WO2023093803A1

WO2023093803A1 - Trimming-type tailplane connection structure

Info

Publication number: WO2023093803A1
Application number: PCT/CN2022/134029
Authority: WO
Inventors: 赵荃; 刘长玮; 叶聪杰; 赵诗鸿
Original assignee: 中国商用飞机有限责任公司; 中国商用飞机有限责任公司上海飞机设计研究院
Priority date: 2021-11-29
Filing date: 2022-11-24
Publication date: 2023-06-01
Also published as: CN113955080A; CN113955080B

Abstract

A trimming-type tailplane connection structure (100), comprising: a tailplane upper mounting frame (111) and a tailplane lower mounting frame (112), the tailplane upper mounting frame (111) and the tailplane lower mounting frame (112) being mounted and connected to the body (200) of an aircraft; tailplane supporting beams (120) for connecting the tailplane upper mounting frame (111) to the tailplane lower mounting frame (112) and supporting same to form a frame plane, the tailplane supporting beams (120) serving as a part of a vertical load transfer system to transfer a vertical load component force, and also serving as a part of a heading load transfer system to transfer a heading component force; a heading linkage (130) for serving as a part of the heading load transfer system to transfer a heading component force, and also serving as a part of the vertical load transfer system to transfer a vertical load component force; and a linkage joint (140) and lateral linkages (150), the linkage joint (140) being provided at the portion where the tailplane upper mounting frame (111) is connected to the tailplane lower mounting frame (112), the two lateral linkages (150) being connected to the linkage joint (140), and the linkage joint (140) and the lateral linkages (150) serving as a part of a lateral load transfer system to transfer a lateral load component force, wherein the vertical load transfer system, the heading load transfer system and the lateral load transfer system are independently provided.

Description

Balanced flat tail connection structure

technical field

The present invention relates to a flat tail connection structure, more particularly to a trim type flat tail connection structure capable of balancing longitudinal moments during flight.

Background technique

The horizontal tail of the aircraft is installed on the horizontal tail at the rear of the fuselage, and the angle of attack of the horizontal stabilizer is changed by the drive of the actuator to balance the longitudinal moment during flight.

As the main wing surface structure of the aircraft, the horizontal tail of the aircraft bears external loads such as aerodynamic loads and inertial loads during the entire flight, and transmits external external loads to the fuselage section through the connecting structure. In this process, the connecting structure of the horizontal stabilizer plays a crucial role.

At present, the design of the horizontal tail connection structure of large aircraft with conventional layout mainly comes from two configurations.

One is the "integral bulkhead horizontal tail connection structure" represented by Boeing B787 and B777, and the other is the "multi-link horizontal tail connection structure" represented by the entire series of European Airbus A3XX aircraft. In addition, other main models, such as Russian SSJ-100 aircraft and MS-21 aircraft, also use the same "multi-link horizontal tail connection structure", while the horizontal tail connection structure of Bombardier/Airbus A220 (C series) aircraft It is based on the design of the "multi-link horizontal tail connection structure" of the European Airbus to modify the design form of some parts, but the design of the force transmission route and function realization scheme is still essentially the same as the "multi-link horizontal tail connection structure". Connection structure" is basically the same. Therefore, it can also be said that the two configurations of the "integral bulkhead horizontal tail connection structure" and "multi-link horizontal tail connection structure" cover almost all models currently in service.

In the professional field of aircraft structural design, the key performances of the trimmed horizontal tail connection structure include structural weight, completeness of the force transmission route, functional realization of the horizontal tail hinge rotation mechanism and bearings, overall aircraft maintenance, and repair characteristics. An ideal design solution requires balancing and meeting the above multiple performance indicators. However, due to the many factors to be considered in the design and the design constraints are also very complicated, so far, there are only the above two relatively mature design configurations Large-scale application on current aircraft models.

The design, verification and innovation of the aircraft's trimming horizontal tail connection structure has always been one of the core technologies that major aircraft manufacturers at home and abroad have focused on. How to break through the existing design limitations and design a new trim-type flat-tail connection structure that can balance and meet multiple specified performance indicators, which is different from the current two configurations, is a technical problem to be solved urgently.

Contents of the invention

The purpose of the present invention is to provide a new configuration of trim type flat tail connection structure that can balance and meet the specified performance index.

