CN208915439U - Adjustable wing swallow shape simulation type unmanned plane - Google Patents

Adjustable wing swallow shape simulation type unmanned plane Download PDF

Info

Publication number
CN208915439U
CN208915439U CN201821688551.1U CN201821688551U CN208915439U CN 208915439 U CN208915439 U CN 208915439U CN 201821688551 U CN201821688551 U CN 201821688551U CN 208915439 U CN208915439 U CN 208915439U
Authority
CN
China
Prior art keywords
wing
empennage
unmanned plane
displacement device
displacement
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.)
Expired - Fee Related
Application number
CN201821688551.1U
Other languages
Chinese (zh)
Inventor
陈新华
吴毅豪
李柏燐
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.)
Foshan Xing Xing Intelligent Technology Co Ltd
Original Assignee
Foshan Xing Xing Intelligent Technology 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 Foshan Xing Xing Intelligent Technology Co Ltd filed Critical Foshan Xing Xing Intelligent Technology Co Ltd
Priority to CN201821688551.1U priority Critical patent/CN208915439U/en
Application granted granted Critical
Publication of CN208915439U publication Critical patent/CN208915439U/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Landscapes

  • Toys (AREA)

Abstract

The utility model provides a kind of adjustable wing swallow shape simulation type unmanned plane, it include: fuselage, the left and right ends of the front fuselage are mounted on wing displacement device, two symmetrically arranged wings are separately mounted on wing displacement device, wing propeller is mounted on two wings, the back body is equipped with empennage displacement device, and two empennages are symmetrically mounted on empennage displacement device, is mounted on empennage propeller on two empennages.The advantages of this adjustable wing swallow shape simulation type unmanned plane combination fixed-wing formula unmanned plane and more rotary wind type unmanned planes, it is deformed using the wing of motor control unmanned plane, unmanned plane can be made to accomplish vertical lift, the quick cruising speed with fixed-wing, also the flight of long range is adapted to, there is flexible anxious acceleration and deceleration ability simultaneously, the playability for greatly enhancing unmanned plane, what is be also easier to caters to the demand of market crowd.

