CN115556917A - Aircraft cargo compartment protection assembly - Google Patents

Aircraft cargo compartment protection assembly Download PDF

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Publication number
CN115556917A
CN115556917A CN202211094154.2A CN202211094154A CN115556917A CN 115556917 A CN115556917 A CN 115556917A CN 202211094154 A CN202211094154 A CN 202211094154A CN 115556917 A CN115556917 A CN 115556917A
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China
Prior art keywords
tab
lug
aircraft
assembly
oblong hole
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熊旭军
赵潇然
陆磊
高宇
黄雨霓
罗泰
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Comac Shanghai Aircraft Design & Research Institute
Commercial Aircraft Corp of China Ltd
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Comac Shanghai Aircraft Design & Research Institute
Commercial Aircraft Corp of China Ltd
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Priority to CN202211094154.2A priority Critical patent/CN115556917A/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/10Bulkheads
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18Floors
    • B64C1/20Floors specially adapted for freight
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16CSHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C11/00Pivots; Pivotal connections
    • F16C11/04Pivotal connections

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Plates (AREA)

Abstract

The present invention provides a fender assembly for use in an aircraft cargo bay, comprising: a plurality of connectors, each connector fixedly attached to an aircraft fuselage structure; a barrage wall movably connected at its top and bottom sides to at least a portion of the plurality of connectors by couplings; wherein each coupling portion comprises: the first lug is arranged on the top side or the bottom side of the arresting wall, and a long round hole extending along the vertical direction is formed in the first lug; a second tab disposed at the connector; the joint bearing is arranged in the second lug plate; and the stud piece penetrates through the joint bearing in the second lug piece and the long round hole of the first lug piece and can move in the long round hole along the vertical direction. The protective component does not participate in the transmission and the carrying of the main structure of the machine body, is easy to assemble and disassemble and has good reliability and maintainability.

Description

飞机货舱防护组件Aircraft cargo compartment protection components

技术领域technical field

本发明涉及飞机拦阻防护装置的技术领域,具体地,本发明涉及一种在飞机货舱中使用的防护组件。The invention relates to the technical field of aircraft blocking protection devices, in particular, the invention relates to a protection assembly used in aircraft cargo compartments.

背景技术Background technique

在民用飞机的常规构造中,电子设备舱(E-E舱)设置在后货舱前面。当飞机发生颠簸或应急着陆事件时,如果未在后货舱前端设置防护装置,则其中的货物可能会由于惯性而冲击货舱前壁,不仅可能造成货舱舱门的堵死与破坏,还可能影响电子设备舱中的配电盘箱等电子设备,造成设备失效风险,严重影响飞行安全。根据适航条款要求,需要在货舱前端设置9g拦阻防护装置,即最高承受沿航向方向的9倍重力过载的拦阻防护装置,以最大程度地降低货物对货舱前壁的冲击,也使得受其影响的电源设备在应急状态下的失效风险最小。同时,为了实现飞机的全生命周期可维护性,还对飞机货舱拦阻防护装置提出了具有可拆卸性的需求,以便于维护货舱前面的电源盘箱设备等电子设备。In conventional configurations of civil aircraft, the electronics bays (E-E bays) are located in front of the aft cargo bay. When the aircraft encounters turbulence or emergency landing, if the protective device is not installed at the front of the rear cargo compartment, the cargo in it may impact the front wall of the cargo compartment due to inertia, which may not only cause blockage and destruction of the cargo compartment door, but may also affect electronic equipment. Electronic equipment such as switchboard boxes in the equipment compartment will cause the risk of equipment failure and seriously affect flight safety. According to the requirements of airworthiness clauses, it is necessary to install a 9g arresting protection device at the front of the cargo hold, that is, an arresting protection device that can withstand up to 9 times the gravity overload along the direction of course, so as to minimize the impact of the cargo on the front wall of the cargo hold, and also make it affected by it. The risk of failure of the power supply equipment in the emergency state is minimal. At the same time, in order to realize the maintainability of the whole life cycle of the aircraft, there is also a requirement for the detachability of the arresting protection device of the aircraft cargo compartment, so as to facilitate the maintenance of electronic equipment such as the power panel equipment in front of the cargo compartment.

现有设计中多采用拦阻网等柔性拦阻防护装置,主要采用若干非金属柔性条带纵横交错形成网体,再使用金属接头将网体固定到飞机机身结构。拦阻网依靠网体条带的弹性变形来实现力的传递与网状结构的运动,即在承受载荷时,网体条带发生线性位移与角位移,从而缓冲货物冲击。但条带的柔性特性导致拦阻网在受到冲击时会发生较大的网体变形,因此需要在货舱门与拦阻网之间设置相对长的缓冲区段,对于小型飞机而言可能造成空间浪费。In existing designs, flexible arresting protection devices such as arresting nets are mostly used, mainly using a number of non-metallic flexible strips criss-crossing to form a net body, and then using metal joints to fix the net body to the aircraft fuselage structure. The arresting net relies on the elastic deformation of the mesh strips to realize the force transmission and the movement of the mesh structure, that is, when the load is applied, the mesh strips undergo linear displacement and angular displacement, thereby buffering the impact of goods. However, the flexible characteristics of the strips lead to a large deformation of the arresting net when it is impacted. Therefore, a relatively long buffer zone needs to be set between the cargo door and the arresting net, which may cause waste of space for small aircraft.

还存在诸如拦阻墙之类的刚性拦阻防护装置,这种装置主要采用刚性金属板材形成墙体,再使用连接件将墙体固定到飞机机身结构。在受到冲击时,拦阻墙经由若干连接件将所受到的载荷分散地传递到飞机机身结构,从而实现力的传递,缓冲货物冲击。与拦阻网相比,拦阻墙的变形程度较小,所需的缓冲区段也较短。但由于拦阻墙会较多地将载荷传递至飞机结构,因此还需要其避免过度约束,以免对机身等结构正常飞行时的传力产生不利影响,即需要设置能够提供一定自由度的连接件。Rigid arresting guards also exist, such as arresting walls, which primarily use rigid sheet metal to form the walls and then use connectors to secure the walls to the aircraft fuselage structure. When impacted, the blocking wall distributes the received load to the aircraft fuselage structure through several connecting pieces, thereby realizing force transmission and cushioning the impact of cargo. Barrier walls deform to a lesser extent and require shorter buffer zones than arresting nets. However, since the blocking wall will transfer more loads to the aircraft structure, it is also necessary to avoid excessive restraint, so as not to have an adverse effect on the force transmission of the fuselage and other structures during normal flight, that is, it is necessary to set up connectors that can provide a certain degree of freedom .

