CN211543861U - Load diffusion piece connected with wing spar - Google Patents

Load diffusion piece connected with wing spar Download PDF

Info

Publication number
CN211543861U
CN211543861U CN201922301849.3U CN201922301849U CN211543861U CN 211543861 U CN211543861 U CN 211543861U CN 201922301849 U CN201922301849 U CN 201922301849U CN 211543861 U CN211543861 U CN 211543861U
Authority
CN
China
Prior art keywords
diffusion piece
load
diffuser element
side face
diffuser
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201922301849.3U
Other languages
Chinese (zh)
Inventor
党敏
余明
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xian Aircraft Design and Research Institute of AVIC
Original Assignee
Xian Aircraft Design and Research Institute of AVIC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Xian Aircraft Design and Research Institute of AVIC filed Critical Xian Aircraft Design and Research Institute of AVIC
Priority to CN201922301849.3U priority Critical patent/CN211543861U/en
Application granted granted Critical
Publication of CN211543861U publication Critical patent/CN211543861U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Toys (AREA)

Abstract

The utility model belongs to the field of airplane structure design, in particular to a load diffusion piece connected with a wing spar; comprises a diffusion piece a (3) and a diffusion piece b (4); the right side face of the diffusion piece a (3), the wing ribs (5) and the left side face of the diffusion piece b (4) are fixedly connected through bolts, the left side face of the diffusion piece a (3) is fixedly connected with the back beam (2), the right side face of the diffusion piece b (4) is fixedly connected with the back beam (2), and the cross section of the formed assembly is triangular. Under the conditions of limited structural space and constrained size and position, the load diffusion piece is designed into a triangular assembly, two ends of the triangle are connected with the beam and the suspension support arm, and the other end of the triangle is connected with the rib; the diffuser web is perforated and stiffened for weight reduction. The form diffuser connects the suspension support arms, beams, wall plates and ribs, and effectively ensures the effective transfer of load to the wall plates and the ribs. The design has high force transmission efficiency and light weight, and meets the assembly requirement.

Description

Load diffusion piece connected with wing spar
Technical Field
The utility model belongs to aircraft structural design field, concretely relates to load diffusion spare of being connected with wing spar.
Background
The airplane is provided with flaperon hanging arms which are generally connected with wing back beams, and the back beams need to be locally reinforced for diffusing the concentrated load, such as adding a diffusion angle box on the inner side of the beams or connecting with inner ribs of box sections. However, the size of some suspension arms is large, the span is large, and the size of the diffusion piece of the beam needs to be correspondingly increased, so that the number of parts is increased, and the weight is increased more.
Disclosure of Invention
The utility model aims at: on the premise of meeting the requirement of diffusion concentrated load, the structure form is optimized, and the structure weight is reduced.
The technical scheme of the utility model: a load diffuser for connection to a wing spar, comprising diffuser a3, diffuser b 4; the right side of the diffuser a3, the wing rib 5 and the left side of the diffuser b4 are fixedly connected through bolts, the left side of the diffuser a3 is fixedly connected with the back beam 2, the right side of the diffuser b4 is fixedly connected with the back beam 2, and the cross section of the formed assembly is triangular.
The diffuser a3 and the diffuser b4 are plate-shaped structures, and a rectangular hole is arranged in the middle.
The upper and lower ends of the rectangular holes of the diffusing piece a3 and the diffusing piece b (4) are respectively provided with a rectangular groove.
One corner of the right side surface of the diffusing piece a3 and the right side surface of the diffusing piece b4 is a trapezoidal surface.
Reinforcing ribs are added in the vertical direction of the sides of the rectangular holes in the middle of the diffusing pieces a3 and b 4.
The reinforcing ribs are near the end where the diffusing pieces a3 and b4 are connected to the rib 5.
The utility model has the advantages that: under the conditions of limited structural space and constrained size and position, the load diffusion piece is designed into a triangular assembly, two ends of the triangle are connected with the beam and the suspension support arm, and the other end of the triangle is connected with the rib; the diffuser web is perforated and stiffened for weight reduction. The form diffuser connects the suspension support arms, beams, wall plates and ribs, and effectively ensures the effective transfer of load to the wall plates and the ribs. The design has high force transmission efficiency and light weight, and meets the assembly requirement.
Drawings
FIG. 1 is a schematic view of the structure of the present invention
FIG. 2 is a schematic view of the assembly state of the present invention
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1 and 2, a load diffuser for connection to a wing spar includes diffuser a3, diffuser b 4; the right side of the diffuser a3, the wing rib 5 and the left side of the diffuser b4 are fixedly connected through bolts, the left side of the diffuser a3 is fixedly connected with the back beam 2, the right side of the diffuser b4 is fixedly connected with the back beam 2, and the cross section of the formed assembly is triangular. The diffusing piece a3 and the diffusing piece b4 are of plate-shaped structures, the middle of the diffusing piece a3 and the diffusing piece b4 is provided with a rectangular hole, four walls form four surfaces, and the upper end and the lower end of the rectangular hole in the middle are respectively provided with a rectangular groove for transmitting the load of the suspension arm 1; one corner of the right side surface of the diffusion piece a3 and the right side surface of the diffusion piece b4 is a trapezoidal surface, so that the connection of the right side surface of the diffusion piece a3, the wing rib 5 and the diffusion piece b4 is more attached; reinforcing ribs are added in the vertical direction of the sides of the rectangular holes in the middle of the diffusion pieces a3 and b4, and the reinforcing ribs are close to one ends, connected with the ribs 5, of the diffusion pieces a3 and b 4.