Description

Adjustable wing swallow shape simulation type unmanned plane
Technical field
The utility model relates to air vehicle technique fields, and in particular to a kind of adjustable wing swallow shape simulation type unmanned plane.
Background technique
Unmanned plane in the current market is divided into fixed-wing formula and more rotary wind types, respectively there is its advantage and disadvantage, multi-rotor unmanned aerial vehicle Have it is excellent handling, structure it is simple easy to maintain and can VTOL convenience, but have endurance short, speed is slow, low efficiency The disadvantages of, flying speed compared with fixed-wing formula it is slow very much, it is relatively elaborate for the flight of long range.Fixed-wing unmanned plane has effect The incomparable advantages of more rotors such as rate is high, and speed is fast, and endurance is long, but can not VTOL, need longer runway to take off And landing, inconvenience is brought to using.It is proposed various types of more rotors currently on the market and fixed-wing combines VTOL fixed-wing unmanned plane, merged the respective advantage of more rotors and fixed-wing, the long endurance of very good solution, speed Fastly, flying distance it is remote and can the problems such as VTOL, cruise in electric power, logistics transportation, public security fire-fighting, agricultural plant protection surveys and draws etc. There is wide development in field.Due to the difference of more rotors and fixed-wing flight essence, have to the screw pitch of propeller different It is required that general solution is to solve the problems, such as this by 2 sets of dynamical systems respectively on the market at present, wherein a set of for revolving more The wing, it is a set of to be used for fixed-wing, but mean that another set of system will become extra useless load under different working conditions, Seriously affect flight efficiency.It is quasi- or use a set of dynamical system, it is driven with the propeller of identical pitch by verting, realization is not Same state of flight, actually multi-rotor unmanned aerial vehicle flying speed is slow, and the most of the time is in floating state, needs fine pitch spiral shell Paddle is revolved, and needs high pitch propeller to drive, the two is difficult mutually to take into account, otherwise spiral since speed is fast when fixed-wing flight Paddle efficiency is very low.
Utility model content
To solve the deficiencies in the prior art, the utility model provides a kind of adjustable wing swallow shape simulation type unmanned plane, utilizes Displacement device controls wing and the empennage deformation of unmanned plane so that unmanned plane be provided simultaneously with fixed-wing unmanned plane and more rotors nobody The advantages of machine, improves propeller service efficiency.
The technical solution of the utility model is as follows: a kind of adjustable wing swallow shape simulation type unmanned plane, comprising: fuselage, the machine The left and right ends of body front end are mounted on wing displacement device, and two symmetrically arranged wings are separately mounted to wing displacement device On, wing propeller is mounted on two wings, the back body is equipped with empennage displacement device, and two empennages are symmetrically pacified On empennage displacement device, empennage propeller is mounted on two empennages.
In the above-mentioned technical solutions, it may be implemented by the control to wing displacement device and empennage displacement device to nobody The control of machine offline mode, specific control mode are as follows:
(1) after taking off pattern switching to booting from shutdown from unmanned plane, by wing displacement device wing is in Upward state, i.e. wing are perpendicular to the ground, and the wing propeller being mounted on wing and ground are in parastate, lead to simultaneously Crossing empennage displacement device makes empennage be in upward state, i.e. empennage is perpendicular to the ground, the empennage spiral being mounted on empennage Paddle and ground be in parastate so that propelled longitudinally power when unmanned plane takes off reaches maximum, realize such as more rotary wind types nobody The general function of quickly taking off of machine;
(2) when switching from low cruise to high speed cruise regime, made by wing displacement device and empennage displacement device Wing and empennage gradually conjugate by upward state perpendicular to the ground be wing and empennage horizontality parallel to the ground, make Horizontal impulse when obtaining unmanned plane airflight cruise reaches maximum, realizes such as the general quick cruise of fixed-wing formula unmanned plane Function;(when low cruise → high-performance cruise, control program is then opposite)
(3) when shutting down landing mode switching to preparation from state of flight, pass through wing displacement device and empennage displacement dress It sets so that wing and empennage displacement are in upward state at such as above-mentioned (1), i.e. wing and empennage is perpendicular to the ground, spiral Paddle and ground are in parastate, so that longitudinal original place landing when unmanned plane lands, is realized as more rotary wind type unmanned planes Rapid in-situ land function.
Preferably, the wing displacement device includes wing displacement steering engine and wing rocking bar crank, and the wing conjugates rudder Machine is mounted on fuselage, and wing rocking bar crank includes first connecting rod, second connecting rod and third connecting rod, wherein one end of first connecting rod It is fixed on the output shaft of wing displacement steering engine, the other end of first connecting rod and one end of second connecting rod are hinged, second connecting rod Other end be fixedly connected with third connecting rod, and third connecting rod is fixed on wing, when wing conjugates servo driving wing When rocking bar crank rotates, wing can be driven to carry out rotation displacement by wing rocking bar crank.
Preferably, the empennage displacement device includes rolling bearing pedestal, empennage displacement steering engine and empennage rocking bar crank, described Empennage displacement steering engine is mounted on tail cone, and rolling bearing pedestal is mounted on the front side of empennage displacement steering engine, and cylindrical shaft is through rolling Bearing block extends outward, and two symmetrically arranged empennages are by cylindrical shaft synchronized links, one end of empennage rocking bar crank and empennage Steering engine connection is conjugated, the other end of empennage rocking bar crank is connect with empennage, when empennage displacement steering engine rotation, can pass through tail Wing rocking bar crank handle turns empennage carries out rotation displacement.
Preferably, protective shell is enclosed on the outside of the rear end of the wing and empennage, the protective shell is lightweight flexible plastic, Complete machine is used using wing and the lightweight flexible plastic of empennage rear end as the support leg of landing, and unmanned plane may make to keep away in landing Exempt to damage wing and empennage.
The utility model has the beneficial effects that:
1) this adjustable wing swallow shape simulation type unmanned plane has had both the high advantage and quadrotor of fixed-wing unmanned plane cruising speed The original place of formula unmanned plane take off vertically landing, hovering and low cruise the advantages of, while the shape of wing and empennage makes with angle It is more steady in the state of high-speed flight to obtain unmanned plane;
2) this adjustable wing swallow shape simulation type unmanned plane is by the switching of quadrotor mode and fixed-wing mode, it can be achieved that height It is fast low cruise, hovering, vertical and landing takeoff;
3) this adjustable wing swallow shape simulation type unmanned plane has used four to start motor, and generated thrust is at least than general Fixed-wing unmanned plane doubles, therefore but also it is more faster than general fixed-wing unmanned plane in high-speed flight;
4) this adjustable wing swallow shape simulation type unmanned plane compared on the market general fixed-wing formula unmanned plane and quadrotor Formula unmanned plane adaptability is stronger, and purposes is more extensive.
Detailed description of the invention
Schematic perspective view when Fig. 1 is the utility model high-speed flight.
Front view when Fig. 2 is the utility model high-speed flight.
Top view when Fig. 3 is the utility model high-speed flight.
Fig. 4 be the utility model take off landing when schematic perspective view.
Fig. 5 be the utility model take off landing when front view.
Fig. 6 be the utility model take off landing when top view.
Fig. 7 be the utility model take off landing when side view.
Fig. 8 is the partial structurtes stereoscopic schematic diagram of wing displacement device in the utility model.
Fig. 9 is the partial structurtes stereoscopic schematic diagram of empennage displacement device in the utility model.
Figure 10 is the local structure top view of empennage displacement device in the utility model.
In figure: 1, fuselage;2, wing;3, wing propeller;4, wing displacement device;5, empennage displacement device;6, empennage Propeller;7, empennage;8, wing conjugates steering engine;9, wing rocking bar crank;10, rolling bearing pedestal;11, empennage conjugates steering engine;12, Empennage rocking bar crank.
Specific embodiment
It is with reference to the accompanying drawings and embodiments, right in order to be more clear the purpose of this utility model, technical solution and advantage The utility model is further elaborated.It should be appreciated that specific embodiment described herein is only used to explain this reality With novel, it is not used to limit the utility model.
A kind of embodiment: adjustable wing swallow shape simulation type unmanned plane.
Referring to figs. 1 to shown in Figure 10, a kind of adjustable wing swallow shape simulation type unmanned plane, comprising: fuselage 1,1 front end of fuselage Left and right ends be mounted on wing displacement device 4, two symmetrically arranged wings 2 are separately mounted on wing displacement device 4, Wing propeller 3 is mounted on two wings 2, wherein the wing displacement device 4 includes wing displacement steering engine 8 and wing Rocking bar crank 9, on the fuselage 1, referring to shown in Fig. 8, wing rocking bar crank 9 includes the first company for wing displacement steering engine 8 installation Bar, second connecting rod and third connecting rod, wherein one end (end A) of first connecting rod is fixed on the output shaft of wing displacement steering engine 8, the The other end (C-terminal) of one connecting rod and one end of second connecting rod are hinged, and the other end (end B) and third connecting rod of second connecting rod are solid Fixed connection, and third connecting rod (side a and b) is fixed on wing 2, and wherein the end A, D is fixing end, and the end A is wing 2 and machine The rotatable end of the connection of body 1, the end D are the connecting rod drive end that wing conjugates steering engine 8, when wing displacement steering engine 8 drives wing rocking bar When the CD axis rotation of crank 9, and then the rotary motion of the AB axis of wing rocking bar crank 9 is driven, so as to drive wing 2 to carry out Rotation displacement;1 rear end of fuselage is equipped with empennage displacement device 5, and two empennages 7 are symmetrically mounted on empennage displacement device 5, Empennage propeller 6 is mounted on two empennages 7, the empennage displacement device 5 includes rolling bearing pedestal 10, empennage displacement steering engine 11 and empennage rocking bar crank 12, wherein the structure of empennage rocking bar crank 12 is identical as the structure of wing rocking bar crank, the empennage Displacement steering engine 11 is mounted on 1 end of fuselage, and rolling bearing pedestal 10 is mounted on the front side of empennage displacement steering engine 11, and cylindrical shaft is through rolling Dynamic bearing seat 10 extends outward, and two symmetrically arranged empennages 7 are by cylindrical shaft synchronized links, one end of empennage rocking bar crank 12 It is connect with empennage displacement steering engine 11, the other end of empennage rocking bar crank 12 is connect with empennage 7, when empennage displacement steering engine 11 rotates When, 7 wing of tail can be driven to carry out rotation displacement (its displacement principle phase for conjugating principle and wing by empennage rocking bar crank 12 Together), and on the outside of the rear end of the wing 2 and empennage 7 it is enclosed with protective shell, the protective shell is lightweight flexible plastic, complete machine It is used using the lightweight flexible plastic of 7 rear end of wing 2 and empennage as the support leg of landing, unmanned plane may make to avoid in landing Damage wing 2 and empennage 7.
In the present embodiment, when this unmanned plane takes off, 2 He of wing is made by wing displacement device 4 and empennage displacement device 5 Empennage 7 is in upward state, i.e. wing 2 and empennage 7 is perpendicular to the ground, the wing propeller 3 that is mounted on wing 2 and The empennage propeller 6 being mounted on empennage 7 is in parastate with ground, starts propeller, at this time similar to quadrotor nobody Machine carries out vertical level land and takes off.It is similar to quadrotor drone after taking off, by finely tuning the revolving speed of four rotors, realize low speed Cruise or hovering.Then by wing displacement device 4 and empennage displacement device 5 quickly control wing 2 and the rotation of empennage 7 to Fig. 1, 2,3 state can be exchanged into fixed-wing drone status, realize high-performance cruise.Under fixed-wing state, flying speed can reduced After switch to quadrotor formula unmanned plane, carry out stooge or vertical landing.As shown in Fig. 2, wing 2 slightly upwarps, it can Fuselage is squeezed to middle part, keeps fuselage more stable by the thrust risen using air-flow;7 tailing wing propeller 6 of vee tail is set It is more stable that meter makes it fly under fixed-wing state, and speed is faster than general fixed-wing.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art Art personnel can also make several improvements and modifications without departing from the principle of this utility model, these improvements and modifications Also it should be regarded as the protection scope of the utility model.

