CN104925266A

CN104925266A - Thin-wall oil tank of unmanned helicopter

Info

Publication number: CN104925266A
Application number: CN201510275121.1A
Authority: CN
Inventors: 王川; 于孟利
Original assignee: Day Started Innovation (beijing) Technology Co Ltd
Current assignee: Day Started Innovation (beijing) Technology Co Ltd
Priority date: 2015-05-26
Filing date: 2015-05-26
Publication date: 2015-09-23
Anticipated expiration: 2035-05-26
Also published as: CN104925266B

Abstract

The invention discloses a thin-wall oil tank of an unmanned helicopter. The oil tank adopts a cubic irregular profile structure, and the oil tank is formed by connecting an upper part and a lower part, wherein the upper part adopts a cubic structure with a groove; the lower part adopts a slope structure formed by splicing four triangle plates, and an oil whirling is arranged at the bottom of the slope structure; a helicopter engine and a belt wheel connected with a helicopter empennage are arranged at the middle upper part of the oil tank; the groove of the oil tank is right matched with the belt wheel, and the heights of both sides of the groove are increased. The lower part of the unmanned helicopter body is curved, and the bottom of the oil tank adopts the slope structure, so that bottom of the oil tank is right fit with the helicopter body. Through the adoption of the design of the oil tank disclosed by the invention, the oil capacity of the oil tank of the helicopter is increased farthest, and the working time of the helicopter is prolonged.

Description

A kind of depopulated helicopter thin-walled fuel tank

Technical field

The present invention relates to the part design of aviette and SUAV (small unmanned aerial vehicle), be specifically related to a kind of depopulated helicopter thin-walled fuel tank, belong to aviation aircraft and technical field of mechanical design.

Background technology

Depopulated helicopter adopts driving engine to provide power substantially, and cruise duration, in fuselage, the design of fuel tank directly determined the length in aircraft cruise duration as the important indicator weighing unmanned plane performance.All the time, the fuel tank of the type interior of aircraft is cube structure, is limited to the stream line pattern curved design of airframe and the labyrinth of inside, tank capacity is less, the material of most fuel tank is heavier simultaneously, and add the own wt of fuselage, these all directly cause the shortening of aircraft operating time.Consider above all factors, we design the Oiltank structure of abnormity, coordinate the integral layout of fuselage, make full use of inner space, improve space availability ratio and fuel load, add the operating time of aircraft, and do inclined design and the design of oily whirlpool of tank bottoms, when aircraft flight occurs that certain direction significantly tilts, fully ensure that the fuel feeding of aircraft is sufficient.

Summary of the invention

The technical matters that 1, will solve

Tradition unmanned plane fuel tank is cube structure, and be subject to the restriction of aircraft curved surface shell and inner space, fuel tank self capacity can reduce when designing, and directly has influence on the operating time of aircraft.Tradition tank bottoms is planar structure, aircraft POL is generally heavy oil, poor fluidity, when oil mass is less, there will be fuel feeding not in time or for the situation of shortage of oil, simultaneously when the action of tilting appears in aircraft flight, there will be the situation for shortage of oil equally, directly can threaten the safety of aircraft, cause safety misadventure.So when tank design, while guarantee Maximum Fuel, ensure that aircraft fuel feeding is sufficient, meeting Integral lifting aeroplane performance, improves aircraft reliability and safety.

2, the technical scheme adopted

Special feature of the present invention mainly fuel tank abnormity design, the inclined design of tank bottoms and oily whirlpool design.

The technical scheme that the present invention specifically implements below is described.

Tradition fuel tank is cube structure, and the present invention is a kind of cube polymorphic structure, and it is combined by upper and lower two parts connection; Its top is the reeded cube structure of band, and its underpart is spliced into ramp structure by 4 pieces of set squares and is provided with oily whirlpool in bottom.See Fig. 1, Fig. 2, Fig. 5, in unmanned fuselage, fuel tank middle and upper part is aero-engine and the belt wheel being connected aircraft tail, and the size of fuel tank groove can put down belt wheel just when designing, and both sides increase height.Unmanned underbelly is curved surface simultaneously, and tank bottoms is designed to ramp structure, fuselage of just fitting, and above design promotes the fuel load of fuel tanker all to greatest extent, extends aircraft operating time.