In order to achieve the above-mentioned purpose of the present invention, the present invention provides a trim type flat tail connection structure, which is characterized in that the flat tail connection structure includes: a flat tail upper installation frame and a flat tail lower installation frame as a flat tail installation frame, The upper installation frame and the lower installation frame of the flat tail are installed and connected to the fuselage of the aircraft; the flat tail support beam, the flat tail support beam connects the upper installation frame of the flat tail with the lower installation frame of the flat tail and supports it to form a frame plane, and The horizontal tail support beam, as a part of the vertical load transmission system, transmits to the fuselage the vertical load component suffered by the frame plane, and at the same time transmits it to the fuselage as a part of the directional load transmission system The component force of the heading on the frame plane; the heading link, the heading link extends from the center of the frame plane to a direction inclined relative to the frame plane, and the heading link acts as the A part of the heading transmission system transmits to the fuselage the component force of the heading on the frame plane, and at the same time, as a part of the vertical transmission system, transmits to the fuselage the vertical force on the frame plane. directional load component force; and a link joint and a lateral link, the link joint is arranged at the connecting portion between the upper mounting frame of the flat tail and the lower mounting frame of the flat tail, and is connected on the connecting rod joint There are two lateral connecting rods, and the connecting rod joints and the lateral connecting rods serve as a lateral load transmission system to transfer the lateral load component suffered by the frame plane to the fuselage, so The vertical carrying system, the heading carrying system and the lateral carrying system are set independently of each other.

Preferably, the horizontal tail support beam is provided with a horizontal tail hinge shaft mechanism as a part of the vertical load transmission system, and the horizontal tail support beam has a first support beam and a second support beam arranged in parallel at a predetermined interval. beam, the horizontal tail hinge shaft mechanism has a hinge part arranged between the first support beam and the second support beam at the middle part of the horizontal tail support beam, and the hinge part is fastened by rotating the connecting part The first support beam and the second support beam are connected to the hinge.

More preferably, the rotating fastening connection part has a bushing, a bolt and a ball bearing, and the bushing passes through the first supporting beam, the hinge, the The second support beam, the ball bearing is arranged between the hinge part and the bushing, so that the hinge part can rotate relative to the first support beam and the second support beam.

Further preferably, a bearing oil injection hole is formed at a position of the bush opposite to the ball bearing, and the bolt is inserted from the side of the first support beam to a position beyond the bearing oil injection hole, Moreover, an oil injection channel is formed in the rod portion of the bolt, and the oil injection channel communicates with the oil injection hole of the bearing.

Preferably, one end of the lateral connecting rod has a U-shaped portion with an open end facing outwards, and the mounting seat installed on the flat tail mounting frame and the flat tail has a An insertion part protruding from the opening end of the U-shaped part, and the opening end of the U-shaped part is connected to the insertion part of the mounting seat through a fastening structure.

More preferably, the two upright parts of the U-shaped part are respectively formed with through holes through which the bolts in the fastening structure can pass, and the insertion part of the mounting seat is formed with through holes, The through hole can allow the bolt to pass through, and a ball bearing capable of rotating the lateral connecting rod relative to the flat tail mounting frame and the flat tail is provided between the hole wall of the through hole and the bolt.

Preferably, said flat tail connection structure has two said lateral links extending in lateral direction towards two different directions.

Preferably, there are two directional links extending obliquely upward and downward relative to the frame plane from the center of the frame plane, and in the supporting reaction forces generated at the two directional links The direction of the component force along the vertical direction is opposite to cancel the force, and the direction of the component force along the course direction in the supporting reaction force generated at the two directional link places is the same, so the superposition of force occurs, The component force along the vertical direction of the counteracted support reaction force is taken as the vertical load component force on the frame plane, and the component force along the course direction of the superimposed support reaction force is taken as the frame plane The load component experienced along the heading.

Preferably, when the flat tail supporting beam is installed on the flat tail mounting frame, the bushing arranged on the flat tail mounting frame is located between the first supporting beam and the second support of the flat tail supporting beam. Between the beams, the first support beam and the second support beam are connected to the bushing through a fastening connection part.

Preferably, a front joint is provided at the front end of the horizontal tail, and the supporting reaction force generated on the front joint of the horizontal tail can be decomposed into a component force along the vertical direction and a component force along the course direction.

Preferably, the upper mounting frame of the flat tail and the lower mounting frame of the flat tail each include a D-shaped frame body, the frame body is composed of an arc-shaped frame, a straight beam and a plurality of reinforcing ribs, and the straight beam will Both ends of the arc-shaped frame are connected, and a plurality of the reinforcing ribs are connected together on the outer side of the straight beam opposite to the arc-shaped frame to form a reinforcing-rib joint.

More preferably, a plurality of said reinforcing ribs point to the same center located on the outside.

More preferably, the reinforcing rib joint part connects a plurality of the reinforcing ribs outside the main body of the frame, and the reinforcing rib joint part of the upper mounting frame of the flat tail is connected with the reinforcing rib joint part of the lower mounting frame of the flat tail interconnected.

