CN209192227U - A kind of new configuration vertical take-off and landing drone - Google Patents
A kind of new configuration vertical take-off and landing drone Download PDFInfo
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- CN209192227U CN209192227U CN201821766248.9U CN201821766248U CN209192227U CN 209192227 U CN209192227 U CN 209192227U CN 201821766248 U CN201821766248 U CN 201821766248U CN 209192227 U CN209192227 U CN 209192227U
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Abstract
The utility model discloses a kind of new configuration vertical take-off and landing drone, belong to aircraft transmission system and lifting rotor field, including fuselage, rolling wing system, vertical fin, rudder, aileron, wing flap, investigate gondola and pressurized strut of rising and falling, rolling wing system is mounted in the duct of wing, rolling wing system is identical by the two groups of four sections of sizes in left and right, oppositely oriented rolling wing composition；The transmission shaft of every section of rolling wing is coaxial, every group of two sections of composition cycloid propeller full vector propulsion systems；A kind of new configuration vertical take-off and landing drone disclosed in this patent can be realized in continental rise platform and sea-based platform VTOL; has better flight quality; the utility model combines the characteristic of rotor craft and Fixed Wing AirVehicle, lower to the dependence of landing site, and adaptive capacity to environment is very strong；Cycloid propeller overall system architecture is light and simple simultaneously, has wide military and civilian prospect.
Description
Technical field
The utility model is a kind of common aero vehicle, is related to aircraft transmission system and lifting rotor field, specifically
It is a kind of new configuration vertical take-off and landing drone.
Background technique
Can be realized the aircraft of VTOL at present is mainly rotor class aircraft, but rotor class flying instrument is effective
The distinct disadvantages such as rate is low, noise is big, manipulation is cumbersome, mechanism is complicated, and forward flight speed is low, and although traditional Fixed Wing AirVehicle is made an uproar
Sound is smaller relative to rotor class aircraft, and big Speed Flight is able to achieve when preceding winged, but Fixed Wing AirVehicle can not be real
Existing VTOL, it is stronger to the dependence of landing site, so the two all receives certain restrictions in use；It at present can be same
The aircraft of Shi Shixian VTOL and big Speed Flight is mainly tiltrotor aircraft, but tiltrotor aircraft exists
Also rotor class aircraft low efficiency is remained while having both both of the above advantage, the disadvantages of noise is big, and operating mechanism is complicated, together
When tiltrotor aircraft itself also have manipulation complicated, the higher equal self-defects of failure rate.
Cycloid propeller is a kind of device of novel generation aerodynamic lift, and blade is while around the revolution of cycloid propeller shaft also around hinge
Chain does vertical dip mining movement, is chiefly used in low reynolds number aircraft, passes through different location blade in cyclomorphosis rotary blade system
The angle of attack lift is provided, changed by the position of off-centre operation on control cycloid propeller to change the phase angle of blade cyclic pitch
Become net vector direction of pull, since the period of cycloid propeller rotates bring nonstationary flow dynamic characteristic, the stall for increasing blade is met
Angle, so that cycloid propeller has the characteristics that high-efficient, noise is low, vectored thrust variation is fast.
A kind of installation cycloid propeller is proposed in patent CN 202481313U by Northwestern Polytechnical University Tang Jiwei et al. application
Flying wing type layout aircraft, the cycloidal paddle propeller of the aircraft is mounted on Flying-wing's machine along Flying-wing's body plane of symmetry
Above body, and the movement of cycloidal paddle propeller blade, using a control mechanism, is realized on the outside of Flying-wing's block upper surface
The VTOL of aircraft is preceding winged, but the flight efficiency of the aircraft is low, and the omega that cycloid propeller generates is vortexed and body
Strong induction interference is formed, the stability and maneuverability of aircraft are bad, and realization degree is lower.
Utility model content
The utility model aiming at the problems existing in the prior art, discloses a kind of new configuration vertical take-off and landing drone, this
Utility model is used as dynamical system using cycloid oar system, which has two dimension omnidirectional vectored thrust, high-efficient, and noise is low etc.