在于2016年12月26日提交,申请号为201611216925.5,题为《一种货舱地板纵梁与拦阻墙连接结构》的中国发明专利申请公布中,提出了一种拦阻墙连接结构,该结构主要通过带有长圆孔的单双耳与关节轴承连接提供一定自由度。当该连接结构随拦阻墙承受航向载荷时,与之连接的货舱地板纵梁在长圆孔内沿该长圆孔的延伸方向平移运动,释放航向载荷;当承受侧向载荷时,连接结构借助关节轴承转动,从而释放侧向载荷,避免地板纵梁随连接结构一起运动而变形;当货舱地板承受垂向载荷时,可通过在双耳片中转动而将垂向载荷传递到拦阻墙。这样的结构利用长圆孔和关节轴承的结构特点满足了沿航向、侧向和垂向的载荷释放和传递需求。但是在受到货物冲击时,拦阻墙所受到的航向载荷远大于侧向和垂向载荷,因此使用该连接结构的地板纵梁会显著冲击长圆孔的端部,长此以往将明显损伤长圆孔周缘,进而降低整个连接件的可靠性,同时较强的冲击力也可能使得与之连接的地板纵梁发生明显变形,对机身传力产生不利影响;其次,该连接件仅通过将地板纵梁与拦阻墙连接在一起而进行固定,传力路径单一,拦阻防护装置参与机身主结构传载,在受到较强冲击时仍可能损伤机身结构。因此,现有技术的拦阻墙及其结构传力路径欠合理,装置可靠性欠佳,仍存在因货物冲击而影响机身结构的问题。Submitted on December 26, 2016, the application number is 201611216925.5. In the publication of the Chinese invention patent application titled "A Connection Structure between Cargo Floor Stringer and Blocking Wall", a connection structure for blocking walls is proposed. The single and double lugs with oblong holes are connected with joint bearings to provide a certain degree of freedom. When the connection structure bears the heading load along with the blocking wall, the cargo floor longitudinal beam connected to it moves in translation along the extension direction of the long hole to release the heading load; when it bears the side load, the connection structure uses joint bearings Rotate to release the lateral load and avoid deformation of the floor stringer moving with the connecting structure; when the cargo hold floor bears a vertical load, the vertical load can be transferred to the blocking wall by rotating in the double lug. Such a structure utilizes the structural characteristics of the oblong hole and the joint bearing to meet the load release and transmission requirements along the course, side and vertical directions. However, when the cargo is impacted, the directional load on the blocking wall is much greater than the lateral and vertical loads. Therefore, the floor stringer using this connection structure will significantly impact the end of the oblong hole, and if things go on like this, it will obviously damage the periphery of the oblong hole. Reduce the reliability of the entire connector, and at the same time, the strong impact force may also cause obvious deformation of the floor stringer connected to it, which will have an adverse effect on the force transmission of the fuselage; secondly, the connector only connects the floor stringer to the blocking wall. They are fixed by being connected together, the force transmission path is single, and the blocking protection device participates in the load transmission of the main structure of the fuselage, which may still damage the fuselage structure when subjected to a strong impact. Therefore, the force transmission path of the arresting wall and its structure in the prior art is unreasonable, the reliability of the device is not good, and there are still problems of affecting the fuselage structure due to the impact of cargo.

因此,需要提出一种改进的飞机货舱防护组件,其能够解决上述现有技术中存在的问题和缺陷。Therefore, it is necessary to propose an improved aircraft cargo compartment protection assembly, which can solve the problems and defects in the above-mentioned prior art.

发明内容Contents of the invention

因此,本发明的目的在于提供一种改进的飞机货舱防护组件,其改进了载荷传递路径,避免防护组件参与机身主结构传载,提升可靠性。Therefore, the object of the present invention is to provide an improved aircraft cargo compartment protection assembly, which improves the load transfer path, prevents the protection assembly from participating in the main structure of the fuselage to carry the load, and improves reliability.

本发明的另一目的在于提供一种可拆卸的飞机货舱防护组件,其易于拆卸和改装,提升维护性。Another object of the present invention is to provide a detachable aircraft cargo compartment protection assembly, which is easy to disassemble and refit, and improves maintainability.

根据本发明,提供了一种在飞机货舱中使用的防护组件,包括:多个连接件,每个所述连接件固定地附接到飞机机身结构;拦阻墙,所述拦阻墙在其顶侧和底侧通过联结部可动地连接到所述多个连接件中的至少一部分;其中,每个所述联结部包括:设置在所述拦阻墙的顶侧或底侧的第一耳片,所述第一耳片中设有沿竖直方向延伸的长圆孔;设置在所述连接件处的第二耳片;关节轴承,所述关节轴承设置在所述第二耳片中;以及栓柱件,所述栓柱件穿设通过所述第二耳片中的关节轴承及所述第一耳片的所述长圆孔,并且能够在所述长圆孔中沿竖直方向运动。这样的构造使得拦阻墙在受到航向载荷时带动第一耳片绕栓柱件转动以释放载荷,避免与之连接的机身结构发生变形;在全机载荷下第二耳片在第一耳片的长圆孔中沿竖直方向平移运动以释放垂向载荷,即释放与拦阻墙连接的机身结构的垂向相对变形;在全机载荷下第二耳片中借助关节轴承在第一耳片中转动以释放侧向载荷,即释放与拦阻墙连接的机身结构的侧向相对变形及转动。由于本公开的防护组件使用第一耳片绕栓柱件转动而不是栓柱件在长圆孔中平移来释放航向载荷,货物对拦阻墙的冲击力被转化为引导第一耳片绕栓柱件转动的力,而非引导栓柱件直接冲击长圆孔端部的力,这使得能够显著降低长圆孔周缘所受到的冲击力,进而降低与拦阻墙连接的机身结构所受到的冲击力,避免其随拦阻墙发生变形;此外,为了维持机身内部空间的稳定性,机身结构设计成使得在受到垂向载荷时所发生的变形微小,因此第二耳片带动栓柱件为释放垂向载荷而在长圆孔中进行的平移运动也微小,不足以对长圆孔端部产生显著冲击力。因此,本公开的防护组件采用的载荷传递路径降低了货物冲击对机身结构的影响,也降低了货物冲击损害防护组件本身的风险,提高了防护组件的可靠性。According to the present invention, there is provided a shielding assembly for use in an aircraft cargo hold, comprising: a plurality of connectors, each of which is fixedly attached to an aircraft fuselage structure; The side and the bottom side are movably connected to at least a portion of the plurality of connectors by joints; wherein each of the joints includes: a first tab disposed on a top side or a bottom side of the barrier wall , the first lug is provided with an oblong hole extending in the vertical direction; the second lug is arranged at the connecting piece; a joint bearing, the joint bearing is arranged in the second lug; and A stud member, the stud member passes through the joint bearing in the second lug and the oblong hole of the first lug, and can move vertically in the oblong hole. Such a structure makes the blocking wall drive the first lug to rotate around the bolt column to release the load when it is subjected to a directional load, so as to avoid deformation of the fuselage structure connected to it; Vertical translational movement in the oblong hole in the vertical direction to release the vertical load, that is, to release the vertical relative deformation of the fuselage structure connected to the blocking wall; Rotate in order to release the lateral load, that is, to release the lateral relative deformation and rotation of the fuselage structure connected to the arresting wall. Since the fencing assembly of the present disclosure uses rotation of the first lug about the stud rather than translation of the stud in the oblong hole to relieve the directional load, the impact force of the cargo against the barrier wall is translated into guiding the first lug around the stud The force of rotation, rather than the force of direct impact of the guide bolt on the end of the oblong hole, makes it possible to significantly reduce the impact force on the periphery of the oblong hole, thereby reducing the impact force on the fuselage structure connected to the blocking wall, avoiding It deforms with the blocking wall; in addition, in order to maintain the stability of the internal space of the fuselage, the fuselage structure is designed so that the deformation that occurs when it is subjected to a vertical load is small, so the second lug drives the bolt to release the vertical load. The translational movement in the oblong hole due to the load is also small, which is not enough to produce a significant impact force on the end of the oblong hole. Therefore, the load transmission path adopted by the protective assembly of the present disclosure reduces the impact of cargo impact on the fuselage structure, reduces the risk of damage to the protective assembly itself due to cargo impact, and improves the reliability of the protective assembly.