Devise oily whirlpool at tank bottoms, see Fig. 1, Fig. 2, fuel tank internal is made up of sponge, weight and oil inlet.Because fuel tank has a small amount of residue in bottom when containing oil, after increasing sponge, ensure abundant oil suction, oil directly can enter oil pipe through sponge filters out residue simultaneously.Weight designs, and is to consider, because Action of Gravity Field can ensure that oil-feed is in bottom always, to add the inclined design of tank bottoms, when ensure that the action of tilting appears in aircraft in flight course, can fuel feeding sufficient, promote reliability.

Fuel tank own material is solid, is thin-wall construction simultaneously, decreases the weight of aircraft self, add aircraft load-carrying.

Wherein, the thickness range of fuel tank thin-wall construction is 1-2 millimeter.

3, beneficial effect

The invention has the advantages that:

1) utilize fuselage interior space first to greatest extent, improve fuel load, increase operating time.

2) relative to conventional oil path design, done the design of oily whirlpool at tank bottoms, the inclined design of tank bottoms simultaneously, fuel feeding when fully ensureing craft inclination is sufficient, increases reliability.

3) fuel tank adopts thin-walled design, and material is durable, reduces aircraft own wt, increases Aircraft Load amount.

Accompanying drawing explanation

Fig. 1 is fuel tank front view.

Fig. 2 is fuel tank left view.

Fig. 3 is fuel tank birds-eye view.

Fig. 4 is fuel tank block diagram.

Fig. 5 is fuel tank block diagram.

In figure, nomenclature is as follows:

1, casing; 2, oily whirlpool; 3, inclined-plane; 4, oil inlet; 5, oil outlet; 6, groove.

Detailed description of the invention

Below by example, embodiments of the present invention are described:

See Fig. 1-Fig. 5, a kind of depopulated helicopter thin-walled of the present invention fuel tank, it is a kind of cube polymorphic structure, and this structure is combined by upper and lower two parts connection; Its top is the reeded cube structure of band, and its underpart is spliced into ramp structure by 4 pieces of set squares and is provided with oily whirlpool in bottom.Fuel tank internal is made up of sponge, weight and oil inlet.Because fuel tank has a small amount of residue in bottom when containing oil, after increasing sponge, ensure abundant oil suction, oil directly can enter oil pipe through sponge filters out residue simultaneously.Weight designs, and is to consider, because Action of Gravity Field can ensure that oil-feed is in bottom always, to add the inclined design of tank bottoms, when ensure that the action of tilting appears in aircraft in flight course, and can fuel feeding abundance.

Fuel tank has designed according to main body mechanism design parameter, by mould one-shot forming during manufacture.Wherein, the thickness range of fuel tank thin-wall construction is 1-2 millimeter.

For installation, by two anchor ears of front and back symmetry, fuel tank is held, be then bolted and anchor ear is fixed on fuselage carbon plate.Anchor ear material adopts aluminum material, can fit completely with fuel tank, and material is light, can reduce unmanned plane own wt, and strength of material is larger simultaneously, can bear stronger shearing force and flexure stress, have stronger reliability.

Claims

1. a depopulated helicopter thin-walled fuel tank, is characterized in that: it is a kind of cube polymorphic structure, is connected combine by upper and lower two parts; Its top is the reeded cube structure of band, and its underpart is spliced into ramp structure by 4 pieces of set squares and is provided with oily whirlpool in bottom; Be aero-engine and the belt wheel being connected aircraft tail in fuel tank middle and upper part, the size of fuel tank groove can put down belt wheel just, and both sides increase height; Unmanned underbelly is curved surface, and tank bottoms is designed to ramp structure, fuselage of just fitting, and above design promotes the fuel load of fuel tanker all to greatest extent, extends aircraft operating time;

Devise oily whirlpool at tank bottoms, fuel tank internal is made up of sponge, weight and oil inlet, because have a small amount of residue in bottom when fuel tank contains oil, after increasing sponge, ensure abundant oil suction, oil directly enters oil pipe through sponge filters out residue simultaneously; Weight designs, consider that Action of Gravity Field ensures that oil-feed is in bottom always, add the inclined design of tank bottoms, when ensure that the action of tilting appears in aircraft in flight course, can fuel feeding sufficient, promote reliability, fuel tank own material is solid, be thin-wall construction simultaneously, decrease the weight of aircraft self, add aircraft load-carrying.

2. a kind of depopulated helicopter thin-walled fuel tank according to claim 1, is characterized in that: the thickness range of this fuel tank thin-wall construction is 1-2 millimeter.