CN206528624U - A kind of lightweight unmanned plane - Google Patents

A kind of lightweight unmanned plane Download PDF

Info

Publication number
CN206528624U
CN206528624U CN201720021896.0U CN201720021896U CN206528624U CN 206528624 U CN206528624 U CN 206528624U CN 201720021896 U CN201720021896 U CN 201720021896U CN 206528624 U CN206528624 U CN 206528624U
Authority
CN
China
Prior art keywords
wing
fuselage
shell
centre
elevator
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
CN201720021896.0U
Other languages
Chinese (zh)
Inventor
黄伟忠
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.)
Jiangsu Ops Auto Parts Co Ltd
Original Assignee
Jiangsu Ops Auto Parts Co Ltd
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 Jiangsu Ops Auto Parts Co Ltd filed Critical Jiangsu Ops Auto Parts Co Ltd
Priority to CN201720021896.0U priority Critical patent/CN206528624U/en
Application granted granted Critical
Publication of CN206528624U publication Critical patent/CN206528624U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Abstract

A kind of lightweight unmanned plane of the utility model, the unmanned plane includes fuselage(1), wing components(4), horizontal stabilizer assemblies(5), the fuselage(1)For hollow structure inside, and fuselage(1)Shell body be made up of cellular board, the fuselage(1)Inner hollow cavity in polylith dividing plate is installed(2), so that by fuselage(1)Internal cavity is separated into multiple separate installation cavitys.A kind of lightweight unmanned plane of the utility model, light weight, cost are low and flight maneuver is flexible.