根据本公开的再一方面,所述第一耳片为双耳片,所述第二耳片为单耳片,所述单耳片插入到所述双耳片中间的间隙中,并且所述第一耳片与所述第二耳片之间留有可动间隙。该可动间隙预留成使得在受到侧向载荷时足以使单耳片在双耳片的内部空间中随关节轴承转动,从而释放与防护组件连接的机身结构的侧向相对变形和转动。According to still another aspect of the present disclosure, the first ear piece is a double ear piece, the second ear piece is a single ear piece, and the single ear piece is inserted into the gap between the double ear pieces, and the There is a movable gap between the first lug and the second lug. The movable gap is reserved to make the single lug rotate with the joint bearing in the inner space of the double lug when subjected to a lateral load, thereby releasing the lateral relative deformation and rotation of the fuselage structure connected with the protective assembly.

根据本公开的再一方面,所述连接件同时固附到飞机地板的横梁和纵梁。这样的固附设计使得可以将防护组件受到的载荷同时传递到多个飞机机身结构,即对载荷进行分散式传递。与单一式传递相比,分散式传递模式下每个与防护组件相连接的飞机机身结构将承受相对低的载荷,从而进一步避免飞机机身结构受防护组件影响而发生变形,降低对机身传力产生不利影响的风险。According to yet another aspect of the present disclosure, the connector is affixed to both the beam and the stringer of the aircraft floor. Such a fixed attachment design makes it possible to simultaneously transfer the load on the protective component to multiple aircraft fuselage structures, that is, to perform distributed transfer of the load. Compared with the single transfer mode, each aircraft fuselage structure connected to the protective components in the decentralized transfer mode will bear relatively low loads, thereby further avoiding the deformation of the aircraft fuselage structure due to the influence of the protective components and reducing the impact on the fuselage. Risk of adverse effects on force transmission.

根据本公开的再一方面,所述联结部还包括成对衬套,所述成对衬套构造成围绕所述第一耳片的所述长圆孔的周缘并延伸到所述长圆孔内;所述栓柱件包括螺栓和螺母,所述螺栓穿设通过所述第二耳片中的关节轴承及所述第一耳片的所述长圆孔,所述螺母旋拧在所述螺栓的端部。衬套进一步保护长圆孔免受摩擦和撞击的影响,延长防护组件的使用寿命。栓柱件的这种设计使得可以通过旋拧螺母而容易地从连接件移除拦阻墙,从而更换衬套等零部件、或者对拦阻墙或货舱前面的飞机电子设备进行维护。According to still another aspect of the present disclosure, the coupling portion further includes a pair of bushes configured to surround the periphery of the oblong hole of the first lug and extend into the oblong hole; The stud member includes a bolt and a nut, the bolt passes through the joint bearing in the second lug and the oblong hole of the first lug, and the nut is screwed on the end of the bolt department. The bushing further protects the oblong hole from friction and impact, extending the life of the guard assembly. This design of the stud allows the barrier wall to be easily removed from the connector by twisting the nuts to replace components such as bushings or to perform maintenance on the barrier wall or aircraft electronics in front of the cargo bay.

根据本公开的再一方面,所述成对衬套中的每一个呈长圆筒状,并在其一端具有径向向外延伸的凸缘,其中,所述成对衬套选自外径一致,但内径尺寸彼此不同的多对衬套。由于所述衬套插入到第一耳片的长圆孔中,不同内径尺寸的衬套限定不同长短的长圆孔内径,即改变所述防护组件在竖直方向上的自由度。这使得可以根据不同机型对防护组件自由度的需求而对长圆孔尺寸进行调整以获得所需自由度。According to still another aspect of the present disclosure, each of the pair of bushes is in the shape of a long cylinder and has a radially outwardly extending flange at one end thereof, wherein the pair of bushes is selected from the group consisting of , but multiple pairs of bushings with different inner diameter dimensions from each other. Since the bushing is inserted into the oblong hole of the first lug, the bushings with different inner diameters define different lengths of the inner diameter of the oblong hole, that is, the degree of freedom of the protection assembly in the vertical direction is changed. This makes it possible to adjust the size of the oblong hole to obtain the required degree of freedom according to the requirements of different models for the degree of freedom of the protective component.

根据本公开的再一方面,所述拦阻墙还通过辅助联结部连接到多个所述连接件的一部分,所述辅助联结部包括具有圆孔的第三耳片、具有辅助关节轴承的第四耳片以及穿设通过所述辅助关节轴承及所述圆孔的栓柱件。辅助联结部用作保持整个防护组件在飞机正常运行中相对稳定,因为第三耳片中的孔的圆形形状不允许第四耳片带动栓柱件在其中平移运动,从而能够稳固与之连接的拦阻墙,防止整个防护组件沿联结部的长圆孔发生非期望位移。According to still another aspect of the present disclosure, the blocking wall is further connected to a part of the plurality of connecting pieces through an auxiliary coupling part, the auxiliary coupling part comprising a third lug with a circular hole, a fourth lug with an auxiliary joint bearing. The lugs and the pegs pass through the auxiliary joint bearing and the circular hole. The auxiliary joint is used to keep the entire shielding assembly relatively stable in normal operation of the aircraft, because the circular shape of the hole in the third lug does not allow the fourth lug to drive the peg member to translate in it, so that it can be firmly connected to it The blocking wall prevents the undesired displacement of the entire protective assembly along the oblong hole of the joint.

较佳地,所述辅助联结部设置在所述拦阻墙的底侧的中间部分,其中,所述辅助联结部的数量不大于二。Preferably, the auxiliary connecting parts are arranged at the middle part of the bottom side of the blocking wall, wherein the number of the auxiliary connecting parts is not more than two.

根据本公开的再一方面,所述第三耳片为双耳片,所述第四耳片为单耳片,所述单耳片插入到所述双耳片中间的间隙中,并且所述第三耳片与所述第四耳片之间留有可动间隙。According to still another aspect of the present disclosure, the third ear piece is a double ear piece, the fourth ear piece is a single ear piece, and the single ear piece is inserted into the gap between the double ear pieces, and the There is a movable gap between the third lug and the fourth lug.