More preferably, a mounting hole for mounting to the fuselage is formed at a position where the two ends of the arc-shaped frame are connected to the two ends of the straight beam.

According to the above configuration, since the horizontal tail support beam, as a part of the vertical load transmission system, transmits the vertical load component force received by the frame plane to the fuselage, and simultaneously serves as a part of the yaw load transmission system to the fuselage. The fuselage transmits the component force of the heading on the frame plane, and the yaw link, as a part of the heading transmission system, transmits the component force of the heading on the frame plane to the fuselage, and at the same time serves as A part of the vertical load transmission system transmits to the fuselage the component force of the vertical load on the frame plane, while the link joint and the lateral link serve as a part of the lateral load transmission system to the fuselage. The fuselage transmits the lateral load components received by the frame plane, and the vertical load transmission system, the directional load transmission system and the lateral load transmission system are set independently of each other, therefore, the The vertical load transmission system, the directional load transmission system and the lateral load transmission system function separately, and the safety feature of preventing structural damage is high.

In addition, the present invention innovatively proposes three sets of independent flat tail load transmission systems, which are integrated with the frame to form a flat tail connection structure with complete functions and meeting the design requirements. Compared with "structure" and "multi-link horizontal tail connection structure", it has better safety features against structural damage.

Description of drawings

Fig. 1 is the schematic diagram of the flat tail connection structure of the trimming type of the present invention located at the fuselage rear (horizon tail).

FIG. 2 is a partially enlarged view showing a state in which the trim-type horizontal tail connection structure shown in FIG. 1 is attached to an aircraft fuselage (horizon tail).

FIG. 3 is a diagram showing a schematic configuration of the trim type horizontal tail connection structure shown in FIG. 1 .

Fig. 4 is an enlarged view showing a connection structure (fastening connector) between a flat tail support beam and a flat tail installation frame in the flat tail connection structure shown in Fig. 3 .

Fig. 5 is a cross-sectional view showing the connection structure (fastening connector) shown in Fig. 4 .

FIG. 6 is an enlarged view showing a schematic connection structure of the horizontal tail hinge shaft mechanism in the horizontal tail connection structure shown in FIG. 3 .

Fig. 7 is a sectional view showing the internal mounting structure of the horizontal tail hinge shaft mechanism shown in Fig. 6 .

FIG. 8 is an enlarged view showing a schematic connection structure of the lateral link in the horizontal tail connection structure shown in FIG. 3 , the horizontal tail mounting frame of the aircraft fuselage, and the horizontal tail.

Fig. 9 is a cross-sectional view showing the internal mounting structure of the side link and the stabilizer shown in Fig. 8 .

Fig. 10(a) to Fig. 10(f) are schematic diagrams showing the decomposition of the force transmission route of the trimmed horizontal tail connection structure.

(Symbol Description)

100 flat tail connection structure;

110 horizontal tail installation frame;

111 mounting frame on the flat tail;

112 lower installation frame of flat tail;

111a, 112a frame main part;

111b, 112b arc-shaped frames;

111c, 112c straight beams;

111d, 112d reinforcing ribs;

111e, 112e reinforcing rib junction;

111f, 112f mounting holes;

111g, 112g mounting seat;

120 horizontal tail support beam;

121 first support beam;

122 second support beam

123 fastening connection part;

123a bolt;

123b nut;

123c sleeve

123d washer

124 horizontal tail hinge shaft mechanism;

124a hinge;

124b rotate and fasten the connecting part;

124b1 bushing;

124b2 bolt;

124b3 ball bearing;

124b4 bearing oil hole;

124b5 oil injection channel;

130 heading link;

140 connecting rod joint;

141 through holes;

142 ball bearings;

150 lateral linkage;

151 U-shaped part;

151a, 151a upright part

151b, 151b through holes;

152 bolts;

153 nuts;

154 connecting parts;

154a through hole;

155 bolts;

156 nuts;

157 washers;

P aerodynamic load;

G lateral inertia load;

R1, R2, R3, R3', R4, R4' supporting reaction force;

Component forces of R1x, R2x, R2x’, R4x, R4x’ along the course direction;

Component forces of R1y, R2y, R2y', R4y, R4y' along the vertical direction;

200 fuselage;

201 flat tail;

210 mount;

211 seats;

212 insertion part;

213 through holes;

220 ball bearings;

230 spacers.