Description

A kind of lightweight unmanned plane
Technical field
The utility model is related to a kind of unmanned plane, more particularly, to unmanned plane a kind of with low cost and low weight, belongs to Unmanned air vehicle technique field.
Background technology
At present, as microelectric technique, computer, communication remote sensing technology are continued to develop, unmanned plane is on military, civilian It is obtained for extensive development;Unmanned plane has the advantages that quick maneuverability, reaction, unmanned flight, operation require low, can be wide It is general to be applied to the fields such as agricultural, exploration, photography, border patrol, military surveillance, military attack;Simultaneously as unmanned plane is minimized The requirement of development, its volume constantly reduces, and space in the still substantial amounts of machine of all kinds of remote controls, control, power-equipment, therefore fuel tank Capacity constantly reduces, but is in order at continuation of the journey and requires, no matter military or civilian be both needed to require that unmanned plane has certain stagnant space-time Between, therefore unmanned plane lightness becomes one and needs the problem captured badly;Meanwhile, unmanned plane perform each generic task when, it is necessary to It has certain steering flexibility, and conventional unmanned plane governor motion not enough facilitates, so as to influence it to use scope.
The content of the invention
The purpose of this utility model is to overcome above-mentioned deficiency there is provided a kind of light weight, cost is low and flight maneuver is flexible Lightweight unmanned plane.
What the purpose of this utility model was realized in:
A kind of lightweight unmanned plane, the unmanned plane includes fuselage, wing components and horizontal stabilizer assemblies, and the fuselage is inside Hollow structure, and the shell body of fuselage is made up of cellular board, and polylith dividing plate is provided with the cavity of the inner hollow of the fuselage, So as to which the cavity of fuselage interior is separated into multiple separate installation cavitys;
The fuselage bottom is provided with the aluminium that a cyclic structure is provided with damper, the head end plane of the fuselage Multiple lightening holes are provided with alloy components, the Al-alloy parts;Wing components, the machine of the fuselage are installed in the middle part of the fuselage Horizontal stabilizer assemblies are installed on tail;
The wing components include wing centre section, outer wing and wing tip, and the wing centre section includes the wing centre section upper plate by arcuate structure Part and wing centre section lower plate bond and are provided with an anti-sump, and structure on the shell body for the hollow structure that pairing is constituted, wing centre section lower plate Into shell body wing upper plate and wing centre section lower plate outer surface on staggeredly be pasted with a plurality of reinforcement, the reinforcement pacify Equipped with wing centre section connector, connecting bolt, which is passed through, realizes wing centre section and fuselage in the pre-buried screw after wing centre section connector with screw-on machine Connection, the shell body left and right sides is provided with connection strap, and the bottom of the shell body, which caves inward, to be formed with two and symmetrically set An aileron is placed with the groove put, each groove, the aileron includes the aileron hollow body being made up of cellular board, institute The top for stating aileron hollow body is provided with the wooden connection strap of aileron, and the two ends of the wooden connection strap of the aileron are separately installed with wing centre section Rotary shaft and wing centre section power transmission shaft, the wing centre section rotary shaft activity are plugged on the cell wall of groove, and the wing centre section power transmission shaft passes through recessed The cell wall of groove is inserted in anti-sump, and wing centre section power transmission shaft is fixedly connected with a driving lever on one end in anti-sump;
The outer wing includes outer wing body and is connected to the outer wing connection strap of outer wing body both sides, the outer wing body For the hollow structure being made up of cellular board, and the outer wing connection strap is connected by bolt with the connection strap on wing centre section;It is described The end of outer wing is installed by the wing tip by there is glass fiber material to be made;
The horizontal stabilizer assemblies include the horizontal tail shell body of hollow structure, and the horizontal tail shell body is provided at both ends with by glass Be provided with installation storehouse on the outer apex of the wing of horizontal tail that fiber material is made, the lower surface of the horizontal tail shell body, the horizontal tail shell body by Cellular board is made, and is staggeredly equipped with a plurality of horizontal tail reinforcement on two surfaces up and down of horizontal tail shell body, and the horizontal tail adds Horizontal tail connector is installed, bolt passes through in the pre-buried screw after horizontal tail connector with screw-on machine and realizes horizontal tail shell in strengthening tendons The connection of body and fuselage, the bottom of the horizontal tail shell body, which caves inward, is formed with two symmetrically arranged grooves, each groove An elevator is inside placed with, the elevator includes in the elevator hollow body being made up of cellular board, the elevator The top of empty body is provided with the wooden connection strap of elevator, and the two ends of the wooden connection strap of elevator are separately installed with elevator Rotary shaft and elevator power transmission shaft, the elevator rotary shaft activity are plugged on the cell wall of horizontal tail shell body groove, and two rise The elevator power transmission shaft of drop rudder passes through the end in insertion installation storehouse after cell wall to be connected by synchronous connecting shaft;
Compared with prior art, the beneficial effects of the utility model are:
The agent structure of the utility model fuselage, wing components and horizontal stabilizer assemblies is all made of cellular board, and in appearance Intensity is improved in face with reinforcement, and is separated out different chambers for installing all kinds of controls by dividing plate in hollow fuselage interior Element processed and flight device, are easy to the later stage to change, safeguard;Meanwhile, wing components can easily realize steering by aileron regulation Flight, and horizontal stabilizer assemblies realize takeoff and landing by the elevator of collaborative work.
Brief description of the drawings
Fig. 1 is a kind of side structure schematic view of lightweight unmanned plane of the utility model.
Fig. 2 is a kind of positive structure diagram of lightweight unmanned plane of the utility model.
Fig. 3 is a kind of sectional view of the airframe structure of lightweight unmanned plane of the utility model.
Fig. 4 is a kind of structural representation of the Al-alloy parts of lightweight unmanned plane of the utility model.
Fig. 5 is a kind of structural representation of the wing of lightweight unmanned plane of the utility model.
Fig. 6 is a kind of structural representation of the wing centre section of lightweight unmanned plane of the utility model.
Fig. 7 is a kind of side view of the wing centre section of lightweight unmanned plane of the utility model.