根据本公开的再一方面,所述拦阻墙包括挡板、多根立柱和多个横向加强件,所述多根立柱竖直地附接到所述挡板,所述横向加强件横向地附接到所述挡板,其中所述第一耳片处于所述立柱的端部;并且其中,所述立柱和所述横向加强件通过托板螺母附接到所述挡板。According to still another aspect of the present disclosure, the barrier wall includes a baffle, a plurality of uprights and a plurality of transverse reinforcements, the plurality of uprights are vertically attached to the baffle, and the transverse reinforcements are laterally attached to the apron, wherein the first tab is at an end of the upright; and wherein the upright and the transverse stiffener are attached to the apron by a bracket nut.

根据本公开的再一方面,所述连接件与所述第二耳片一体成型,并通过紧固件附接到所述飞机机身结构。According to a further aspect of the present disclosure, the connector is integrally formed with the second tab and attached to the aircraft fuselage structure by fasteners.

本公开的防护组件通过竖直设置的长圆孔耳片连接与关节轴承结构,将飞机发生颠簸或应急着陆事件时货物对防护组件的冲击力以及飞机机身结构的相对变形通过在联结部中的旋转或平移运动进行转移和释放,从而避免防护组件和与其连接的飞机机身结构跟随彼此发生变形,实现防护组件不参与机身主结构传载,降低货物冲击对机身结构的影响,或机身结构本身变形对防护组件的影响;此外,通过将连接件同时固附到飞机底板的横梁和纵梁,将防护组件所受到的载荷分散地传递到不同的飞机机身结构,进一步降低承受载荷的飞机机身结构随防护组件变形的风险。此外,本公开的防护组件使用易于拆装的螺栓件将拦阻墙和连接件连接在一起,可以方便地通过旋拧螺母将拦阻墙安装到或移除出固附到机身结构的连接件,从而便于更换防护组件零件、或维护货舱前面的飞机电子设备,提升了飞机的维护性。The protection assembly of the present disclosure is connected to the joint bearing structure through the vertically arranged oblong hole lugs, and the impact force of the cargo on the protection assembly and the relative deformation of the aircraft fuselage structure when the aircraft turbulence or emergency landing event occurs through the joint in the joint part Rotation or translation movement can be transferred and released, so as to prevent the protective components and the aircraft fuselage structure connected to them from deforming with each other, realize that the protective components do not participate in the main structure of the fuselage, and reduce the impact of cargo impact on the fuselage structure. The influence of the deformation of the fuselage structure itself on the protective components; in addition, by attaching the connectors to the beams and longitudinal beams of the aircraft floor at the same time, the loads on the protective components are distributed to different aircraft fuselage structures, further reducing the load bearing The risk of deformation of the aircraft fuselage structure along with the shielding components. In addition, the protective assembly of the present disclosure connects the arresting wall and the connector together with easily disassembled bolts, and the arresting wall can be easily installed or removed from the connector attached to the fuselage structure by screwing the nut, Therefore, it is convenient to replace the protective component parts or maintain the aircraft electronic equipment in front of the cargo compartment, thereby improving the maintainability of the aircraft.

附图说明Description of drawings

为了更完全理解本发明,可参考结合附图来考虑示例性实施例的下述描述。附图并不意在将本发明限制于其所描绘的特定实施例,且不一定是按比例的。附图中:For a more complete understanding of the present invention, the following description of the exemplary embodiments may be considered with reference to the accompanying drawings. The drawings are not intended to limit the invention to the particular embodiments depicted and are not necessarily to scale. In the attached picture:

图1是根据本发明示例性实施例的防护组件的正视图;1 is a front view of a shield assembly according to an exemplary embodiment of the present invention;

图2是图1的防护组件的局部放大视图,示出了根据本发明示例性实施例的联结部;FIG. 2 is a partial enlarged view of the shield assembly of FIG. 1, showing a coupling portion according to an exemplary embodiment of the present invention;

图3是图2的联结部的细节性正视图;Figure 3 is a detailed front view of the joint of Figure 2;

图4是图2的联结部的细节性侧视图;Figure 4 is a detailed side view of the coupling portion of Figure 2;

图5是图2的联结部沿图3中A-A线剖取的剖视图;Fig. 5 is a sectional view taken along the A-A line in Fig. 3 of the coupling portion of Fig. 2;

图6是示出根据本发明示例性实施例的防护组件的连接件与机身结构相连接的示意性视图;FIG. 6 is a schematic view showing that a connector of a protective assembly is connected to a fuselage structure according to an exemplary embodiment of the present invention;

图7是图1的防护组件的局部放大视图,示出了拦阻墙中各部件的连接关系;Fig. 7 is a partially enlarged view of the protective assembly of Fig. 1, showing the connection relationship of the various components in the blocking wall;

图8是根据本发明示例性实施例的防护组件释放航向载荷的运动示意图;Fig. 8 is a schematic diagram of the movement of the protection assembly releasing the directional load according to an exemplary embodiment of the present invention;

图9是根据本发明示例性实施例的防护组件释放垂向载荷的运动示意图;Fig. 9 is a schematic diagram of the movement of the protective assembly releasing the vertical load according to an exemplary embodiment of the present invention;

图10是根据本发明示例性实施例的防护组件释放侧向载荷的运动示意图。Fig. 10 is a schematic diagram of the movement of the protective assembly releasing side loads according to an exemplary embodiment of the present invention.

附图标记列表List of reference signs

100 防护组件100 protective components

1 拦阻墙1 Barrier Wall

11 立柱11 uprights

12 横向加强件12 Lateral reinforcements

13 挡板13 bezel

2 连接件2 connectors

3 联结部3 link

31 第一耳片31 First ear piece

311 长圆孔311 oblong hole

32 第二耳片32 Second ear piece

33 栓柱件33 stud parts

331 螺栓331 Bolt

332 螺母332 Nut

34 关节轴承34 joint bearing

35 衬套35 Bushing

4 托板螺母4 bracket nuts

200 飞机地板200 aircraft floor

201 地板纵梁201 Floor stringers

202 地板横梁202 floor beams

具体实施方式detailed description

下面结合具体实施例和附图对本公开作进一步说明,在以下描述中阐述了更多细节以便于充分理解本公开,但本公开显然能够以多种不同于此描述的其他方式来实施,本领域技术人员可以在不脱离在所附权利要求中限定的范围的情况下,对本公开的实施例进行各种演绎和推广,因此不应以此具体实施例的内容限制本公开的保护范围。在所有附图和具体实施方式中使用相同的附图标记指代相同或相似的部件。The present disclosure will be further described below in conjunction with specific embodiments and accompanying drawings. In the following description, more details are set forth in order to fully understand the present disclosure, but the present disclosure can obviously be implemented in many other ways different from this description. Skilled persons can make various deductions and extensions to the embodiments of the present disclosure without departing from the scope defined in the appended claims, so the content of this specific embodiment should not limit the protection scope of the present disclosure. The same reference numbers are used throughout the drawings and detailed description to refer to the same or like parts.

