Abstract

Disclosed are an aircraft engine suspension and a suspension box section (100) thereof. The suspension box section (100) comprises: a body; and a suspension-engine connection part and a suspension-wing connection part formed in the body. An engine of an aircraft is connected to the suspension box section (100) through the suspension-engine connection part. The suspension box section (100) is connected to a wing or a fuselage of the aircraft through the suspension-wing connection part. The body of the suspension box section comprises: an upper wall plate (120), a bottom plate and side wall plates (130). The bottom plate is arranged to be opposite to the upper wall plate (120); and the side wall plates (130) are connected between the upper wall plate (120) and the bottom plate, wherein the upper wall plate (120) is composed of at least two plate portions and is formed into a raised structure.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 27/06 - Aircraft characterised by the type or position of power plants of piston type within, or attached to, wings

Abstract

A coupling device for inner and outer flaps, comprising: a piston cylinder assembly (2); a piston rod assembly (1), which is provided in the piston cylinder assembly and is radially fixed and axially movable relative to the piston cylinder assembly; an arc-shaped wedge member (3), which is fixed to the outer side of the piston cylinder assembly and comprises a first wedge squeezing surface (7); a concave ring (4), which is fixed to the outer side of the piston rod assembly and comprises a second wedge squeezing surface (8). When the first wedge squeezing surface is in contact with the second wedge squeezing surface, an axial force is generated, realizing forward buffering. The coupling device for the inner and outer flaps can realize an overtravel forward buffering function and is simple in structure and easy to mount and maintain.

IPC Classes  ?

• B64C 9/26 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps

Abstract

The present invention relates to a pixel subdivision load transfer method and system. The pixel subdivision load transfer method comprises: obtaining surface pressure distribution data, the data being in the form of surface elements and corresponding pressure; subdividing surface element pixels into subdivision surface elements which are small enough; allocating the subdivision surface elements to corresponding structure bearing points; integrating the subdivision surface elements allocated to the same structure bearing point into concentrated force and moment, and transferring the concentrated force and moment to the structure bearing point; comparing load distribution before the transfer with load distribution after the transfer to obtain a difference, and determining whether the difference is less than given tolerance; if the difference is less than the given tolerance, obtaining a final load; and if the difference is greater than or equal to the given tolerance, continuing performing pixel subdivision on the surface elements, and repeating the subsequent steps until the final load is obtained. The pixel subdivision load transfer method and system of the present invention can achieve the following beneficial technical effects: transferring a pneumatic surface load onto a structure node, and achieving conservation before and after the transfer, and a precise match of load distribution.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

An apparatus and a method for adjusting an angle of installation of an aircraft landing light. The apparatus (1) comprises: a base (50), the base (50) comprising a rotary part (52) and a fixed part (53), and the rotary part (52) being capable of rotating about the fixed part (53); a carrier (30), being a hollow cylinder and fixed on the rotary part (52); a laser transmitter (20), a first end of which is provided with a laser outgoing hole (21) and a second end of which runs through the carrier (30) and is fixedly connected to the rotary part (52); and an adjusting mechanism (70) disposed on the carrier (30), used to adjust an angle of the laser transmitter (20) relative to the base (50). The apparatus and the method can easily and noticeably adjust an angle of installation of an aircraft landing light.

IPC Classes  ?

• G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
• F21V 17/00 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
• F21V 19/00 - Fastening of light sources or lamp holders

Abstract

A method for producing an aluminum alloy profile for a stringer of an aircraft wing comprises: determining the composition of an aluminum alloy, and calculating required quantity of raw materials according to the determined composition of the aluminum alloy; melting and refining the raw materials, to produce a molten aluminum alloy material; performing spray forming in a double-nozzle spray forming device, to form a billet; after the billet is formed, performing backward extrusion on the billet in a backward extruder, to form an aluminum alloy profile.

IPC Classes  ?

• C22F 1/053 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
• C22C 21/10 - Alloys based on aluminium with zinc as the next major constituent