Fig. 8 is a kind of side view of the upper plate of the wing centre section of lightweight unmanned plane of the utility model.
Fig. 9 is a kind of side view of the lower plate of the wing centre section of lightweight unmanned plane of the utility model.
Figure 10 is a kind of partial sectional view of the aileron of lightweight unmanned plane of the utility model.
Figure 11 is a kind of structural representation of the outer wing of lightweight unmanned plane of the utility model.
Figure 12 is a kind of structural representation of the horizontal stabilizer assemblies of lightweight unmanned plane of the utility model.
Figure 13 is a kind of side view of the horizontal stabilizer assemblies of lightweight unmanned plane of the utility model.
Figure 14 is a kind of partial sectional view of the elevator of lightweight unmanned plane of the utility model.
Figure 15 is a kind of connection driving structure schematic diagram of the elevator of lightweight unmanned plane of the utility model.
Wherein:
Fuselage 1, dividing plate 2, Al-alloy parts 3, wing components 4, horizontal stabilizer assemblies 5;
Damper 1.1;
Lightening hole 3.1;
Wing centre section 4.1, outer wing 4.2, wing tip 4.3;
Wing centre section upper plate 4.1.1, wing centre section lower plate 4.1.2, anti-sump 4.1.3, reinforcement 4.1.4, wing centre section connector 4.1.5, connection strap 4.1.6, aileron 4.1.7, wing centre section rotary shaft 4.1.8, wing centre section power transmission shaft 4.1.9, driving lever 4.1.10;
The wooden connection strap 4.1.7.2 of aileron hollow body 4.1.7.1, aileron;
Outer wing body 4.2.1, outer wing connection strap 4.2.2;
The outer apex of the wing 5.3 of horizontal tail shell body 5.1, horizontal tail reinforcement 5.2, horizontal tail, horizontal tail connector 5.4, elevator 5.5, liter Rudder rotary shaft 5.6, elevator power transmission shaft 5.7, synchronous connecting shaft 5.8 drop;
Storehouse 5.1.1 is installed;
The wooden connection strap 5.5.2 of elevator hollow body 5.5.1, elevator.
Embodiment
Referring to Fig. 1 ~ 15, a kind of lightweight unmanned plane that the utility model is related to, the unmanned plane includes fuselage 1, wing Component 4 and horizontal stabilizer assemblies 5, the fuselage 1 are hollow structure inside(Concretely, the fuselage 1 is by two housing sections pair up and down Close the hollow structure being bonded), and the shell body of fuselage 1 is made of cellular board(So as to serve loss of weight effect), it is described Polylith dividing plate 2 is installed, so as to the cavity inside fuselage 1 is separated into multiple mutually only in the cavity of the inner hollow of fuselage 1 Vertical installation cavity, the automatically controlled component different for installing;
The bottom of fuselage 1 is provided with damper 1.1, the head end plane of the fuselage 1 and is provided with a ring-type knot Multiple lightening holes 3.1 are provided with the Al-alloy parts 3 of structure, the Al-alloy parts 3;The middle part of the fuselage 1 is provided with wing components 4, horizontal stabilizer assemblies 5 are installed on the tail of the fuselage 1;
The wing components 4 include wing centre section 4.1, outer wing 4.2 and wing tip 4.3, and the wing centre section 4.1 includes by arc knot The wing centre section upper plate 4.1.1 and wing centre section lower plate 4.1.2 of structure bond the shell body for the hollow structure that pairing is constituted, wing centre section lower plate One anti-sump 4.1.3 is installed on 4.1.2, and constitutes the wing upper plate 4.1.1 and wing centre section lower plate 4.1.2 of shell body appearance Staggeredly it is pasted with face on a plurality of reinforcement 4.1.4, the reinforcement 4.1.4 and wing centre section connector 4.1.5 is installed, connects spiral shell Bolt passes through the connection for being screwed in after wing centre section connector 4.1.5 and wing centre section 4.1 and fuselage 1 being realized in the pre-buried screw on fuselage 1, described outer The housing left and right sides is provided with connection strap 4.1.6, the bottom of the shell body cave inward be formed with two it is symmetrically arranged recessed Aileron a 4.1.7, the aileron 4.1.7 is placed with groove, each groove and includes hollow of aileron being made up of cellular board Body 4.1.7.1, the aileron hollow body 4.1.7.1 top are provided with the wooden connection strap 4.1.7.2 of aileron, and the aileron is wooden Connection strap 4.1.7.2 two ends are separately installed with wing centre section rotary shaft 4.1.8 and wing centre section power transmission shaft 4.1.9, the wing centre section rotary shaft 4.1.8 activity is plugged on the cell wall of groove, and the cell wall of the wing centre section power transmission shaft 4.1.9 through groove is inserted in anti-sump 4.1.3 it is interior, and wing centre section power transmission shaft 4.1.9 is fixedly connected with a driving lever 4.1.10 on one end in anti-sump 4.1.3;Pass through Driving lever 4.1.10 driving ailerons 4.1.7 is rotated, so as to realize the control turned to aircraft;Concretely, in use, peace can be passed through Wing centre section power transmission shaft 4.1.9 rotations are driven loaded on the electric pushrod driving driving lever 4.1.10 in anti-sump 4.1.3;
The outer wing 4.2 includes outer wing body 4.2.1 and is connected to the outer wing connection strap of outer wing body 4.2.1 both sides 4.2.2, the outer wing body 4.2.1 is the hollow structure being made up of cellular board, and the outer wing connection strap 4.2.2 passes through bolt It is connected with the connection strap 4.1.6 on wing centre section 4.1;The end of the outer wing 4.2 is installed by the wing tip by there is glass fiber material to be made 4.3;
The horizontal stabilizer assemblies 5 include the horizontal tail shell body 5.1 of hollow structure, and the two ends of the horizontal tail shell body 5.1 are set It is equipped with the apex of the wing 5.3 outside the horizontal tail being made up of glass fiber material, the lower surface of the horizontal tail shell body 5.1 and is provided with installation storehouse 5.1.1, the horizontal tail shell body 5.1 is made up of cellular board, and is staggered on two surfaces up and down of horizontal tail shell body 5.1 Have and horizontal tail connector 5.4 is installed on a plurality of horizontal tail reinforcement 5.2, the horizontal tail reinforcement 5.2, bolt passes through horizontal tail connector The connection that horizontal tail shell body 5.1 and fuselage 1 are realized in the pre-buried screw on fuselage 1, the horizontal tail shell body 5.1 are screwed in after 5.4 Bottom cave inward to be formed with two symmetrically arranged grooves, each groove and be placed with an elevator 5.5, the lifting Rudder 5.5 includes the elevator hollow body 5.5.1, the elevator hollow body 5.5.1 that are made up of cellular board top peace Equipped with the wooden connection strap 5.5.2 of elevator, the two ends of the wooden connection strap 5.5.2 of elevator are separately installed with elevator rotation Axle 5.6 and elevator power transmission shaft 5.7, the activity of elevator rotary shaft 5.6 are plugged in the cell wall of the groove of horizontal tail shell body 5.1 On, the elevator power transmission shaft 5.7 of two elevators 5.5 passes through the end of insertion installation storehouse 5.1.1 after cell wall to pass through synchronized links Axle 5.8 is connected;
In addition:It should be noted that above-mentioned embodiment is only a prioritization scheme of this patent, the skill of this area Any change or improvement that art personnel are done according to above-mentioned design, within the protection domain of this patent.