Claims (4)

1. a kind of adjustable wing swallow shape simulation type unmanned plane, including fuselage, it is characterised in that: the left and right ends of the front fuselage are equal Wing displacement device is installed, two symmetrically arranged wings are separately mounted on wing displacement device, are pacified on two wings Equipped with wing propeller, the back body is equipped with empennage displacement device, and two empennages are symmetrically mounted on empennage displacement device On, empennage propeller is mounted on two empennages.
2. adjustable wing swallow shape simulation type unmanned plane as described in claim 1, it is characterised in that: the wing displacement device includes Wing conjugates steering engine and wing rocking bar crank, and the wing displacement steering engine is mounted on fuselage, and wing rocking bar crank includes first Connecting rod, second connecting rod and third connecting rod, wherein one end of first connecting rod is fixed on the output shaft of wing displacement steering engine, and first connects The other end of bar and one end of second connecting rod are hinged, and the other end of second connecting rod is fixedly connected with third connecting rod, and the Three-link is fixed on wing.
3. adjustable wing swallow shape simulation type unmanned plane as described in claim 1, it is characterised in that: the empennage displacement device includes Rolling bearing pedestal, empennage displacement steering engine and empennage rocking bar crank, the empennage displacement steering engine are mounted on tail cone, rolling bearing Seat is mounted on the front side of empennage displacement steering engine, and cylindrical shaft extends outward through rolling bearing pedestal, two symmetrically arranged empennages By cylindrical shaft synchronized links, one end of empennage rocking bar crank is connect with empennage displacement steering engine, the other end of empennage rocking bar crank It is connect with empennage.
4. adjustable wing swallow shape simulation type unmanned plane as described in claim 1, it is characterised in that: the rear end of the wing and empennage Outside is enclosed with protective shell.
CN201821688551.1U 2018-10-18 2018-10-18 Adjustable wing swallow shape simulation type unmanned plane Expired - Fee Related CN208915439U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201821688551.1U CN208915439U (en) 2018-10-18 2018-10-18 Adjustable wing swallow shape simulation type unmanned plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201821688551.1U CN208915439U (en) 2018-10-18 2018-10-18 Adjustable wing swallow shape simulation type unmanned plane