本文中使用的“航向”、“垂向”、“侧向”等方位术语是基于飞机行进方向而考虑的,沿飞机行进方向为航向方向,在竖直平面内垂直于飞机行进方向的方向为垂向方向,而在水平平面内垂直于飞机行进方向的方向为侧向方向,这三个方向相互正交。The orientation terms such as "heading", "vertical" and "sideways" used in this article are considered based on the direction of travel of the aircraft. The vertical direction, and the direction perpendicular to the direction of travel of the aircraft in the horizontal plane is the lateral direction, and these three directions are mutually orthogonal.

如图1所示,根据本发明较佳实施例的在飞机货舱中使用的防护组件100总体包括拦阻墙1和多个连接件2,其中,拦阻墙1在其顶侧和底侧经由联结部3可动地连接到连接件2中的至少一部分,而每个连接件2固定地附接到诸如飞机地板200之类的飞机机身结构。这样的构造使得防护组件100竖直地布置在飞机货舱内。As shown in FIG. 1 , a protective assembly 100 used in an aircraft cargo compartment according to a preferred embodiment of the present invention generally includes a blocking wall 1 and a plurality of connecting parts 2 , wherein the blocking wall 1 is connected at its top and bottom sides via joints. 3 is movably connected to at least a portion of the linkages 2 , while each linkage 2 is fixedly attached to an aircraft fuselage structure such as an aircraft floor 200 . Such a configuration allows the shield assembly 100 to be arranged vertically in the cargo hold of an aircraft.

如图1和图7所示,拦阻墙1包括多根立柱11、多个横向加强件12以及挡板13,其中,每根立柱11延伸过挡板13的整个高度,并通过托板螺母4竖直地附接到挡板13;而多个横向加强件12通过托板螺母4横向地附接到挡板13,并彼此平行地布置在立柱11之间。在拦阻墙1受到货物冲击时,挡板13将载荷传递至立柱11,再由立柱11将载荷通过连接到拦阻墙顶、底侧的连接件2传递到飞机机身结构。横向加强件12用以辅助支承挡板13,降低挡板13的弯曲应力。As shown in FIGS. 1 and 7 , the blocking wall 1 includes a plurality of uprights 11 , a plurality of transverse reinforcements 12 and a baffle 13 , wherein each upright 11 extends over the entire height of the baffle 13 and passes through the bracket nut 4 vertically attached to the apron 13 ; while a plurality of transverse reinforcements 12 are laterally attached to the apron 13 by means of the bracket nuts 4 and are arranged between the uprights 11 parallel to each other. When the blocking wall 1 is impacted by cargo, the baffle plate 13 transmits the load to the column 11, and then the column 11 transmits the load to the aircraft fuselage structure through the connecting piece 2 connected to the top and bottom of the blocking wall. The transverse reinforcement 12 is used to assist in supporting the baffle 13 and reduce the bending stress of the baffle 13 .

连接件2通过诸如铆钉、普通螺栓或高锁螺栓之类的紧固件固附到飞机机身结构,并在其一端通过联结部3可动地连接到拦阻墙1。处于拦阻墙1顶侧的连接件2附接到飞机客舱地板,而处于拦阻墙1底侧的连接件2附接到飞机货舱地板。在本示例性实施例中,如图6所示,连接件2同时固附到飞机客舱/货舱地板200的地板纵梁201和地板横梁202。具体地,连接件2设置在地板纵梁201与地板横梁202交错形成的网状结构中,并在其侧部固附抵靠地板纵梁201,在其端部固附抵靠相邻的两根地板横梁202。这样的设计使得可以将防护组件100受到的载荷分散地传递到地板横梁与纵梁,即同时传递到多个飞机机身结构,进而使得每个与防护组件100相连接的飞机机身结构将承受相对低的载荷,从而进一步避免飞机机身结构受防护组件影响而发生变形,降低对机身传力产生不利影响的风险。The connecting piece 2 is fixed to the aircraft fuselage structure by fasteners such as rivets, common bolts or high-lock bolts, and is movably connected to the blocking wall 1 at one end thereof through a coupling portion 3 . The connectors 2 on the top side of the arresting wall 1 are attached to the aircraft cabin floor, while the connectors 2 on the bottom side of the arresting wall 1 are attached to the aircraft cargo floor. In this exemplary embodiment, as shown in FIG. 6 , the connector 2 is simultaneously attached to the floor stringers 201 and the floor cross beams 202 of the aircraft cabin/cargo floor 200 . Specifically, the connector 2 is arranged in the network structure formed by interlacing the floor stringers 201 and the floor cross beams 202, and is fixed against the floor stringers 201 at its sides, and is fastened against the adjacent two adjacent beams at its ends. Root floor beam 202. Such a design makes it possible to dispersely transmit the load received by the protective assembly 100 to the floor beams and longitudinal beams, that is, to transmit to multiple aircraft fuselage structures at the same time, so that each aircraft fuselage structure connected with the protective assembly 100 will bear Relatively low load, so as to further avoid the deformation of the aircraft fuselage structure due to the influence of the protective components, and reduce the risk of adverse effects on the force transmission of the fuselage.

联结部3将拦阻墙1和连接件2连接在一起,联结部3允许关联部件相对运动从而释放载荷。如图2至图5所示,联结部3包括:设置在拦阻墙1的顶侧或底侧的第一耳片31,该第一耳片31中设有沿竖直方向延伸的长圆孔311,在本示例性实施例中,第一耳片31为双耳片,并处于拦阻墙1的立柱11的上端部或下端部;设置在连接件2处的第二耳片32,在本示例性实施例中,第二耳片32为与连接件2成一体的单耳片,并插入到第一耳片31中间的空隙中,并且第一耳片31与第二耳片32之间留有可动间隙;设置在第二耳片32中的关节轴承34;栓柱件33,该栓柱件33包括螺栓331和螺母332,螺栓331在其一端形成径向向外延伸的凸缘,并穿设通过第二耳片32中的关节轴承34与第一耳片31的长圆孔311,螺母332旋拧在螺栓331的另一端,使得栓柱件33能够带动第二耳片32在第一耳片31的长圆孔311中沿竖直方向运动而不脱出第一耳片31。可动间隙的设置允许第二耳片32能够借助关节轴承34在第一耳片31内转动,从而释放侧向载荷。而可拆卸的螺栓螺母设计使得能够容易地将拦阻墙1安装到或移除出连接件2,从而方便地更换或维护零部件。The coupling part 3 connects the blocking wall 1 and the connecting part 2 together, and the coupling part 3 allows the relative movement of the related parts to release the load. As shown in Figures 2 to 5, the coupling part 3 includes: a first lug 31 arranged on the top side or bottom side of the blocking wall 1, and the first lug 31 is provided with an oblong hole 311 extending vertically , in this exemplary embodiment, the first lug 31 is a double lug, and is located at the upper end or lower end of the column 11 of the blocking wall 1; the second lug 32 provided at the connecting piece 2, in this example In a preferred embodiment, the second ear piece 32 is a single ear piece integrated with the connector 2, and is inserted into the gap in the middle of the first ear piece 31, and there is a gap between the first ear piece 31 and the second ear piece 32. There is a movable gap; the joint bearing 34 arranged in the second lug 32; the stud member 33, the stud member 33 includes a bolt 331 and a nut 332, and the bolt 331 forms a radially outwardly extending flange at one end thereof, And pass through the joint bearing 34 in the second lug 32 and the oblong hole 311 of the first lug 31, the nut 332 is screwed on the other end of the bolt 331, so that the bolt 33 can drive the second lug 32 on the second lug 32. The oblong hole 311 of one ear piece 31 moves vertically without coming out of the first ear piece 31 . The setting of the movable gap allows the second lug 32 to rotate in the first lug 31 by means of the joint bearing 34, thereby releasing the lateral load. The design of detachable bolts and nuts makes it easy to install or remove the blocking wall 1 to or from the connecting piece 2, so that parts can be replaced or maintained conveniently.