Feature may be implemented to take off vertically using cycloid oar system, and being converted to when preceding winged fixed-wing mode can be with before biggish
Rapidly degree, which is flown to, arrives at the destination rear vertical landing, very convenient, fast, solves problems of the prior art.
The utility model is realized in this way:
A kind of new configuration vertical take-off and landing drone, including fuselage, the wing of fuselage two sides, wing include the secondary main wing in left and right two
And winglet on the wing above main wing, rolling wing system, the rolling wing are mounted on main wing and the wing in the duct of winglet composition
System is identical by the two groups of four sections of sizes in left and right, oppositely oriented rolling wing composition.The lift that the wing is provided under vertical winged state is rolled to fly with flat
Thrust under state, the class duct body that winglet and main wing are composed on the wing can provide additional thrust to rolling wing system, to pendulum
Line paddle generates certain advantageous induction, it is permanent it is flat fly during, the induced velocity that rolling wing system generates can delay main wing rear
Air-flow separation, increase stalling angle, further increase the flight quality of aircraft.The transmission shaft of every section of rolling wing is coaxial, takes phase
Same cross section, every section of rolling wing system are monolithic construction.Every group of two sections of composition cycloid propeller full vector propulsion systems；The rolling
The wing includes partition ring, and inner ring, outer ring are installed in the annular left and right sides of partition ring respectively；Rudder is sequentially installed with outside the outer ring surface
Machine pull rod, steering engine rocker arm, steering engine, the interior steering engine installed of wing, can drive aileron and wing flap to rotate；Pacify outside the inner ring surface
Equipped with blade bracket；The partition ring is uniformly distributed on peripheries with control pull rod；The blade bracket, control pull rod end with
Blade connection；It further include cycloid propeller rotary shaft in the rolling wing, cycloid propeller rotary shaft passes through side plate and is connected to outer ring, on side plate
There is the mounting hole of cycloid propeller rotary shaft, have bearing in hole, plays fixed function, cycloid propeller rotary shaft is the main load portion of cycloid propeller
Part, brushless motor rotates through transmission system and is transferred to cycloid propeller rotary shaft, and then blade is driven to revolve around rotary shaft.
The afterbody is respectively perpendicular is equipped with vertical fin up and down, and the quantity of vertical fin is two or more, at least
There is a vertical fin to be installed on above vertical take-off and landing drone, at least there is a vertical fin and be installed below vertical take-off and landing drone,
Undercarriage when taking off vertically or land as vertical take-off and landing drone.
Further, the both ends of vertical fin up and down are equipped with pressurized strut of rising and falling；It is equipped at the vertical fin tail edge
Rudder.
Further, the quantity of the vertical fin is two or more, at least one vertical fin is installed on VTOL
Above unmanned plane, at least there is a vertical fin and be installed below vertical take-off and landing drone.
Further, aileron and wing flap are mounted on by hinge at the main wing rear of the two sides.Aileron and wing flap are logical
It crosses hinge installation and at main wing rear, can realize that aircraft hangs down under winged state and flat winged state by rudderon and wing flap
Pose adjustment.
Further, investigation gondola is installed on the downside of the head of the fuselage.
Further, the control pull rod is set as four, by alloy steel pole and the nylon spherical hinge sleeve ring at both ends
Composition；It controls the nylon spherical hinge sleeve ring of pull rod one end and the metal hinge head at blade rear cooperates, control the other end of pull rod
The nylon spherical hinge sleeve ring fulcrum uniformly distributed with partition ring be connected.
Further, the blade has four, is made of balsa wood material, and shape is rectangle, uniformly distributed five ribs, edge
Blade open up to center line be provided with bilateral slot, carbon pipe is embedded into through slot, drives rear carbon pipe to making by control pull rod
Wing does pitching cycle movement around leading edge carbon pipe.
Further, several blades are provided between the blade bracket, every blade is equipped at the 75% of chord length
Control pull rod.
Further, it is 12 ° that the cycloid propeller pitch axis of the blade and unmanned plane, which horizontally advance angular separation,.
