CN110450948A - A kind of vertically taking off and landing flyer - Google Patents
A kind of vertically taking off and landing flyer Download PDFInfo
- Publication number
- CN110450948A CN110450948A CN201910764964.6A CN201910764964A CN110450948A CN 110450948 A CN110450948 A CN 110450948A CN 201910764964 A CN201910764964 A CN 201910764964A CN 110450948 A CN110450948 A CN 110450948A
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- China
- Prior art keywords
- line shaft
- wing
- connecting rod
- propeller
- power
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of vertically taking off and landing flyer, the vertically taking off and landing flyer is different from existing vertically taking off and landing flyer, there are six line shafts for setting, improve the take-off weight that aircraft can carry, in order to guarantee center of the aerodynamic center in line shaft of full machine, the aircraft is provided with front wing and rear wing, so that the aerodynamic center of entire aircraft between front wing and rear wing, meets the control requirement that center of gravity and power axis center are overlapped in vertically taking off and landing flyer；Six line shafts are separately positioned on two connecting rods, connecting rod connects the wing tip of front wing and rear wing, it streams the wing tip of front wing and flow to rear wing along connecting rod, additional speed is provided for rear aerofoil air-flow, so that playing the role of wing drag before reducing increases rear wing lift；The installation site of line shaft is symmetrical arranged on two connecting rods, can provide uniform power for entire vertically taking off and landing flyer.
Description
[technical field]
The invention belongs to technical field of aircraft design, and in particular to a kind of vertically taking off and landing flyer.
[background technique]
VTOL Fixed Wing AirVehicle technology is long-standing, and relatively common at present is the combined type or 4 (2+2) of 4+1
Tilting type, in addition there are tailstock formulas or 3 (2+1) tilting types etc. to apply less type.
Since Fixed Wing AirVehicle longitudinal center of gravity position is usually at wing, it is contemplated that VTOL state power center (PC) needs
It to be overlapped with center of gravity, the vertical starting power that vertically taking off and landing flyer uses at present is substantially 4 axis power (8 paddle of 4 axis, 4 paddle or 4 axis),
But the structure, because of the limitation of uniaxial tensile force, the total take-off weight of aircraft is restricted.
[summary of the invention]
It is an object of the invention to overcome the above-mentioned prior art, a kind of vertically taking off and landing flyer is provided；This is vertical
Landing aircraft improves the take-off weight that aircraft can carry.
In order to achieve the above objectives, the present invention is achieved by the following scheme:
A kind of vertically taking off and landing flyer, including fuselage；The preceding part bilateral of fuselage is each provided with a front wing, and rear part is double
Side is each provided with a rear wing, and two front wings are symmetrical relative to fuselage, and two rear wings are symmetrical relative to fuselage；Each front wing
Wing tip passes through a connecting rod with the middle part of the same side rear wing respectively and is fixedly connected, and the connecting rod is parallel to the axis of fuselage；It is each
Setting is fixedly installed propeller, the power being arranged on two connecting rods on each line shaft there are three line shaft on a connecting rod
Shaft position is symmetrical arranged relative to fuselage axis.
A further improvement of the present invention is that:
Preferably, the line shaft on the connecting rod on right side include respectively the first line shaft of the connecting rod front end on the right side of setting,
Third line shaft in middle position and the 5th line shaft in rear end；It include the company for being separately positioned on left side on the connecting rod in left side
Second line shaft of bar front end, in the 4th line shaft in middle position and in the 6th line shaft of rear end.
Preferably, each line shaft is provided with a power intake, one or two power output end；Each is dynamic
The power intake of power axis is connected to the power output end of engine, and engine is arranged in connecting rod；Each line shaft moves
M propeller is fixedly installed on power output end.
Preferably, for third line shaft and the 4th line shaft, when power output end is one and M is 1, the spiral
Paddle is in the top of connecting rod；When power output end is two and M is 1, propeller is separately positioned on above and below connecting rod.
Preferably, for the first line shaft and the second line shaft, when power output end is one and M is 1, propeller exists
The front or top of connecting rod；When power output end is two and M is 1, propeller is above and below connecting rod.
For the 5th line shaft and the 6th line shaft, when power output end is one and M is 1, propeller is in connecting rod
Rear or top；When power output end is two and M is 1, propeller is above and below connecting rod.
Preferably, the engine is motor, piston engine or turboprop；
Preferably, the motor is mixed using pure electric power or oil electricity as its power source；The piston engine or turbine spiral shell
The power source of rotation paddle motor is that pure oil is dynamic.