Publications (1)

Publication Number Publication Date
CN208915439U true CN208915439U (en) 2019-05-31

Family

ID=66709657

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201821688551.1U Expired - Fee Related CN208915439U (en) 2018-10-18 2018-10-18 Adjustable wing swallow shape simulation type unmanned plane

Country Status (1)

Country Link
CN (1) CN208915439U (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110329492A (en) * 2019-06-25 2019-10-15 李海刚 Unmanned plane
CN113697097A (en) * 2021-09-01 2021-11-26 中国航空研究院 Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings
CN115123535A (en) * 2022-08-11 2022-09-30 北京北航天宇长鹰无人机科技有限公司 Tilt wing unmanned aerial vehicle

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110329492A (en) * 2019-06-25 2019-10-15 李海刚 Unmanned plane
CN113697097A (en) * 2021-09-01 2021-11-26 中国航空研究院 Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings
CN113697097B (en) * 2021-09-01 2024-01-02 中国航空研究院 Fixed wing aircraft overall aerodynamic layout with tiltable outer wings and rotor wings
CN115123535A (en) * 2022-08-11 2022-09-30 北京北航天宇长鹰无人机科技有限公司 Tilt wing unmanned aerial vehicle

Similar Documents

Publication Publication Date Title
CN101837195B (en) Model airplane with vertical takeoff and landing
CN200995782Y (en) Airplane
CN106882371A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN208915439U (en) Adjustable wing swallow shape simulation type unmanned plane
CN106043696A (en) Flying system for unmanned aerial vehicle
CN103332293A (en) Tilting double-duct subminiature unmanned plane
CN106915459A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN205418102U (en) All -wing aircraft formula rotor craft that verts
CN106428527A (en) Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings
CN109878697A (en) Folding wing and fixed-wing Multi-axis aircraft
CN205998126U (en) A kind of unmanned plane during flying system
CN105173076B (en) A kind of vertical take-off and landing drone
CN205396534U (en) Rotor unmanned aerial vehicle verts
CN204548497U (en) A kind of many rotor flight devices
CN109319106A (en) A kind of high-speed rotor machine
CN206871360U (en) A kind of multiple degrees of freedom flapping-wing modal with high propulsive efficiency
CN108298074A (en) The component that verts for the more rotor flying vehicles of manned duct
CN208360498U (en) One kind is verted double-rotor aerobat
CN107380428A (en) Dish-style rotor craft
CN107021208A (en) The tail sitting posture VUAV and control method of a kind of utilization duct
CN201744174U (en) Model airplane vertically taking off and landing
CN108891591A (en) A kind of aircraft
CN105346725A (en) Vertical take-off and landing unmanned aerial vehicle
CN105059525A (en) Aerodynamic layout of small-sized vertical takeoff and landing aircraft
CN205150230U (en) Modular four -axis all -wing aircraft aircraft

Legal Events

Date Code Title Description
GR01 Patent grant
GR01 Patent grant
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20190531