The invention also discloses the flight control methods of new configuration vertical take-off and landing drone, and specific control method is such as
Under:
Under the action of steering engine position change will occur for partition ring, to make the center location of partition ring relative to cycloid propeller
The rotary shaft center of circle will generate shift phenomenon；The distance between the center of circle of rotating disk, the cycloid propeller rotary shaft center of circle are known as eccentricity；
When eccentricity is 0, blade effective angle of attack is 0, and the directional velocity and string of blade are always consistent, will not
Generate lift；
When eccentricity is not 0, blade effective angle of attack is not also 0, and blade is done and periodically bowed by the control of control pull rod
Movement is faced upward, vectored thrust is generated, it is possible thereby to change the flight attitude of aircraft；
Blade movement is in surface, manipulates pull rod by pulling, and blade comes back, and generates positive incidence, lift with linear velocity
For surface；Blade movement is in underface, pushes the manipulation pull rod of blade so that blade is generated with linear velocity direction and just attacked
Angle, lift direction are surface,
Blade movement is in upper left side, manipulates pull rod by control, and it is positive incidence that blade is still generated with linear velocity, is risen
Power direction is upper left side；Blade movement is in lower left, pushes the manipulation pull rod of blade so that blade and linear velocity direction generate
Positive incidence, lift direction are upper right side；
Blade movement does not generate lift since paddle speed is parallel with string in left；Blade movement is in right,
By manipulating the control of pull rod, keeps paddle speed parallel with string, do not generate lift；
Blade movement is in upper right side, and by controlling the control of pull rod, blade comes back, and lift is upper right side；Blade movement
In lower right, lead to the control of control pull rod, blade is made to generate positive incidence, lift direction is upper left side.
The beneficial effect of the utility model and the prior art is:
1) the flying wing type new concept aircraft of this patent proposition, using cycloid propeller full vector propulsion system, the dynamical system
The features such as system has two-dimentional omnidirectional vectored thrust, high-efficient, and noise is low, the cycloid oar system of the utility model may be implemented vertically
Take off, and be converted to when preceding winged fixed-wing mode can be flown to biggish forward flight speed arrive at the destination after vertical landing,
It is convenient, fast；
2) the utility model is compared to traditional rotor craft, and the new concept aircraft using cycloid oar system due to being made
For power, the characteristic of rotor craft and Fixed Wing AirVehicle is combined, lower to the dependence of landing site, environment adapts to energy
Power is very strong；Cycloid propeller overall system architecture is light simultaneously, not complicated mechanical structure, therefore its machine that its can be made full use of excellent
Dynamic property and extremely low noise execute the tasks such as monitoring, the scouting under complicated landform environment, before having wide military and civilian
Scape；The utility model can be realized vertical and landing takeoff, while have both the ability of big Speed Flight；
3) the aerodynamic configuration of aircraft aerodynamic efficiency of the utility model is high, lift resistance ratio is big, flight noise is low, body knot
Structure is simple, and overall weight is light；Can be in city, islands and reefs, the landings such as mountainous region and naval vessel condition is risen than relatively rugged environment
Fly and landing, winged before horizontal and hovering wind resistance are good；
4) in addition, the induced velocity that the utility model rolling wing system generates can delay the air-flow of main wing rear to separate, increase
Big stalling angle improves the flight quality of aircraft；Realize that the vertical winged state of aircraft flies with flat by the aileron and wing flap of setting
Pose adjustment under state；It can be realized in continental rise platform and sea-based platform VTOL, vertically risen compared to traditional rotor class
Drop unmanned plane possesses better flight quality.