Preferably, the spanwise length of each front wing is less than the spanwise length of its rear rear wing.
Preferably, on the basis of the bottom surface of fuselage, the height of front wing is lower than the height of rear wing.
Preferably, the outer end of each front wing is provided with sweepforward, and the outer end of each rear wing is provided with sweepback.
Compared with prior art, the invention has the following advantages:
The invention discloses a kind of vertically taking off and landing flyer, which flies different from existing VTOL
Row device, there are six line shafts for setting, improve the take-off weight that aircraft can carry, in order to guarantee the aerodynamic center of full machine dynamic
The center of power axis, the aircraft are provided with front wing and rear wing, so that the aerodynamic center of entire aircraft is in front wing and rear wing
Between, meet the control requirement that center of gravity and power axis center are overlapped in vertically taking off and landing flyer；Six line shafts are respectively set
On two connecting rods, connecting rod connects the wing tip of front wing and rear wing, streams the wing tip of front wing and flow to rear wing along connecting rod,
Additional speed is provided for rear aerofoil air-flow, so that playing the role of wing drag before reducing increases rear wing lift；On two connecting rods
The installation site of line shaft is symmetrical arranged, and can provide uniform power for entire vertically taking off and landing flyer.
Further, the line shaft on each connecting rod is separately positioned on front end, middle position and rear end, so that line shaft
Power uniformly can be provided for vertically taking off and landing flyer, and two third line shafts and the 4th line shaft are respectively in connecting rod
Between, it can guarantee centerline of the aerodynamic center in third line shaft and the 4th line shaft line of vertically taking off and landing flyer, together
At the center of Shi Liu line shaft line.
Further, line shaft provides power by engine, and the power output end of line shaft can be according to circumstances set as
One or two, can also be provided with multiple propellers according to demand on each power output end.
Further, for different line shafts, different orientation can be arranged in propeller, different to be suitable for
Situation.
Further, engine can select common aircraft engine, and the power source of engine is also equipped with a variety of
Selection.
Further, the spanwise length of front wing is less than the spanwise length of rear wing, by adjusting the area and shape of front wing, energy
Enough adjust the aerodynamic center position of entire aircraft.
Further, the height of front wing is lower than the height of rear wing, and front wing wake flow is allowed to form advantageous interference to rear wing.
Further, front wing band sweepforward, rear wing band sweepback, enables to layout weight more to concentrate, rotary inertia is smaller, has
It is controlled conducive to the entirety of aircraft.
[Detailed description of the invention]
Fig. 1 is the structure composition schematic diagram of vertically taking off and landing flyer of the invention；
Fig. 2 is the fixed-wing cruise modal graph that vertically taking off and landing flyer of the present invention is 4+2 tilting type；
Four view of vertically taking off and landing flyer Fig. 3 of the invention；Wherein: (a) figure is left view；(b) figure is front view；(c)
Figure is top view；(d) figure is perspective view；
Fig. 4 is the fixed-wing cruise modal graph that vertically taking off and landing flyer is 6+1 form；
Wherein: the first line shaft of 1-；The second line shaft of 2-；3- third line shaft；The 4th line shaft of 4-；The 5th power of 5-
Axis；The 6th line shaft of 6-；7- fuselage；8- front wing；9- rear wing；10- fixed fin；11- connecting rod.
[specific embodiment]
The present invention is further elaborated in the following with reference to the drawings and specific embodiments.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention；Term " first ", " second ", " third "
It is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance；In addition, unless otherwise specific regulation and limit
Fixed, term " installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, be also possible to detachably connect
It connects；It can be directly connected, the connection inside two elements can also be can be indirectly connected through an intermediary.For this
For the those of ordinary skill in field, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
The invention discloses a kind of vertically taking off and landing flyer, the front of vertically taking off and landing flyer fuselage 7 is set as front and back, is flown
The rear of row device fuselage 7 is rear, and along the direction of fuselage 7 from back to front, the left side of fuselage 7 is the left-hand in the present invention, machine
The right side of body 7 is the dextrad in the present invention；Underneath with left and right as standard.