Detailed ways

Hereinafter, the trim type horizontal tail connection structure 100 of the present invention will be described in detail with reference to the accompanying drawings. Fig. 1 is the schematic diagram that is positioned at the fuselage rear portion (horizontal tail 201) of the present invention's flat tail connection structure 100 of the trim type, and Fig. 2 is the state that the flat tail connection structure 100 of the trim type shown in Fig. 1 is installed to the aircraft fuselage 200 Fig. 3 is a diagram showing a schematic structure of the trim type horizontal tail connection structure 100 shown in Fig. 1 . FIG. 4 is an enlarged view showing a connection structure (fastening connection portion 123 ) between the tail support beam 120 and the tail mounting frame 110 in the tail connection structure 100 shown in FIG. 3 . FIG. 5 is a cross-sectional view showing the connection structure (fastening connection portion 123 ) shown in FIG. 4 .

As shown in Fig. 1 and Fig. 2, the horizontal tail connection structure 100 of the trim type of the present invention is installed on the horizontal tail 201 of the fuselage 200 at the rear of the aircraft, and the frame plane of the flat tail mounting frame 110 is subjected to different aerodynamic loads, inertial loads, etc. Direction loads are transferred to the aircraft fuselage 200 .

As shown in Figure 2, the flat tail connection structure 100 of the present invention comprises the upper mounting frame 111 and the lower mounting frame 112 of the flat tail as the flat tail mounting frame 110, the flat tail support beam 120, the steering link 130 (see Figure 3), the connecting rod joint 140 and lateral link 150.

The flat tail upper mounting frame 111 and the flat tail lower mounting frame 112 respectively include substantially D-shaped frame

main parts

111a, 112a. The frame

main parts

111a, 112a are, for example, composed of arc-shaped frames 111b, 112b,

straight beams

111c, 112c, and a plurality of reinforcing

ribs

111d, 112d. The ends are connected, and a plurality of the reinforcing

ribs

111d, 112d are connected together on the outer side of the

straight beams

111c, 112c opposite to the arc-shaped frames 111b, 112b, so as to form the reinforcing

rib joints

111e, 112e. It is preferable to direct a plurality of said reinforcing

ribs

111d, 112d to the same center located on the outside. In addition, mounting

holes

111f, 112f for mounting the flat tail 201 of the aircraft fuselage 200 are formed at the positions where the ends of the arc-shaped frames 111b, 112b are connected to the ends of the

straight beams

111c, 112c.

More specifically, as shown in FIG. 2 and FIG. 3, the frame

main body

111a, 112a has three reinforcing

ribs

111d, 112d, and the middle one of the reinforcing

ribs

111d, 112d is perpendicular to the

straight beams

111c, 112c. Connect the arc-shaped frames 111b, 112b to the central parts of the

straight beams

111c, 112c, and the two reinforcing

ribs

111d, 112d on both sides connect the arc-shaped frames 111b, 112b to the parts other than the central parts of the

straight beams

111c, 112c , and the three reinforcing

ribs

111d, 112d are connected together at the outer side of the

straight beams

111c, 112c opposite to the arc-shaped frames 111b, 112b. The three said reinforcing

ribs

111d, 112d point to the same center located on the outside.

The

reinforcement rib joints

111e, 112e connect a plurality of the

reinforcement ribs

111d, 112d outside the frame

main body

111a, 112a, and the reinforcement rib joints 111e of the upper mounting frame 111 of the flat tail are installed with the bottom of the flat tail. The reinforcing rib coupling portions 112e of the frame 112 are connected to each other.

The flat tail support beam 120 is arranged between the flat tail upper mounting frame 111 and the flat tail lower mounting frame 112, and is connected with the

straight beams

111c, 112c on the left and right sides by fastening the connecting parts 123 The mounting

seat portions

111g and 112g are connected.

More specifically, the horizontal tail support beam 120, which is part of the vertical load transfer system and the yaw load transfer system, will be described. As shown in FIG. 4 , the horizontal tail support beam 120 has a first support beam 121 and a second support beam 122 arranged in parallel with a predetermined distance apart. The mounting

seat parts

111g, 112g of the

beams

111c, 112c are located between the first support beam 121 and the second support beam 122 of the horizontal tail support beam 120, and the first support beam 121 and the second support beam 122 are connected by the fastening connection part 123 It is connected to the mounting

seat parts

111g and 112g.

As shown in Figure 5, the fastening connection part 123 is composed of a bolt 123a and a nut 123b, and the bolt 123a passes through the first support beam 121 and one side of the second support beam 122 (for example, the first support beam 121 side) in sequence. Insert a support beam 121, mounting

seat portions

111g, 112g, and the second support beam 122, and use nuts 123b on the other side of the first support beam 121 and the second support beam 122 (for example, the second support beam 122 side) Tighten the bolts 123a. In addition, preferably, sleeves 123c are interposed between the mounting

seat portions

111g, 112g and the first support beam 121 or the second support beam 122, respectively. In addition, more preferably, washers 123d are interposed between the head of the bolt 123a and the first support beam 121, and between the nut 123b and the second support beam 122, respectively.