Detailed description of the invention
Fig. 1 is the utility model vertical take-off and landing drone left axle side view；
Fig. 2 is the utility model vertical take-off and landing drone right axle side view；
Structural schematic diagram when Fig. 3 is the utility model vertical take-off and landing drone VTOL；
Fig. 4 is that the utility model vertical take-off and landing drone by takeoff phase is transitioned into level flight stage schematic diagram；
Fig. 5 is the utility model vertical take-off and landing drone level flight condition schematic diagram；
Fig. 6 is the utility model vertical axis propeller eccentric circle control mechanism top view；
Fig. 7 is the front view of the utility model vertical axis propeller eccentric circle control mechanism；
Fig. 8 is the assembling schematic diagram of the utility model control rocker arm and parallelogram mechanism；
Fig. 9 is the utility model rotating disc perspective view of the explosion；
Figure 10 is the utility model blade schematic diagram；
Wherein, 1- fuselage, 2- rolling wing system, 3- vertical fin, 4- rudder, 5- aileron, 6- wing flap, 7- investigate gondola, and 8- rises
Fall pressurized strut, 9- partition ring, 10- inner ring, 11- outer ring, 12- cycloid propeller rotary shaft, 13- side plate, 14- steering engine, 15- blade branch
Frame, 16- steering engine rocker arm, 17- steering gear pull rod, 18- control pull rod, 19- blade, 20- main wing, winglet on the 21- wing, 22- cycloid propeller
Pitch axis.
Specific embodiment
It is clear to keep the purpose of this utility model, technical solution and effect clearer, it is practical to this to be exemplified below example
Novel further description.It should be understood that specific implementation described herein is not used to only to explain the utility model
Limit the utility model.
As shown in Figure 1 and 2, a kind of new configuration vertical take-off and landing drone of the utility model includes fuselage 1, rolling wing system 2, hangs down
Tail 3, rudder 4, aileron 5, wing flap 6, investigation gondola 7 and pressurized strut 8 of rising and falling.
Wherein, the wing includes winglet 21 on the wing above the secondary main wings 20 in left and right two and main wing, main wing 20 and
Rolling wing system 2 is mounted in the duct that winglet 21 forms on the wing, the rolling wing system 2 is identical by the two groups of four sections of sizes in left and right,
Oppositely oriented rolling wing composition；The transmission shaft of every section of rolling wing is coaxial, every group of two sections of composition cycloid propeller full vector propulsion systems；
Aileron 5 and wing flap 6 are mounted on by hinge at 20 rear of main wing, aileron and wing flap pass through hinge installation and main wing
At rear, the pose adjustment that aircraft hangs down under winged state and flat winged state can be realized by rudderon and wing flap.
Wing includes winglet 21 on the wing above the secondary main wings 20 in left and right two and main wing, 21 groups of winglet on main wing 20 and the wing
At duct in be mounted with rolling wing system 2, the rolling wing system 2 by left and right two groups of identical, oppositely oriented rollings of four sections of sizes
Wing composition；The transmission shaft of every section of rolling wing is coaxial, every group of two sections of composition cycloid propeller full vector propulsion systems.
As shown in Fig. 6 ~ 10, the rolling wing includes partition ring 9, and inner ring 10, outer ring are installed in the annular left and right sides of partition ring 9 respectively
11.Steering gear pull rod 17, steering engine rocker arm 16, steering engine 14 are sequentially installed with outside 11 face of outer ring；Paddle is installed outside 10 face of inner ring
Leaf bracket 15 is provided with several blades 19 between blade bracket 15, and every blade is equipped with control pull rod at the 75% of chord length
18, it is 12 ° that cycloid propeller pitch axis 22 and unmanned plane in blade 19, which horizontally advance angular separation,；9 surrounding of partition ring is equal
It is furnished with control pull rod 18；The blade bracket 15, control pull rod 18 are connect with blade 19 in end.Pull rod 18 is controlled to be arranged
It is four, is made of the nylon spherical hinge sleeve ring at alloy steel pole and both ends；Control the nylon spherical hinge sleeve of 18 one end of pull rod
Metal hinge head at ring and 19 rear of blade cooperates, and nylon spherical hinge sleeve ring and the partition ring 9 for controlling the other end of pull rod 18 are equal
The fulcrum of cloth is connected.Blade 19 has four, is made using balsa wood material, and shape is rectangle, uniformly distributed five ribs, along paddle
The center line of Ye Zhanxiang is provided with bilateral slot, and carbon pipe is embedded into through slot, so that mechanism is during the motion, by controlling pull rod
18 drive rear carbon pipes are to make wing do pitching cycle movement around leading edge carbon pipe.