Claims (6)

1. A load diffuser element for connection to a wing spar, comprising a diffuser element a (3), a diffuser element b (4); the right side face of the diffusion piece a (3), the wing ribs (5) and the left side face of the diffusion piece b (4) are fixedly connected through bolts, the left side face of the diffusion piece a (3) is fixedly connected with the back beam (2), the right side face of the diffusion piece b (4) is fixedly connected with the back beam (2), and the cross section of the formed assembly is triangular.
2. A load diffuser element for connection to a wing spar as claimed in claim 1, wherein the diffuser elements a (3) and b (4) are of plate-like configuration with a rectangular aperture in the middle.
3. A load diffuser element for attachment to a wing spar as claimed in claim 1, wherein the rectangular holes in the diffuser element a (3) and diffuser element b (4) each have a rectangular slot at each of their upper and lower ends.
4. A load diffuser element for connection to a wing spar as claimed in claim 1, wherein the right side of diffuser element a (3) and the right side of diffuser element b (4) are trapezoidal in shape at one corner.
5. A load diffuser element for attachment to a wing spar as claimed in claim 1, wherein stiffeners are added to the diffuser element a (3) and diffuser element b (4) perpendicular to the sides of the rectangular hole in the middle.
6. A load diffuser element for connection to a wing spar as claimed in claim 5, wherein the stiffener is located adjacent the end of the diffuser element a (3) and diffuser element b (4) to which the rib (5) is connected.
CN201922301849.3U 2019-12-19 2019-12-19 Load diffusion piece connected with wing spar Active CN211543861U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201922301849.3U CN211543861U (en) 2019-12-19 2019-12-19 Load diffusion piece connected with wing spar

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201922301849.3U CN211543861U (en) 2019-12-19 2019-12-19 Load diffusion piece connected with wing spar

Publications (1)

Publication Number Publication Date
CN211543861U true CN211543861U (en) 2020-09-22

Family

ID=72507425

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201922301849.3U Active CN211543861U (en) 2019-12-19 2019-12-19 Load diffusion piece connected with wing spar

Country Status (1)

Country Link
CN (1) CN211543861U (en)

Similar Documents

Publication Publication Date Title
CN201713963U (en) Replaceable connecting beam
CN212951088U (en) Unmanned aerial vehicle outer wing that contains whole oil tank
CN216787448U (en) Assembled steel-wood truss steel web member and wood chord steel connected node
CN211543861U (en) Load diffusion piece connected with wing spar
CN110654072A (en) Shearing reinforced honeycomb plate
EP3118387A1 (en) Solar roof tile and solar roof tile system
CN218624493U (en) Modular wind power blade connecting structure
CN109208784A (en) Shear wall
CN211918977U (en) Load diffusion joint connected with wing spar
CN208037888U (en) A kind of superpower boom system of multi-arm frame with mapping function
CN216003090U (en) Engine back support structure and airplane
CN203188120U (en) Main girder structure of truss type bridge girder erection machine and trussed type bridge girder erection machine
CN212401540U (en) Aircraft body and rotor craft thereof
CN112606998B (en) Aircraft aileron composite material integral joint
CN113250318A (en) Modularization steel frame connection structure
CN206750115U (en) A kind of outer hanging joint of wing
CN211567133U (en) Shearing reinforced honeycomb plate
CN113581476A (en) Engine back support structure and airplane
CN103434636B (en) Fuselage butt joint structure for connecting aircraft vertical tails and aircraft comprising fuselage butt joint structure
CN211223837U (en) Aircraft wing box structure
CN116104688B (en) Two-section wind power blade connection structure
CN219927953U (en) Composite material wing type sail internal steel frame structure
CN220233435U (en) Antenna mounting bracket for mounting multiple large antennas
CN103466079A (en) Manipulation and suspension coupled support arm component of airplane tail fin
CN217420237U (en) Steel constructs roof beam

Legal Events

Date Code Title Description
GR01 Patent grant
GR01 Patent grant