此外,联结部3还包括成对衬套35,该成对衬套35构造成在第一耳片31的两侧外部围绕第一耳片31的长圆孔311的周缘并延伸到长圆孔311内,螺栓331的凸缘和螺母332分别经由垫片压抵成对衬套35。成对衬套35中的每一个呈长圆筒状,并在其一端具有径向向外延伸的凸缘,其可以保护长圆孔311免于直接承受栓柱件33的摩擦和撞击,从而降低长圆孔的受损风险,延长部件使用寿命。In addition, the coupling part 3 also includes a pair of bushings 35 configured to surround the circumference of the oblong hole 311 of the first lug 31 on both sides of the first lug 31 and extend into the oblong hole 311. , the flanges of the bolts 331 and the nuts 332 are pressed against the pair of bushes 35 via washers, respectively. Each of the pair of bushings 35 is in the shape of a long cylinder, and has a radially outwardly extending flange at one end thereof, which can protect the oblong hole 311 from directly bearing the friction and impact of the bolt 33, thereby reducing the oblong hole. The risk of damage to the hole is eliminated and the service life of the components is extended.

联结部3使得拦阻墙1在受到航向载荷时带动第一耳片31绕栓柱件33转动以释放载荷;在全机载荷下第二耳片32在长圆孔311中沿竖直方向平移运动以释放与防护组件100连接的机身结构的垂向相对变形,避免防护组件100随之变形;在全机载荷下第二耳片32通过处于其中的关节轴承34在第一耳片31中转动以释放与防护组件100连接的机身结构的侧向相对变形及转动,避免防护组件100随之变形。根据本公开,货物对拦阻墙1的冲击力被转化为引导第一耳片31绕栓柱件33转动的力,这使得长圆孔311周缘直接受到的冲击力较小,同时也使得经由连接件2传递到飞机机身结构的冲击力也较小,从而降低机身结构随拦阻墙1发生变形的风险;此外,为了维持机身内部空间的稳定性,飞机机身结构通常设计成使得在受到垂向载荷时所发生的变形微小,因此第二耳片32为释放垂向载荷而在长圆孔311中进行的平移运动也微小,不足以对长圆孔311端部产生显著冲击力。因此,本公开的防护组件所采用的载荷传递路径降低了货物冲击对机身结构的影响,同时也降低了导致拦阻墙1形变或飞机机身结构形变的载荷损害防护组件100本身的风险,提高了防护组件的可靠性。The coupling part 3 makes the blocking wall 1 drive the first lug 31 to rotate around the bolt column 33 to release the load when receiving the directional load; the second lug 32 translates vertically in the oblong hole 311 to Release the vertical relative deformation of the fuselage structure connected with the protective assembly 100, avoiding the subsequent deformation of the protective assembly 100; under the full machine load, the second lug 32 rotates in the first lug 31 through the joint bearing 34 in it to Release the lateral relative deformation and rotation of the fuselage structure connected to the shielding component 100 to avoid the consequent deformation of the shielding component 100 . According to the present disclosure, the impact force of the goods on the barrier wall 1 is converted into a force that guides the first lug 31 to rotate around the bolt 33, which makes the impact force directly received by the periphery of the oblong hole 311 smaller, and also makes the impact force through the connecting piece 2 The impact force transmitted to the fuselage structure of the aircraft is also small, thereby reducing the risk of deformation of the fuselage structure along with the arresting wall 1; in addition, in order to maintain the stability of the internal space of the fuselage, the fuselage structure of the aircraft is usually designed so that it will The deformation of the oblong hole 311 is small because of the slight deformation of the second lug 32 to release the vertical load, which is not enough to produce a significant impact force on the end of the oblong hole 311 . Therefore, the load transfer path adopted by the protective assembly of the present disclosure reduces the impact of cargo impact on the fuselage structure, and also reduces the risk of damage to the protective assembly 100 itself due to loads that cause deformation of the arresting wall 1 or deformation of the aircraft fuselage structure. The reliability of the protective components is improved.

在实际操作中,每型飞机对防护组件100具有不同的自由度需求。例如,大型飞机的载货量大,飞机机身结构的形变也相对较大,其要求防护组件100有较大的自由度,在此情况下为长圆孔尺寸较大,以使得能够通过栓柱件33和第二耳片32在第一耳片31的长圆孔311内的平移及旋转运动充分释放载荷。然而,小型飞机相较大型飞机而言载货量小,由于其内部空间较小、载重较少,飞机机身结构在受到载荷时的形变也相对较小,此时其并不要求防护组件100有较大的自由度。相反,如果自由度太大,即长圆孔尺寸太大,则会造成在释放航向载荷时栓柱件在长圆孔内相对旋转的同时也会平移较长的距离,从而导致其在到达长圆孔周缘时带有相对高的移动速度,反而对长圆孔周缘造成冲击。因此,本发明的防护组件较佳地包括外径一致,但内径尺寸彼此不同的多对衬套,以根据不同飞机对防护组件100的自由度需求选择不同尺寸的成对衬套,并将其安装到枢转部3,以对长圆孔311的内径尺寸进行调整。In actual operation, each type of aircraft has different requirements on the degree of freedom of the protective assembly 100 . For example, a large aircraft has a large cargo capacity, and the deformation of the aircraft fuselage structure is also relatively large, which requires the protection assembly 100 to have a large degree of freedom. The translational and rotational movements of the member 33 and the second lug 32 in the oblong hole 311 of the first lug 31 fully release the load. However, compared with larger aircrafts, small aircrafts have a smaller cargo capacity. Due to their smaller internal space and less load, the deformation of the aircraft fuselage structure is relatively small when subjected to loads. At this time, it does not require protective components 100 There are greater degrees of freedom. On the contrary, if the degree of freedom is too large, that is, the size of the oblong hole is too large, it will cause the peg to rotate relatively in the oblong hole when the yaw load is released, and it will also translate a long distance, which will cause it to reach the periphery of the oblong hole. With a relatively high moving speed, it impacts on the periphery of the oblong hole instead. Therefore, the protective assembly of the present invention preferably includes multiple pairs of bushes with the same outer diameter but different inner diameters, so as to select pairs of bushes with different sizes according to the freedom requirements of different aircraft for the protective assembly 100, and combine them Installed to the pivoting part 3 to adjust the inner diameter of the oblong hole 311 .