Rolling in the wing further includes cycloid propeller rotary shaft 12, and cycloid propeller rotary shaft 12 is the main load component of cycloid propeller, brushless
Motor rotates through transmission system and is transferred to cycloid propeller rotary shaft 12, and then blade 19 is driven to revolve around rotary shaft；Cycloid propeller rotation
Shaft 12 passes through side plate 13 and is connected to outer ring 11, and side plate 13 has cycloid propeller rotation using carbon fibre material for rectangle on side plate 13 1
The mounting hole of shaft 12 has bearing in hole, plays fixed function.
1 tail portion of fuselage is respectively perpendicular is equipped with vertical fin 3 up and down, and upper and lower 3 both ends of vertical fin are equipped with pressurized strut 8 of rising and falling；It is described
3 tail edge of vertical fin at rudder 4 is installed, vertical fin 3 is installed in the vertical orientation of vertical take-off and landing drone, is risen as vertical
Undercarriage of drop unmanned plane when taking off vertically or land, the quantity of vertical fin 3 are two or more, at least one vertical fin
It is installed on above vertical take-off and landing drone, at least there is a vertical fin and be installed below vertical take-off and landing drone.
As shown in Fig. 3 ~ 5, Fig. 3,4,5 describe the utility model vertical take-off and landing drone and are tilted to flat winged shape from taking off
State.Structural schematic diagram when wherein Fig. 3 is the utility model vertical take-off and landing drone VTOL, Fig. 4 are that the utility model hangs down
Straight landing unmanned plane is transitioned into level flight stage schematic diagram by takeoff phase, and Fig. 5 is the utility model vertical take-off and landing drone
Level flight condition schematic diagram, it can be seen that the utility model vertical take-off and landing drone angle in transient process is becoming always
Change, until going to flat winged state.
Under the action of steering engine 14 position change will occur for partition ring 9, to make 9 center location of partition ring relative to cycloid
12 center of circle of paddle rotary shaft will generate shift phenomenon, and the center of circle of rotating disk is called partially with the distance between 12 center of circle of cycloid propeller rotary shaft
The heart away from.
When eccentricity is 0, blade effective angle of attack is 0, and the directional velocity and string of blade 19 are always consistent, will not
Lift can be generated；When eccentricity is not 0, blade effective angle of attack is not also 0, and blade 19 does week by the control of manipulation pull rod
The pitching movement of phase property generates vectored thrust, it is possible thereby to change the flight attitude of aircraft.Assuming that pass through the manipulation of steering engine 14, rotation
Turntable is displaced to the lower right of cycloid propeller rotary shaft, as shown in Figure 7.Blade is in surface, manipulates pull rod, blade by pulling
It comes back, generates positive incidence with linear velocity, lift is surface；Blade is in upper left side, manipulates pull rod by control, blade is collinear
It is positive incidence that speed, which still generates, and lift direction is upper left side；Blade is in left, since paddle speed is parallel with string,
Do not generate lift；Blade movement is in lower left, pushes the manipulation pull rod of blade so that blade is generated with linear velocity direction and just attacked
Angle, lift direction are upper right side；Blade is below, and pushes the manipulation pull rod of blade so that blade and linear velocity direction produce
Raw positive incidence, lift direction are surface, and blade is in lower right, manipulate pull rod by control, blade is made to generate positive incidence,
Lift direction is upper left side；Blade is in right, by manipulating the control of pull rod, keeps paddle speed parallel with string, does not generate
Lift；Blade is in upper right side, and by controlling the control of pull rod 18, blade comes back, and lift is upper right side.
From there through the lift situation that circumferentially generates of analysis blade it can be concluded that, when blade is in the left and right,
Lift will not be generated；And when blade is in other orientation, so that it may to generate the lift component of surface.So working as rotating disk
When being displaced to cycloid propeller 12 lower section of rotary shaft, by the movement of cycloid propeller, blade will generate the resultant force that direction is surface.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, without departing from the principle of this utility model, several improvement can also be made, these improvement also should be regarded as
The protection scope of the utility model.
