 optional washers with the thickness decreasing by 0.1mm in the trial assembly process from the thickest to the thinnest, so that the installation can be smoothly performed, and the clearance of the structure after installation is ensured to be less than 0.1 mm. All the contact surfaces of the washer 10 and the washer 11, the threaded area of the nut 9, the bottom of the head of the bolt 8, the polish rod and the threaded area are protected by grease which has good metal surface adhesion, can reduce friction between connecting structures and has an isolating function and a good anti-corrosion function. The phenomenon that the traditional anticorrosion sealing mixture is easy to fall off under the action of rotational abrasion in installation and use is avoided.

As shown in fig. 3, the upper joint 14 is provided with a bond wire attachment hole; and the bond strap connecting hole is electrically connected with the horizontal tail wing through a bolt.

The length-adjustable support structure can transmit partial load of a horizontal tail wing to a vertical tail wing structure through the support structure, so that the stress level of the root of the horizontal tail wing and the horizontal tail wing joint is reduced, and the service life of the horizontal tail wing is prolonged; the supporting rod with adjustable length is used for offsetting tolerance accumulated in the assembly and manufacturing process of parts of the horizontal tail wing and the vertical tail wing, and ensures the smooth installation of the supporting rod.

The strength of the horizontal tail joint is improved, the horizontal tail joint is optimally designed, materials of the horizontal tail joint are replaced, 15-5PH stainless steel with high strength, better corrosion resistance and better fatigue performance is used, the CAE analysis software is used for carrying out topology optimization design on the structure, iteration is carried out repeatedly, redundant materials are removed, and weight reduction design is carried out.

The diameter of the threaded area of the connecting bolt of the horizontal tail is increased, and the original anti-corrosion sealing mixture between each connecting piece and the structure is changed into lubricating grease. Thereby improving the surface adhesion of the coating, reducing the friction and the abrasion between the connecting structures, having the function of isolation and simultaneously having good anti-corrosion performance.

And accurately calculating the tolerance of a paint layer between the horizontal tail joint and the horizontal tail, the tolerance of parts and the tolerance accumulated value of the sealant to obtain the maximum and minimum value ranges of the gap between the horizontal tail joint and the horizontal tail, setting a plurality of gaskets with the thickness decreasing by 0.1mm in the range, and trial assembling from the thickest to the thinnest in the assembling process until the gaskets can be successfully assembled so as to ensure that the gap of the structural part is less than 0.1 mm.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.