WO2023093803A1 - Structure de liaison de plan fixe horizontal de type à compensation de régime - Google Patents

Structure de liaison de plan fixe horizontal de type à compensation de régime Download PDF

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Publication number
WO2023093803A1
WO2023093803A1 PCT/CN2022/134029 CN2022134029W WO2023093803A1 WO 2023093803 A1 WO2023093803 A1 WO 2023093803A1 CN 2022134029 W CN2022134029 W CN 2022134029W WO 2023093803 A1 WO2023093803 A1 WO 2023093803A1
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WIPO (PCT)
Prior art keywords
tail
support beam
frame
mounting frame
flat
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PCT/CN2022/134029
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English (en)
Chinese (zh)
Inventor
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
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Publication of WO2023093803A1 publication Critical patent/WO2023093803A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/02—Tailplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces

Definitions

  • 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.
  • 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.
  • 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.
  • the connecting structure of the horizontal stabilizer plays a crucial role.
  • the design of the horizontal tail connection structure of large aircraft with conventional layout mainly comes from two configurations.
  • 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.
  • 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 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.
  • 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
  • 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
  • the vertical carrying system, the heading carrying system and the lateral carrying system are set independently of each other.
  • 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.
  • 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.
  • 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.
  • 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.
  • one end of the lateral connecting rod has a U-shaped portion with an open end facing outwards
  • 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.
  • 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.
  • said flat tail connection structure has two said lateral links extending in lateral direction towards two different directions.
  • 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
  • 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 is taken as the vertical load component force on the frame plane.
  • 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.
  • 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.
  • 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.
  • a plurality of said reinforcing ribs point to the same center located on the outside.
  • 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.
  • 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.
  • 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
  • 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.
  • 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.
  • 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.
  • 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
  • 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 .
  • 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 .
  • 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.
  • 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.
  • 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.
  • 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.
  • the horizontal tail support beam 120 which is part of the vertical load transfer system and the yaw load transfer system, will be described.
  • 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.
  • 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.
  • sleeves 123c are interposed between the mounting seat portions 111g, 112g and the first support beam 121 or the second support beam 122, respectively.
  • 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.
  • 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
  • Fig. 7 is a section showing the internal installation structure of the flat tail hinge shaft mechanism 124 shown in Fig. 6 picture.
  • 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.
  • 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.
  • 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.
  • 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 .
  • 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
  • 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 .
  • the bolt 152 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.
  • 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.
  • FIG. 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
  • Figure 10(b) is an enlarged representation of the effect of aerodynamic load P and lateral inertial load G
  • 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
  • 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.
  • the fuselage 200 bears the effects of the aerodynamic load P and the lateral inertial load G at the same time.
  • 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
  • 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'.
  • 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)
  • 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.
  • 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
  • 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 force transmission path of the lateral load transmission system will be described.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.

Abstract

Une structure de liaison de plan fixe horizontal de type à compensation de régime (100) comprenant : un cadre de montage supérieur de plan fixe horizontal (111) et un cadre de montage inférieur de plan fixe horizontal (112), le cadre de montage supérieur de plan fixe horizontal (111) et le cadre de montage inférieur de plan fixe horizontal (112) étant montés et reliés au fuselage (200) d'un aéronef ; des poutres de support de plan fixe horizontal (120) pour relier le cadre de montage supérieur du plan fixe horizontal (111) au cadre de montage inférieur du plan fixe horizontal (112) et le soutenir pour former un plan de cadre, les poutres de support du plan fixe horizontal (120) faisant office de partie d'un système de transfert de charge verticale pour transférer une force de composante de charge verticale et faisant également office de partie d'un système de transfert de charge de cap pour transférer une force de composante de cap ; une liaison de cap (130) pour faire office de partie du système de transfert de charge de cap pour transférer une force de composante de cap et faisant également office de partie du système de transfert de charge verticale pour transférer une force de composante de charge verticale ; et une articulation de liaison (140) et des liaisons latérales (150), l'articulation de liaison (140) étant disposée au niveau de la partie où le cadre de montage supérieur du plan fixe horizontal (111) est relié au cadre de montage inférieur du plan fixe horizontal (112), les deux liaisons latérales (150) étant reliées à l'articulation de liaison (140) et l'articulation de liaison (140) et les liaisons latérales (150) faisant office de partie d'un système de transfert de charge latérale pour transférer une force de composante de charge latérale, le système de transfert de charge verticale, le système de transfert de charge de cap et le système de transfert de charge latérale étant fournis indépendamment.
PCT/CN2022/134029 2021-11-29 2022-11-24 Structure de liaison de plan fixe horizontal de type à compensation de régime WO2023093803A1 (fr)

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CN202111431696.XA CN113955080B (zh) 2021-11-29 2021-11-29 配平式的平尾连接结构
CN202111431696.X 2021-11-29

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CN113955080B (zh) * 2021-11-29 2023-10-20 中国商用飞机有限责任公司 配平式的平尾连接结构
CN114906313B (zh) * 2022-06-10 2023-11-10 白鲸航线(北京)科技有限公司 一种飞机尾翼与机身的连接结构
CN115817791B (zh) * 2023-01-09 2023-04-14 北京启时智航科技有限公司 平尾作动机构及机翼结构

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CN102307782A (zh) * 2008-12-18 2012-01-04 空客运营有限公司 在飞行器的后端中的负载引导区域的结构
CN102963521A (zh) * 2012-11-09 2013-03-13 北京航空航天大学 一种民用飞机水平尾翼中央翼
CN104340352A (zh) * 2013-07-30 2015-02-11 空中客车西班牙运营有限责任公司 飞机的后机身区段
CN110920867A (zh) * 2019-12-09 2020-03-27 中航沈飞民用飞机有限责任公司 一种民用客机平尾侧向惯性载荷承载铰链接头
CN113955080A (zh) * 2021-11-29 2022-01-21 中国商用飞机有限责任公司 配平式的平尾连接结构

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