In addition, the flat tail support beam 120 is provided with a flat tail hinge shaft mechanism 124 described later, and the flat tail hinge shaft mechanism 124 will be described in detail below with reference to FIG. 6 and FIG. 7 . Wherein, Fig. 6 is an enlarged view showing the schematic connection structure of the flat tail hinge shaft mechanism 124 in the flat tail connection structure 100 shown in Fig. 3 , and Fig. 7 is a section showing the internal installation structure of the flat tail hinge shaft mechanism 124 shown in Fig. 6 picture.

As shown in Fig. 6, the horizontal tail hinge shaft mechanism 124 has a hinge part 124a arranged between the first support beam 121 and the second support beam 122 at the middle part of the horizontal tail support beam 120, and the hinge part 124a is fastened by rotation The portion 124b connects the first support beam 121 and the second support beam 122 with the hinge member 124a.

As shown in FIG. 7 , the rotational fastening connection part 124b has a bushing 124b1, a bolt 124b2, and a ball bearing 124b3. The bush 124b1 passes through the first support beam 121 , the hinge member 124a , the second support beam 122 sequentially from the first support beam 121 side and passes out to the second support beam 122 side. The ball bearing 124b3 is disposed between the hinge member 124a and the bushing 124b1, and the hinge member 124a can be positioned relative to the first support beam 121 and the second support beam by using the ball bearing 124b3. 122 turns. A bearing oiling hole 124b4 is formed at a portion of the bush 124b1 facing the ball bearing 124b3. The bolt 124b2 is inserted from the side of the first support beam 121 to a position beyond the bearing oil injection hole 124b4, and an oil injection channel 124b5 is formed in the shaft of the bolt 124b2, and the oil injection channel 124b5 communicates with the bearing oil injection hole 124b4 Therefore, lubricating oil can be injected into the ball bearing 124b3 from the bearing oil injection hole 124b4 through the oil injection channel 124b5, so as to reduce the frictional resistance when the ball bearing 124b3 rotates.

Next, with reference to FIG. 8 and FIG. 9 , the lateral link 150 as a lateral transmission system will be described.

What Fig. 8 and Fig. 9 show is the schematic connection structure of the flat tail lateral connecting rod 150 shown in Fig. 3 and the flat tail installation frame 110 and the flat tail 201 of the aircraft, wherein, Fig. 8 is an enlarged view, and Fig. 9 is an internal installation structure Sectional view. The two ends of the lateral connecting rod 150 are double lug joints. Figure 9 shows the form of connection with the flat tail 201, but the connection form of the lateral connecting rod 150 and the flat tail mounting frame 110 is the same as that of the flat tail 201. The connected object is different.

As shown in Figure 9, the lateral connecting rod 150 as the lateral transmission system is inserted at one end with a U-shaped part 151 with the opening end outward, and the open end of the U-shaped part 151 of the lateral connecting rod 150 passes through the The fastening structure formed by the bolt 152 and the nut 153 is connected with the mounting seat 210 installed on the flat tail 201 of the aircraft fuselage 200 . Through

holes

151 b , 151 b through which bolts 152 can pass are respectively formed on the two

upright portions

151 a , 151 a of the U-shaped portion 151 .

In addition, as shown in Figure 9, the mounting seat 210 that is installed on the flat tail 201 (and flat tail installation frame 110) of the aircraft has the insertion portion 212 that stretches out toward the open end of U-shaped portion 151 from the seat surface 211 of mounting seat 210 A through hole 213 is also formed on the insertion portion 212 of the mounting seat 210, the through hole 213 can be used for the bolt 152 to pass through, and a side wall is provided between the hole wall of the through hole 213 and the bolt 152 To the ball bearing 220 that the connecting rod 150 rotates relative to the stabilizer 201 (and the stabilizer mounting frame 110). In addition, it is preferable that spacers 230 are respectively interposed between the ball bearing 220 and the seat portion 210 and the insertion portion 212 of the mounting seat 210 .

By inserting the bolt 152 from one side of the U-shaped portion 151 of the lateral link 150 and sequentially passing through the through hole 151b formed on the upright portion 151a on one side of the U-shaped portion 151, the through hole 213 formed on the mounting seat 210, and the through hole 213 formed on the The through hole 151b of the upright portion 151a on the other side of the U-shaped portion 151, and the bolt 152 is fastened with a nut 153 on the other side of the U-shaped portion 151, so that the lateral link 150 can be connected as shown in FIG. It is installed on the horizontal tail 201 (and the horizontal tail installation frame 110 ) of the aircraft in a rotating manner relative to the horizontal tail 201 (and the horizontal tail installation frame 110 ) of the aircraft.

Next, the yaw link 130 as a part of the yaw transmission system will be described.