如果所有拦阻墙1仅通过联结部3连接到连接件2,即所有立柱11都通过带有沿竖直方向延伸的长圆孔的双耳片连接到连接件2,则处于拦阻墙1顶侧和底侧的长圆孔的存在使得整个拦阻墙1能够沿长圆孔的延伸方向平移。即使在飞机正常运行期间,拦阻墙1也可能上下振动,这无益于保持整体结构稳定。因此,需要消除这种非期望振动。因此附加地,防护组件100还包括辅助联结部,该辅助联结部处于拦阻墙1底侧,较佳地设置在如图1所示的拦阻墙1的中间立柱11的下端,其数量不多于2。辅助联结部的结构与联结部3相似,二者的区别之处仅在于辅助联结部的第三耳片(双耳片)中的孔为圆孔。该孔的这种圆形形状不允许栓柱件带动第四耳片(单耳片)在其中进行平移运动,从而将拦阻墙1限定在相对固定的位置,消除其在飞机正常运行期间的非期望振动。与联结部3相同,辅助联结部的第三耳片处于立柱11的端部,第四耳片与连接件2一体成型。If all blocking walls 1 are connected to connectors 2 only through joints 3, that is, all columns 11 are connected to connectors 2 by double lugs with oblong holes extending vertically, then the top side of blocking wall 1 and the The existence of the oblong hole on the bottom side enables the entire barrier wall 1 to translate along the extending direction of the oblong hole. Even during normal operation of the aircraft, the arresting wall 1 may vibrate up and down, which is not conducive to maintaining the stability of the overall structure. Therefore, there is a need to eliminate such undesired vibrations. Therefore, additionally, the protection assembly 100 also includes an auxiliary coupling part, which is located at the bottom side of the blocking wall 1, preferably arranged at the lower end of the middle column 11 of the blocking wall 1 as shown in FIG. 1, and its number is no more than 2. The structure of the auxiliary coupling part is similar to that of the coupling part 3, the only difference between the two is that the hole in the third lug (two lugs) of the auxiliary coupling part is a round hole. This circular shape of the hole does not allow the bolt to drive the fourth lug (single lug) to carry out translational movement therein, thereby limiting the blocking wall 1 to a relatively fixed position, eliminating its abnormality during normal operation of the aircraft. Expect vibrations. Same as the coupling part 3 , the third lug of the auxiliary coupling part is located at the end of the column 11 , and the fourth lug is integrally formed with the connecting part 2 .

图8至图10示出了防护组件100在受到航向载荷、垂向载荷及侧向载荷时如何通过旋转和平移运动对载荷进行转移和释放。8 to 10 illustrate how the shield assembly 100 transfers and releases loads through rotational and translational motions when subject to yaw loads, vertical loads, and side loads.

如图8所示,在飞机减速或进行应急着陆时,货物会因惯性而冲击拦阻墙1,产生航向载荷。该航向载荷沿图中空心箭头所示方向施加到拦阻墙1上。此时,挡板13沿航向方向弯曲,立柱11随之弯曲,使得立柱11两端的耳片绕栓柱件沿图中实心箭头所示的方向转动,从而将航向载荷部分地转移到连接件2,进而转移到与连接件2连接的地板200的地板纵梁201与地板横梁202。As shown in Fig. 8, when the aircraft decelerates or performs an emergency landing, the cargo will impact the blocking wall 1 due to inertia, resulting in a directional load. The heading load is applied to the arresting wall 1 along the direction indicated by the hollow arrow in the figure. At this time, the baffle plate 13 bends along the direction of the course, and the upright post 11 bends accordingly, so that the lugs at both ends of the upright post 11 rotate around the bolt part in the direction indicated by the solid arrow in the figure, thereby partially transferring the course load to the connecting part 2 , and then transferred to the floor stringer 201 and the floor cross beam 202 of the floor 200 connected with the connector 2 .

如图9所示,在货物随机身颠簸而进行上下震动时,会产生垂向载荷。该垂向载荷沿图中空心箭头所示方向施加到飞机机身结构,引起飞机货舱地板与客舱地板结构的垂向相对变形。此时,栓柱件33带动第二耳片32沿图中实心箭头所示方向在第一耳片31的长圆孔311中平移运动,释放飞机货舱地板与客舱地板结构的垂向相对变形,即通过长圆孔提供的垂向自由度避免拦阻墙1随飞机地板结构的变形而弯曲变形。当拦阻墙1自身产生垂向变形时反之亦然,可以通过第一耳片31与第二耳片32的相对运动释放该变形,避免飞机地板结构随拦阻墙的变形而变形。As shown in Figure 9, when the cargo vibrates up and down due to body bumps, a vertical load will be generated. The vertical load is applied to the aircraft fuselage structure in the direction indicated by the hollow arrow in the figure, causing the vertical relative deformation of the aircraft cargo floor and passenger cabin floor structures. At this time, the peg piece 33 drives the second lug 32 to move in translation in the oblong hole 311 of the first lug 31 along the direction shown by the solid arrow in the figure, releasing the vertical relative deformation of the aircraft cargo floor and the cabin floor structure, that is The vertical freedom provided by the oblong hole prevents the arresting wall 1 from being bent and deformed with the deformation of the aircraft floor structure. When the blocking wall 1 itself undergoes vertical deformation, and vice versa, the deformation can be released through the relative movement of the first lug 31 and the second lug 32, so as to avoid deformation of the aircraft floor structure along with the deformation of the blocking wall.

如图10所示,在飞机倾斜或转弯时,会产生侧向载荷。该侧向载荷沿图中空心箭头所示方向施加到飞机机身结构,引起飞机货舱地板与客舱地板结构的侧向相对变形。此时,机身结构带动连接件2倾斜,连接件2带动与之一体成型的单耳片借助关节轴承沿图中实心箭头所示的旋转方向在双耳片中转动,释放飞机货舱地板与客舱地板结构的侧向相对变形,即通过长圆孔提供的侧向自由度避免拦阻墙1随飞机地板结构的变形而弯曲变形。当货物倾斜地冲击拦阻墙1而产生侧向载荷时,反之亦然,可以避免侧向载荷传递到与防护组件100连接的飞机机身结构,从而防止其随拦阻墙1变形而变形。As shown in Figure 10, side loads are generated when the aircraft is banked or turned. The side load is applied to the aircraft fuselage structure in the direction indicated by the hollow arrow in the figure, causing the lateral relative deformation of the aircraft cargo floor and passenger cabin floor structures. At this time, the fuselage structure drives the connecting piece 2 to tilt, and the connecting piece 2 drives the integrally formed single lug to rotate in the double lug along the rotation direction shown by the solid arrow in the figure by means of the joint bearing, releasing the aircraft cargo floor and the passenger cabin. The lateral relative deformation of the floor structure, that is, the lateral freedom provided by the oblong hole prevents the arresting wall 1 from bending and deforming with the deformation of the aircraft floor structure. When cargo obliquely impacts the blocking wall 1 to generate side load, and vice versa, it can prevent the side load from being transmitted to the aircraft fuselage structure connected with the shielding assembly 100 , thereby preventing its deformation with the deformation of the blocking wall 1 .