Claims (9)
1. a kind of new configuration vertical take-off and landing drone, including fuselage (1), the wing of fuselage (1) two sides, which is characterized in that described
Wing include winglet (21) on the wing above the secondary main wings (20) in left and right two and main wing, winglet (21) on main wing (20) and the wing
Rolling wing system (2) is mounted in the duct of composition, the rolling wing system (2) is identical by the two groups of four sections of sizes in left and right, rotation direction phase
Anti- rolling wing composition；The transmission shaft of every section of rolling wing is coaxial, every group of two sections of composition cycloid propeller full vector propulsion systems；The rolling wing
Including partition ring (9), inner ring (10), outer ring (11) are installed in the annular left and right sides of partition ring (9) respectively；
Steering gear pull rod (17), steering engine rocker arm (16), steering engine (14) are sequentially installed with outside described outer ring (11) face；The inner ring
(10) blade bracket (15) are installed outside face；The partition ring (9) is uniformly distributed on peripheries with control pull rod (18)；The blade branch
Frame (15), control pull rod (18) are connect with blade (19) in end；It further include cycloid propeller rotary shaft (12) in the rolling wing,
Cycloid propeller rotary shaft (12) passes through side plate (13) and is connected to outer ring (11)；Described fuselage (1) tail portion is respectively perpendicular installation up and down
There are vertical fin (3).
2. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the vertical fin up and down
(3) both ends are equipped with pressurized strut of rising and falling (8)；Rudder (4) are installed at described vertical fin (3) tail edge.
3. a kind of new configuration vertical take-off and landing drone according to claim 2, which is characterized in that the vertical fin (3)
Quantity is two or more, at least one vertical fin is installed on above vertical take-off and landing drone, at least there is a vertical fin
It is installed below vertical take-off and landing drone.
4. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the main wing of the two sides
(20) aileron (5) and wing flap (6) are mounted on by hinge at rear.
5. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the fuselage (1)
Investigation gondola (7) is installed on the downside of head.
6. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the control pull rod
(18) four are set as, is made of the nylon spherical hinge sleeve ring at alloy steel pole and both ends；Control the Buddhist nun of pull rod (18) one end
Metal hinge head at imperial spherical shape hinge sleeve ring and blade (19) rear cooperates, and controls the nylon spherical hinge sleeve of the other end of pull rod (18)
The ring fulcrum uniformly distributed with partition ring (9) is connected.
7. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the blade (19) has
Four, made of balsa wood material, shape is rectangle, uniformly distributed five ribs, along blade open up to center line be provided with bilateral slot,
Carbon pipe is embedded into through slot, drives rear carbon pipe to make wing do the pitching period around leading edge carbon pipe by control pull rod (18)
Property movement.
8. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the blade bracket
(15) it is provided between several blades (19), every blade is equipped with control pull rod (18) at the 75% of chord length.
9. a kind of new configuration vertical take-off and landing drone according to claim 1, which is characterized in that the blade (19)
It is 12 ° that cycloid propeller pitch axis (22) and unmanned plane, which horizontally advance angular separation,.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821766248.9U CN209192227U (en) | 2018-10-30 | 2018-10-30 | A kind of new configuration vertical take-off and landing drone |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821766248.9U CN209192227U (en) | 2018-10-30 | 2018-10-30 | A kind of new configuration vertical take-off and landing drone |
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| CN209192227U true CN209192227U (en) | 2019-08-02 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229367A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | A kind of new configuration vertical take-off and landing drone and its flight control method |
| CN116424544A (en) * | 2023-06-14 | 2023-07-14 | 清华大学 | Aircraft flap |
-
2018
- 2018-10-30 CN CN201821766248.9U patent/CN209192227U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229367A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | A kind of new configuration vertical take-off and landing drone and its flight control method |
| CN116424544A (en) * | 2023-06-14 | 2023-07-14 | 清华大学 | Aircraft flap |
| CN116424544B (en) * | 2023-06-14 | 2023-08-15 | 清华大学 | Aircraft flap |
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