The directional link 130 is directed from the same center to the outside of the three reinforcing

ribs

111d, 112d of the frame

main body

111a, 112a toward the upper mounting frame 111 of the horizontal tail relative to the mounting frame 110 of the horizontal tail. There are two horizontal tail mounting frames 112 extending obliquely upward and downward (see FIG. 10( e )) for supporting the horizontal tail connecting mechanism 100 .

Hereinafter, with reference to Fig. 10 (a) to Fig. 10 (e), the vertical carrying system and lateral direction of the flat tail system including the flat tail connection structure 100 of the present embodiment and the front joint of the flat tail 201 located at the rear end of the fuselage are respectively discussed. The load transmission system and the force transmission route of the heading transmission system will be described. Among them, Figure 10(a) is a schematic diagram of the overall force analysis of the horizontal tail system under the action of aerodynamic load P and lateral inertial load G, and Figure 10(b) is an enlarged representation of the effect of aerodynamic load P and lateral inertial load G The schematic diagram of the force analysis of the front joint of the flat tail 201 below, Fig. 10 (c) is a schematic diagram of the force analysis of the flat tail support beam 120 under the action of the aerodynamic load P and the lateral inertial load G, Fig. 10 (d) is It shows the diagram of the force transmission path of the vertical load transmission system under the action of the aerodynamic load P, and Fig. 10(e) is a schematic diagram showing the force transmission path of the lateral load transmission system under the action of the lateral inertial load G, Fig. 10 (f) is a diagram showing the force transmission path of the heading load transmission system under the joint action of the aerodynamic load P and the lateral inertial load G.

As shown in Figure 10(a), during the flight of the aircraft, the fuselage 200 bears the effects of the aerodynamic load P and the lateral inertial load G at the same time. Under the action of the above load, the support reaction force R1 is generated at the front joint of the flat tail 201, the support reaction forces R2 and R2' are generated at the two horizontal tail support beams 120, and the support reaction force R3 is generated at the two lateral connecting rods 150. The two directional links 130 generate supporting reaction forces R4, R4'. Among them, as shown in Figure 10(b), the supporting reaction force R1 generated by the front joint of the horizontal tail 201 can be decomposed into a component force R1y along the vertical direction and a component force R1x along the heading direction, as shown in Figure 10(c) As shown, the supporting reaction forces R2, R2' generated on the horizontal tail support beam 120 can be decomposed into component forces R2y, R2y' along the vertical direction and component forces R2x, R2x' along the yaw direction.

Next, the force transmission path of the vertical load transmission system will be described. When the fuselage 200 is only subjected to the downward aerodynamic force P as a vertical load, as shown in Fig. Component force R1y, the component force R1y is directly transmitted to the fuselage 200 as a vertical load component force, and a component force R2y along the vertical direction that is opposite to the direction of the aerodynamic force P is generated at the flat tail support beams 120 on both sides. R2y', the component forces R2y and R2y' have the same direction and are superimposed as load components along the vertical direction from the horizontal tail support beam 120 to the fuselage 200 via the horizontal tail upper mounting frame 111 and the horizontal tail lower mounting frame 112 of the horizontal tail connecting structure 100 , in addition, the support reaction forces R4, R4' generated at the yaw link 130 can be decomposed into component forces R4y, R4y' along the vertical direction and component forces R4x, R4x' along the yaw direction, which along the vertical direction The direction of the component force R4y, R4y' in the direction is opposite to force cancellation, and the component force along the vertical direction of the support reaction force R4, R4' after force cancellation (if the component force R4y=component force R4y', then support The component force along the vertical direction of the reaction force R4, R4' is zero) as the load component force along the vertical direction received by the frame plane and also as the load component force along the vertical direction through the horizontal tail connecting structure 100 The mounting frame 111 and the lower mounting frame 112 of the horizontal tail are transmitted to the fuselage 200 , thereby forming a force transmission path of the vertical load transmission system.

Next, the force transmission path of the lateral load transmission system will be described. When the fuselage 200 is only subjected to an inertial load G as a side load, as shown in FIG. The force R3 produces a support reaction force R3' as a tensile load at the lateral link 150 located on the opposite side of the direction of the inertial load G. The upper horizontal tail mounting frame 111 and the flat tail lower mounting frame 112 of the connecting structure 100 are transmitted to the fuselage 200 , thereby forming a force transmission path of the lateral load transmission system.

