CN208915439U - Adjustable wing swallow shape simulation type unmanned plane - Google Patents
Adjustable wing swallow shape simulation type unmanned plane Download PDFInfo
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- 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
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- wing
- empennage
- unmanned plane
- displacement device
- displacement
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- 238000004088 simulation Methods 0.000 title claims abstract description 17
- 238000006073 displacement reaction Methods 0.000 claims abstract description 67
- 238000005096 rolling process Methods 0.000 claims description 10
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 7
- 230000001681 protective effect Effects 0.000 claims description 5
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 230000001133 acceleration Effects 0.000 abstract 1
- 230000002708 enhancing effect Effects 0.000 abstract 1
- 229920002457 flexible plastic Polymers 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000004899 c-terminal region Anatomy 0.000 description 1
- 230000001268 conjugating effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008571 general function Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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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
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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN201821688551.1U CN208915439U (en) | 2018-10-18 | 2018-10-18 | Adjustable wing swallow shape simulation type unmanned plane |
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Application Number | Priority Date | Filing Date | Title |
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CN201821688551.1U CN208915439U (en) | 2018-10-18 | 2018-10-18 | Adjustable wing swallow shape simulation type unmanned plane |
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CN201821688551.1U Expired - Fee Related CN208915439U (en) | 2018-10-18 | 2018-10-18 | Adjustable wing swallow shape simulation type unmanned plane |
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Cited By (3)
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 |
-
2018
- 2018-10-18 CN CN201821688551.1U patent/CN208915439U/en not_active Expired - Fee Related
Cited By (4)
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 |
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Date | Code | Title | Description |
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GR01 | Patent grant | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190531 |