因此,根据本公开的拦阻墙1不参与飞机机身主结构传载,机身结构的变形不引起拦阻墙1的变形,从而避免拦阻墙1对机身本体结构的过度约束;拦阻墙1所传递给机身结构的载荷也经由合理的传力路径而得到分散,不会对机身主结构产生显著影响。Therefore, according to the present disclosure, the arresting wall 1 does not participate in the load transmission of the main structure of the aircraft fuselage, and the deformation of the fuselage structure does not cause the deformation of the arresting wall 1, thereby avoiding the excessive restraint of the arresting wall 1 on the fuselage body structure; The load transmitted to the fuselage structure is also dispersed through a reasonable force transmission path, which will not have a significant impact on the main structure of the fuselage.

本发明的防护组件通过设置改进的连接件与可动联结部,实现了创新性的防护组件不参与机身主结构传载的设计,有效避免了正常飞行时防护组件对机身本体结构的过度约束,反之也避免了防护组件的形变对飞机机身结构产生过度影响,提升了拦阻防护装置的可靠性,解决了现有技术中由于传力路径欠佳而使得防护组件所传递的载荷影响机身本体结构的问题。此外,由于联结部采用可拆卸的构造,使得能够容易地装拆拦阻墙,提升了拦阻防护装置及飞机本体的维护性,满足了现有技术对维护性的需求。附加地,还借助采用不同尺寸的衬套来实现联结部内长圆孔的尺寸调整,进而调整防护组件的自由度,以满足不同飞机对拦阻防护装置自由度的不同需求,提升了防护组件的通用性。The protection assembly of the present invention realizes the innovative design that the protection assembly does not participate in the load transmission of the main structure of the fuselage by setting improved connectors and movable joints, effectively avoiding the excessive impact of the protection assembly on the fuselage body structure during normal flight. On the contrary, it also avoids the excessive influence of the deformation of the protective component on the aircraft fuselage structure, improves the reliability of the blocking protective device, and solves the problem of the influence of the load transmitted by the protective component due to the poor force transmission path in the prior art. Problems with body structure. In addition, since the coupling part adopts a detachable structure, the blocking wall can be easily assembled and disassembled, which improves the maintainability of the blocking protection device and the aircraft body, and satisfies the maintenance requirements of the prior art. In addition, the size adjustment of the oblong hole in the coupling part is realized by using bushes of different sizes, and then the degree of freedom of the protective component is adjusted to meet the different requirements of different aircraft for the degree of freedom of the blocking protective device, which improves the versatility of the protective component .

本发明并不局限于上述实施例,上述实施例仅仅是示意性的而非限制性的。本领域技术人员在本发明的启示下,在不脱离本发明宗旨和权利要求所保护的范围情况下,可以做出任何可能的变动和修改。因此,凡是未脱离本发明技术方案的内容,依据本发明的技术实质对上述实施例所作的任何修改、等同变化及修饰,均落入本发明权利要求所界定的保护范围之内。The present invention is not limited to the above-mentioned embodiments, which are only illustrative and non-restrictive. Under the enlightenment of the present invention, those skilled in the art can make any possible changes and modifications without departing from the gist of the present invention and the scope of protection of the claims. Therefore, any modifications, equivalent changes and modifications made to the above-mentioned embodiments according to the technical essence of the present invention shall fall within the scope of protection defined by the claims of the present invention.

Claims (10)

1. A fender assembly for use in an aircraft cargo bay comprising:
a plurality of connectors, each of the connectors fixedly attached to an aircraft fuselage structure;
a barrage wall movably connected at its top and bottom sides to at least a portion of the plurality of connectors by couplings;
wherein each of the links includes:
the first lug is arranged on the top side or the bottom side of the arresting wall, and a long round hole extending along the vertical direction is formed in the first lug;
a second tab disposed at the connector;
a knuckle bearing disposed in the second tab; and
a stud member passing through a joint bearing in the second tab and the oblong hole of the first tab and movable in a vertical direction in the oblong hole.
2. The shield assembly of claim 1 wherein the first tab is a double tab and the second tab is a single tab, the single tab is inserted into a gap in the middle of the double tab, and a movable gap is left between the first tab and the second tab.
3. The fender assembly of claim 1, wherein the connector is affixed to both a cross member and a longitudinal member of an aircraft floor.
4. The shield assembly of claim 1, wherein the coupling further comprises a pair of bushings, each of the pair of bushings configured to surround a periphery of the oblong hole of the first tab and extend into the oblong hole; the bolt piece comprises a bolt and a nut, the bolt penetrates through a joint bearing in the second lug piece and the long round hole of the first lug piece, and the nut is screwed at the end of the bolt.
5. The shield assembly of claim 4 wherein each of said pair of bushings is elongated cylindrical in shape and has a radially outwardly extending flange at one end thereof, wherein said pair of bushings is selected from a plurality of pairs of bushings having a uniform outer diameter but different inner diameter dimensions from one another.
6. The fender assembly of claim 1, wherein the barricade is further connected to a portion of the plurality of connectors by an auxiliary coupling, the auxiliary coupling comprising a third tab having a circular aperture, a fourth tab having an auxiliary knuckle bearing, and a stud member passing through the auxiliary knuckle bearing and the circular aperture.
7. The fender assembly of claim 6, wherein the auxiliary couplings are disposed at a medial portion of the underside of the barrier wall, and wherein the number of auxiliary couplings is no greater than two.
8. The shield assembly of claim 6, wherein the third tab is a double tab and the fourth tab is a single tab, the single tab is inserted into a gap in the middle of the double tab, and a movable gap is left between the third tab and the fourth tab.
9. The fender assembly of claim 1, wherein the barricade comprises a fender, a plurality of posts vertically attached to the fender, and a plurality of transverse stiffeners transversely attached to the fender,
wherein the first tab is at an end of the post;
and wherein the upright and the transverse stiffener are attached to the baffle by a pallet nut.
10. The fender assembly of claim 1, wherein the connector is integrally formed with the second tab and attached to the aircraft fuselage structure by a fastener.
CN202211094154.2A 2022-09-08 2022-09-08 Aircraft cargo compartment protection assembly Pending CN115556917A (en)

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CN113734415A (en) * 2020-05-15 2021-12-03 中航西飞民用飞机有限责任公司 Aircraft cargo hold arresting net structure and design method
CN114735193A (en) * 2022-04-19 2022-07-12 中国商用飞机有限责任公司 Block wall and fuselage flexible connection structure and aircraft

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101663198A (en) * 2007-03-13 2010-03-03 泰莱尔国际有限公司 The net arrangement and the adaptor union thereof of the cargo hold in a kind of especially aircraft
US20130092793A1 (en) * 2010-04-09 2013-04-18 Premium Aerotec Gmbh Aircraft, and fastening arrangement for a floor structure in an aircraft
RU2012101869A (en) * 2012-01-20 2013-07-27 Открытое Акционерное Общество "Научно-Производственная Корпорация "Иркут" CARGO AIRCRAFT SECURITY DEVICE
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