Next, the force transmission path of the directional load transmission system will be described. When the fuselage 200 is subjected to the combined action of the aerodynamic force P and the inertial load G, a component force R1x pointing to the course direction on the opposite side of the horizontal tail connection structure 100 is generated at the front joint of the horizontal tail 201, and the component force R1x is used as a load along the course The component force is directly transmitted to the fuselage 200. In addition, the supporting reaction force R4, R4' is generated at the directional link 130, and the above-mentioned supporting reaction force R4, R4' can be decomposed into component forces R4y, R4y along the vertical direction 'and the component force R4x, R4x' along the course direction, the direction of the component force R4x, R4x' along the course direction is the same (the superposition of force occurs) and is the same as the component force R1x along the course direction, the superimposed The component forces along the course direction of the reaction forces R4 and R4' are used as the component forces along the course direction of the frame plane.

It is transmitted to the fuselage 200 through the upper and lower mounting frame 111 of the horizontal tail connecting structure 100 and the lower mounting frame 112 of the horizontal tail. In addition, the horizontal tail support beam 120 will also produce support reaction forces R2x, R2x' in opposite directions due to the action of the inertial load G, and also pass through the horizontal tail upper mounting frame 111 of the horizontal tail connecting structure 100 as a load component along the course. The lower mounting frame 112 is transmitted to the fuselage 200, thereby forming a force transmission path of the heading transmission system.

The three systems of the vertical loading system, the heading loading system and the lateral loading system are independent of each other and function respectively.

Additional advantages and modifications will readily occur to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.

For example, in an embodiment of the present invention, the yaw link 130 is set to extend obliquely upward and downward relative to the plane where the horizontal tail upper mounting frame 111 and the horizontal tail lower mounting frame 112 as the horizontal tail mounting frame 110 are located. Two examples are used for illustration, but the present invention is not limited thereto. The directional link 130 only needs to be extended from the center of the frame plane to a direction inclined relative to the frame plane, or only One, and more than three can also be set.

In addition, in the embodiments and illustrations of the present invention, the yaw link 130 extends in a direction parallel to the vertical plane, that is, extends toward the vertical direction and also extends toward the yaw direction, but the present invention is not limited thereto, so The directional link 130 extending obliquely upward and downward also includes the situation that the directional link 130 can be extended laterally at the same time. At this time, the directional link 130 can also be used as a part of the lateral load system The body 200 transmits the load component along the lateral direction on the frame plane.

Claims

A trim type horizontal tail connection structure (100), characterized in that,

The flat tail connection structure (100) comprises:

Mounting frame (111) and lower mounting frame (112) of flat tail as flat tail mounting frame (110), described flat tail upper mounting frame (111) and described flat tail lower mounting frame (112) are installed and connected to the machine of aircraft body(200);

The horizontal tail support beam (120), the horizontal tail support beam (120) connects the horizontal tail upper mounting frame (111) and the horizontal tail lower mounting frame (112) and supports them to form a frame plane, and the horizontal tail support beam (120 ) as a part of the vertical load transmission system to the fuselage (200) to transmit the vertical load component force on the frame plane, and at the same time as a part of the heading load transmission system to the fuselage (200 ) transmits the component force of the heading that the frame plane is subjected to;

a yaw link (130), the yaw link (130) is extended from the center of the frame plane to a direction inclined relative to the frame plane, and the yaw link (130) serves as the yaw transmission A part of the system transmits to the fuselage (200) the component force of the heading on the frame plane, and at the same time transmits the component of the frame plane to the fuselage (200) as part of the vertical load transfer system. The vertical load component of ; and

A link joint (140) and a lateral link (150), the link joint (140) is arranged at the connecting portion of the upper mounting frame (111) of the flat tail and the lower mounting frame (112) of the flat tail, and Two lateral connecting rods (150) are connected to the connecting rod joint (140), and the connecting rod joint (140) and the lateral connecting rod (150) serve as a lateral load transmission system to the The fuselage (200) transmits the load component along the lateral direction received by the frame plane,

The vertical carrying system, the heading carrying system and the lateral carrying system are set independently of each other.
The flat tail connecting structure (100) of trimming type as claimed in claim 1, is characterized in that,

The horizontal tail support beam (120) is provided with a horizontal tail hinge shaft mechanism (124) as a part of the vertical load transmission system and a part of the directional load transmission system,

The flat tail support beam (120) has a first support beam (121) and a second support beam (122) arranged in parallel with a predetermined distance apart,

The horizontal tail hinge shaft mechanism (124) has a hinge (124a) arranged between the first support beam (121) and the second support beam (122) at the middle part of the horizontal tail support beam (120). ), the hinge (124a) connects the first support beam (121) and the second support beam (122) to the hinge (124a) by rotating the fastening connection portion (124b).
The flat tail connecting structure (100) of trim type as claimed in claim 2, is characterized in that,

The rotational fastening connection (124b) has a bushing (124b1), a bolt (124b2) and a ball bearing,