Referring to Fig. 1 and Fig. 3, the vertically taking off and landing flyer include fuselage 7, fuselage 7 preceding part bilateral be provided with front wing
8, rear part bilateral is provided with rear wing 9, and the spanwise length of rear wing 9 is greater than the spanwise length of front wing 8；The wing tip of every side front wing 8
Rear wing 9 in its rear is fixedly connected by a connecting rod 11 respectively, and the connecting rod 11 is parallel to the axis of fuselage 7, and two
Axisymmetrical of a connecting rod 11 relative to fuselage 7；Connecting rod 11 connects the wing tip of front wing 8 and rear wing 9, makes 8 wing tip of front wing
It streams and flow to rear wing 9 along connecting rod 11, provide additional speed for 9 face air-flow of rear wing, increase to play and reduce 8 resistance of front wing
The effect of 9 lift of rear wing.The setting height of front wing 8 can be higher than rear wing 9, can also be lower than rear wing 9, the preferably height of front wing 8
Degree allows 8 wake flow of front wing to form advantageous interference to rear wing 9 lower than rear wing 9 by adjusting the established angle and shape of wing 8；
Front wing 8 and rear wing 9 can be straight wing can also with sweep angle, as shown in Figure 1, preferably front wing 8 is with sweepforward, rear wing 9 with sweepback,
Layout weight is enabled to more to concentrate, rotary inertia is smaller, is conducive to the whole control of aircraft；The rear end fixation of fuselage 9 is set
It is equipped with fixed fin 10, for the stabilized flight device in flight course.
It is provided with line shaft on two connecting rods 11, there are three line shafts for setting on each connecting rod 11, therefore this is vertical
Landing aircraft is provided with 6 line shafts altogether, and respectively the first line shaft 1, the second line shaft 2, third line shaft the 3, the 4th are dynamic
Power axis 4, the 5th line shaft 5 and the 6th line shaft 6；Wherein, the first line shaft 1, third line shaft 3 and the 5th line shaft 5 are on the right side
On the connecting rod 11 of side, the second line shaft 2, the 4th line shaft 4 and the 6th line shaft 6 are fixed on the connecting rod 11 in left side,
First line shaft 1 and the second line shaft 2 are arranged at the front end of connecting rod 11, and axisymmetrical of the two relative to fuselage 7, third
Line shaft 3 and the 4th line shaft 4 are arranged at the middle position of connecting rod 11, and axisymmetrical of the two relative to fuselage 7, and the 5th
Line shaft 5 and the 6th line shaft 6 are arranged at the rear end of connecting rod 11, and axisymmetrical of the two relative to fuselage 7；The power
Axis is provided with power intake and output end, and power intake is connected with engine, and power output end is connected with propeller；Start
Machine is mounted on the inside of connecting rod 11, the endless number system of the engine, can use one with six power input shafts, can also be with
Six power input shafts are respectively arranged to be connected with the power output end of an engine, can also be arranged in the connecting rod 11 on right side
One engine, for providing power simultaneously for the first line shaft 1, third line shaft 3 and the 5th line shaft 5, the company in left side
One engine is set in bar 11, for providing power simultaneously for the second line shaft 2, the 4th line shaft 4 and the 6th line shaft 6.
The engine can be motor, piston engine or turboprop；It is corresponding when engine be motor when,
Power source be pure electric power or oil electricity mixing, oily electricity be mixed into oily turn is changed to it is electronic；When engine is piston engine or whirlpool
Airscrew engine is taken turns, power source is that pure oil is dynamic.
Two power output ends or a power output end can be arranged in six line shafts, each line shaft, each
It is fixedly installed M propeller on power output end, therefore may include 2M propeller in any one line shaft, M is >=1
Natural number；Preferred M is 1, i.e. is provided with a propeller on a power output end；It is provided with when on a power output end
When M propeller, the distance between adjoining spiral paddle >=propeller diameter × 1.1；For third line shaft 3 and the 4th power
Axis 4, when propeller is 1, propeller is on the top of connecting rod 11, and when propeller is 2, a propeller is in connecting rod 11
Top, a propeller is in the lower part of connecting rod 11；For the first line shaft 1 and the second line shaft 2, when propeller is 1, spiral shell
Revolving paddle can be on the top of connecting rod 11, also can be in the front end of connecting rod 11, and when propeller is 2, a propeller is in connecting rod
11 top, a propeller is in the lower part of connecting rod 11；For the 5th line shaft 5 and the 6th line shaft 6, when propeller is 1
When, propeller can be on the top of connecting rod 11, also can be in the rear end of connecting rod 11, when propeller is 2, a propeller exists
The top of connecting rod 11, a propeller is in the lower part of connecting rod 11.For the first line shaft 1, the second line shaft 2, the 5th line shaft 5
With the 6th line shaft 6, the rotation of power axis direction can be realized by the way that rotating mechanism is arranged, the rotating mechanism can pass through tune
The pedestal for motivation of haircuting realizes the rotation of power axis direction, and transmission mechanism can also be arranged between engine and line shaft, real
The rotation of existing power axis direction.