Claims (1)

1. a kind of lightweight unmanned plane, it is characterised in that:The unmanned plane includes fuselage(1), wing components(4)And horizontal stabilizer assemblies (5), the fuselage(1)For hollow structure inside, and fuselage(1)Shell body be made up of cellular board, the fuselage(1)Inside Polylith dividing plate is installed in hollow cavity(2), so that by fuselage(1)Internal cavity is separated into multiple separate installations Cavity;
The fuselage(1)Bottom is provided with damper(1.1), the fuselage(1)Head end plane on a ring-type is installed The Al-alloy parts of structure(3), the Al-alloy parts(3)On be provided with multiple lightening holes(3.1);The fuselage(1)Middle part install There are wing components(4), the fuselage(1)Tail on horizontal stabilizer assemblies are installed(5);
The wing components(4)Include wing centre section(4.1), outer wing(4.2)And wing tip(4.3), the wing centre section(4.1)Include by The wing centre section upper plate of arcuate structure(4.1.1)With wing centre section lower plate(4.1.2)The shell body for the hollow structure that pairing is constituted is bonded, Wing centre section lower plate(4.1.2)On an anti-sump is installed(4.1.3), and constitute the wing upper plate of shell body(4.1.1)And wing centre section Lower plate(4.1.2)Outer surface on staggeredly be pasted with a plurality of reinforcement(4.1.4), the reinforcement(4.1.4)It is upper to install There is wing centre section connector(4.1.5), connecting bolt pass through wing centre section connector(4.1.5)After screw in fuselage(1)On pre-buried screw in Realize wing centre section(4.1)With fuselage(1)Connection, the shell body left and right sides is provided with connection strap(4.1.6), the shell body Bottom cave inward to be formed with two symmetrically arranged grooves, each groove and be placed with an aileron(4.1.7), the pair The wing(4.1.7)Include the aileron hollow body being made up of cellular board(4.1.7.1), the aileron hollow body(4.1.7.1) Top the wooden connection strap of aileron is installed(4.1.7.2), the wooden connection strap of the aileron(4.1.7.2)Two ends be separately installed with Wing centre section rotary shaft(4.1.8)With wing centre section power transmission shaft(4.1.9), the wing centre section rotary shaft(4.1.8)Activity is plugged in the groove of groove On wall, the wing centre section power transmission shaft(4.1.9)Cell wall through groove is inserted in anti-sump(4.1.3)It is interior, and wing centre section power transmission shaft (4.1.9)Positioned at anti-sump(4.1.3)A driving lever is fixedly connected with interior one end(4.1.10);
The outer wing(4.2)Include outer wing body(4.2.1)And it is connected to outer wing body(4.2.1)The outer wing connection of both sides Bar(4.2.2), the outer wing body(4.2.1)For the hollow structure being made up of cellular board, and the outer wing connection strap(4.2.2) Pass through bolt and wing centre section(4.1)On connection strap(4.1.6)It is connected;The outer wing(4.2)End install by there is glass material Expect the wing tip being made(4.3);
The horizontal stabilizer assemblies(5)Include the horizontal tail shell body of hollow structure(5.1), the horizontal tail shell body(5.1)Two ends It is provided with the apex of the wing outside the horizontal tail being made up of glass fiber material(5.3), the horizontal tail shell body(5.1)Lower surface on be provided with installation Storehouse(5.1.1), the horizontal tail shell body(5.1)It is made up of cellular board, and horizontal tail shell body(5.1)Two surfaces up and down on It is staggeredly equipped with a plurality of horizontal tail reinforcement(5.2), the horizontal tail reinforcement(5.2)On horizontal tail connector is installed(5.4), bolt Through horizontal tail connector(5.4)After screw in fuselage(1)On pre-buried screw in realize horizontal tail shell body(5.1)With fuselage(1)'s Connection, the horizontal tail shell body(5.1)Bottom cave inward to be formed with two symmetrically arranged grooves, each groove and put It is equipped with an elevator(5.5), the elevator(5.5)Include the elevator hollow body being made up of cellular board(5.5.1), institute State elevator hollow body(5.5.1)Top the wooden connection strap of elevator is installed(5.5.2), the wooden connection of the elevator Bar(5.5.2)Two ends be separately installed with elevator rotary shaft(5.6)With elevator power transmission shaft(5.7), the elevator rotation Axle(5.6)Activity is plugged in horizontal tail shell body(5.1)On the cell wall of groove, two elevators(5.5)Elevator power transmission shaft (5.7)Storehouse is installed in insertion after through cell wall(5.1.1)End pass through synchronous connecting shaft(5.8)It is connected.
CN201720021896.0U 2017-01-10 2017-01-10 A kind of lightweight unmanned plane Active CN206528624U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201720021896.0U CN206528624U (en) 2017-01-10 2017-01-10 A kind of lightweight unmanned plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201720021896.0U CN206528624U (en) 2017-01-10 2017-01-10 A kind of lightweight unmanned plane