The bush (124b1) passes through the first support beam (121), the hinge (124a), and the second support beam (122) sequentially from the side of the first support beam (121),

The ball bearing is arranged between the hinge (124a) and the bush (124b1), so that the hinge (124a) can be relative to the first support beam (121) and the second The support beam (122) rotates.
The flat tail connecting structure (100) of trim type as claimed in claim 3, is characterized in that,

A bearing oil injection hole (124b4) is formed at a position of the bush (124b1) opposite to the ball bearing,

The bolt (124b2) is inserted from the side of the first support beam (121) to a position beyond the oil injection hole (124b4) of the bearing, and an oil injection channel (124b5) is formed in the shank of the bolt (124b2),

The oil injection channel (124b5) communicates with the bearing oil injection hole (124b4).
The flat tail connecting structure (100) of trimming type as claimed in claim 1, is characterized in that,

The lateral connecting rod (150) is inserted at one end with a U-shaped portion (151) with its open end facing outwards,

The installation seat (210) installed on the flat tail installation frame (110) and the flat tail (201) has the opening from the seat surface (211) of the installation seat (210) to the U-shaped part (151) The insertion portion (212) protruding from the end,

The opening end of the U-shaped portion (151) is connected to the insertion portion (212) of the mounting seat (210) through a fastening structure.
The flat tail connecting structure (100) of trim type as claimed in claim 5, is characterized in that,

The two upright parts (151a, 151a) of the U-shaped part (151) are respectively formed with through holes (151b, 151b) through which the bolts (152) in the fastening structure can pass through,

A through hole (213) is formed on the insertion part (212) of the mounting base (210), the through hole (213) can be passed through by the bolt (152), and the hole of the through hole (213) A ball bearing (220) is provided between the wall and the bolt (152) to enable the lateral connecting rod (150) to rotate relative to the flat tail mounting frame (110) and the flat tail (201).
The flat tail connecting structure (100) of trimming type as claimed in claim 1, is characterized in that,

The flat tail connection structure (100) has two of the lateral links (150) extending in two different directions in the lateral direction.
The flat tail connecting structure (100) of trimming type as claimed in claim 1, is characterized in that,

There are two directional links (130) extending obliquely upward and downward relative to the frame plane from the center of the frame plane,

The direction of the component force (R4y, R4y') along the vertical direction in the supporting reaction force (R4, R4') generated at the two yaw linkages (130) is opposite to that of force cancellation,

The component forces (R4y, R4y') along the course direction in the reaction forces (R4, R4') generated at the two course links (130) are in the same direction and the superposition of forces occurs,

The component force along the vertical direction of the offset reaction force (R4, R4') is used as the component force along the vertical direction of the frame plane,

The component force along the course direction of the superimposed support reaction force (R4, R4') is used as the component force along the course direction of the frame plane.
The flat tail connecting structure (100) of trim type as claimed in claim 2, is characterized in that,

When the flat tail supporting beam (120) is installed on the flat tail mounting frame (110), the bushing provided on the flat tail mounting frame (110) is located on the first side of the flat tail supporting beam (120). between the support beam (121) and the second support beam (122), and connect the first support beam (121) and the second support beam (122) to the Bushing connection.
The trim type horizontal tail connection structure (100) according to any one of claims 1 to 9, characterized in that,

A front joint is provided at the front end of the flat tail (201),

The supporting reaction force (R1) generated on the front joint of the horizontal tail (201) can be decomposed into a component force (R1y) along the vertical direction and a component force (R1x) along the heading direction.
The trim type horizontal tail connection structure (100) according to any one of claims 1 to 9, characterized in that,

The upper mounting frame (111) of the flat tail and the lower mounting frame (112) of the flat tail each include a D-shaped frame main body,

The main body of the frame is composed of an arc-shaped frame, a straight beam and a plurality of reinforcing ribs, the straight beam connects the two ends of the arc-shaped frame, and the plurality of reinforcing ribs are connected between the straight beam and the arc-shaped The outer parts of the opposite sides of the frame are joined together to form a stiffener joint.
The trim type horizontal tail connection structure (100) according to claim 11, characterized in that,

A plurality of said reinforcing ribs point to the same center located on the outside.
The trim type horizontal tail connection structure (100) according to claim 11, characterized in that,

The reinforcement rib joint part connects a plurality of the reinforcement ribs outside the frame main body, and the reinforcement rib joint part (111e) of the horizontal tail upper mounting frame (111) is connected with the horizontal tail lower mounting frame (112) The rib joints (112e) are connected to each other.
The trim type horizontal tail connection structure (100) according to claim 11, characterized in that,

Mounting holes for mounting to the fuselage (200) are formed at the positions where the two ends of the arc-shaped frame are connected to the two ends of the straight beam.