Preferably, it is capable of fixing setting propeller in the front end of fuselage or rear end, propeller will be arranged at this will rise
The power supply and cruising phase of depression of order section separate.Since battery maximum discharge current and energy density are negatively correlated, so cruise
The electric current that stage needs is small, so that it may select the battery of higher energy density, further promote cruise duration.Propeller it is preposition and
Postposition the difference is that the wake flow of preposition propeller plays acceleration to wing air-flow, it is more efficient, but pitot needs cloth
It sets elsewhere such as the leading edge of a wing, air speed pipe size will lengthen, and assembly difficulty is slightly larger.Propeller postposition efficiency is slightly lower, but empty
Speed pipe does not have to change.It is illustrated in figure 4 front end fixed setting propeller,
Above-mentioned different propeller set-up mode, corresponding different form；Such as 6+1 composite wing, i.e. each line shaft exists
A propeller is arranged in the top of connecting rod 11, and the front end of fuselage 7 or rear end are also equipped with a propeller；Landing stage front end
Or rear end propeller does not work, remaining propeller works, cruising phase only has the propeller works of front end or rear end, remaining spiral
Paddle stops working.
It referring to fig. 2, is the propeller on the first line shaft 1 and the second line shaft 2 before connecting rod 11 such as 4+2 tilting type
It just and can vert, remaining four propeller is in the top of connecting rod 11, landing stage the first line shaft 1 and the second line shaft 2
On propeller go to upward, all propellers work at the same time, the spiral shell on cruising phase the first line shaft 1 and the second line shaft 2
Rotation paddle verts to propeller works facing forward, only on the first line shaft 1 and the second line shaft 2, remaining propeller does not work；Or
Person is the propeller of the 5th line shaft 5 and the 6th line shaft 6 at the rear of connecting rod 11, remaining four propeller is in connecting rod 11
Top, the propeller on the 5th line shaft 5 of landing stage and the 6th line shaft 6 are gone to upward, and all propellers work at the same time, and patrol
Propeller on the 5th line shaft 5 of boat stage and the 6th line shaft 6 verts to backwards, only the 5th line shaft 5 and the 6th power
Propeller works on axis 6, remaining propeller do not work.
It is that the propeller on the first line shaft 1 and the second line shaft 2 is dynamic in the front of connecting rod 11, the 5th such as 2+4 tilting type
The propeller of power axis 5 and the 6th line shaft 6 is at the rear of connecting rod 11, and the propeller of third line shaft 3 and the 4th line shaft 4 is even
The top of bar 11, landing stage the first line shaft 1, the second line shaft 2, the 5th line shaft 5 and the 6th line shaft 6 propeller turn
To upward, all propellers are worked at the same time, and the propeller on cruising phase the first line shaft 1 and the second line shaft 2 verts to court
Before, the propeller on the 5th line shaft 5 and the 6th line shaft 6 verts to backwards, only the first line shaft 1, the second line shaft 2,
Propeller works on 5th line shaft 5 and the 6th line shaft 6, remaining propeller do not work.
Vertically taking off and landing flyer of the invention is suitable for unmanned plane, is also applied for manned situation.
The aircraft uses front and back double-vane layout, and the span area of front wing 8 is less than rear wing 9, by adjusting the face of front wing 8
Product, size and shape, so that full machine aerodynamic center position is at the center of six axis, it is dynamic in third line shaft 3 and the 4th in other words
At the line center of power axis 4, meet the control requirement that center of gravity and power axis center are overlapped in vertically taking off and landing flyer, during this is pneumatic
The heart is between the wing of front and back, so that the center of gravity of the lengthwise position of aircraft is no longer on wing.The present invention uses connecting rod by front and back
Wing connection, connecting rod provide power installation site.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of vertically taking off and landing flyer, which is characterized in that including fuselage (7)；The preceding part bilateral of fuselage (7) is each provided with one
A front wing (8), rear part bilateral are each provided with a rear wing (9), two front wings (8) relative to fuselage (7) symmetrically, two rear wings
(9) symmetrical relative to fuselage (7)；The wing tip of each front wing (8) and the middle part of the same side rear wing (9) pass through a connecting rod respectively
(11) it is fixedly connected, the connecting rod (11) is parallel to the axis of fuselage (7)；There are three power for setting on each connecting rod (11)
Axis is fixedly installed propeller on each line shaft, and the power shaft position being arranged on two connecting rods (11) is relative to fuselage (7)
Axisymmetrical setting.