Publications (1)

Publication Number Publication Date
CN206528624U true CN206528624U (en) 2017-09-29

Family

ID=59917211

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201720021896.0U Active CN206528624U (en) 2017-01-10 2017-01-10 A kind of lightweight unmanned plane

Country Status (1)

Country Link
CN (1) CN206528624U (en)

Similar Documents

Publication Publication Date Title
CN206243488U (en) Many power combinations change the unmanned plane for adapting to different landing mode different task load
IL244376A (en) An unmanned aerial vehicle
CN206528624U (en) A kind of lightweight unmanned plane
CN206528616U (en) A kind of lightweight low-cost unmanned target drone
CN206528611U (en) A kind of wing structure of lightweight unmanned plane
CN102963521A (en) Central wing of horizontal tail of civil airplane
CN206528622U (en) A kind of unmanned plane wing structure
CN206528625U (en) A kind of unmanned plane tail structure
CN210526849U (en) Fixed wing unmanned aerial vehicle of tilting-rotating force
CN106741828A (en) A kind of lightweight low-cost unmanned target drone
CN110844065A (en) Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing
CN204822068U (en) Aircraft is shiied in two oar VTOL
CN108423171A (en) Without rudder face VTOL fixed-wing unmanned plane
CN108466691A (en) The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan
CN208181413U (en) A kind of steady damping multi-rotor unmanned aerial vehicle fuselage box
CN214138949U (en) Novel VTOL fixed wing unmanned aerial vehicle
CN211055389U (en) Suspension type cargo hold suitable for multiaxis unmanned aerial vehicle
CN108528701A (en) A kind of rear single-blade formula combined wing aircraft of the band double compound auxiliary wings of duct and additional fin
CN110481772A (en) Single-screw paddle composite wing manned vehicle after a kind of
CN108657424A (en) Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust
CN108482663A (en) The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin
CN108820201A (en) Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust
CN108639329A (en) A kind of spiral shell with the auxiliary wing of twin screw and the attached wing pushes away combined wing aircraft
CN108791872A (en) With the compound auxiliary wing of ducted fan and additional fin without the compound rotor aircraft of back pressure formula
CN108545179A (en) Single ducted fan formula composite wing manned vehicle afterwards

Legal Events

Date Code Title Description
GR01 Patent grant
GR01 Patent grant