2. a kind of vertically taking off and landing flyer according to claim 1, which is characterized in that the power on the connecting rod (11) on right side
Axis include respectively first line shaft (1) of the connecting rod on the right side of setting (11) front end, middle position third line shaft (3) and
The 5th line shaft (5) in rear end；It include second of connecting rod (11) front end on the left of being separately positioned on the connecting rod (11) in left side
Line shaft (2), in the 4th line shaft (4) in middle position and in the 6th line shaft (6) of rear end.
3. a kind of vertically taking off and landing flyer according to claim 2, which is characterized in that each line shaft is provided with one
Power intake, one or two power output end；The power that the power intake of each line shaft is connected to engine is defeated
Outlet, engine setting is in connecting rod (11)；M propeller is fixedly installed on the power output end of each line shaft.
4. a kind of vertically taking off and landing flyer according to claim 3, which is characterized in that for third line shaft (3) and
Four line shafts (4), when power output end is one and M is 1, top of the propeller in connecting rod (11)；Work as power output
End for two and M be 1 when, propeller is separately positioned on above and below connecting rod (11).
5. a kind of vertically taking off and landing flyer according to claim 3, which is characterized in that for the first line shaft (1) and
Two line shafts (2), when power output end is one and M is 1, propeller is in the front or top of connecting rod (11)；When power is defeated
When outlet is two and M is 1, propeller is above and below connecting rod (11)；
For the 5th line shaft (5) and the 6th line shaft (6), when power output end is one and M is 1, propeller is in connecting rod
(11) rear or top；When power output end is two and M is 1, propeller is above and below connecting rod (11).
6. a kind of vertically taking off and landing flyer according to claim 3, which is characterized in that the engine is motor, piston
Engine or turboprop.
7. a kind of vertically taking off and landing flyer according to claim 6, which is characterized in that the motor is with pure electric power or oil electricity
Mixing is used as its power source；The power source of the piston engine or turboprop is that pure oil is dynamic.
8. a kind of vertically taking off and landing flyer according to claim 1, which is characterized in that the span of each front wing (8) is long
Degree is less than the spanwise length of its rear rear wing (9).
9. a kind of vertically taking off and landing flyer according to claim 1, which is characterized in that on the basis of the bottom surface of fuselage (7),
The height of front wing (8) is lower than the height of rear wing (9).
10. vertically taking off and landing flyer described in -9 any one according to claim 1, which is characterized in that each front wing (8)
Outer end is provided with sweepforward, and the outer end of each rear wing (9) is provided with sweepback.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910764964.6A CN110450948A (en) | 2019-08-19 | 2019-08-19 | A kind of vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910764964.6A CN110450948A (en) | 2019-08-19 | 2019-08-19 | A kind of vertically taking off and landing flyer |
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| CN110450948A true CN110450948A (en) | 2019-11-15 |
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| CN201910764964.6A Pending CN110450948A (en) | 2019-08-19 | 2019-08-19 | A kind of vertically taking off and landing flyer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN205633042U (en) * | 2016-05-06 | 2016-10-12 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle |
| CN107985584A (en) * | 2017-12-06 | 2018-05-04 | 邹家勇 | Multi-functional flight equipment |
| CN108569399A (en) * | 2018-04-10 | 2018-09-25 | 西北工业大学 | A kind of short take-off and landing unmanned plane using distributed duct power |
| CN109131865A (en) * | 2017-06-19 | 2019-01-04 | 贝尔直升机德事隆公司 | Recoverable and extensible flying rotor system |
| CN109263903A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of multifunction aircraft |
| CN208530842U (en) * | 2018-02-13 | 2019-02-22 | 北京航空航天大学 | Composite rotor aircraft |
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2019
- 2019-08-19 CN CN201910764964.6A patent/CN110450948A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205633042U (en) * | 2016-05-06 | 2016-10-12 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle |
| CN109131865A (en) * | 2017-06-19 | 2019-01-04 | 贝尔直升机德事隆公司 | Recoverable and extensible flying rotor system |
| CN107985584A (en) * | 2017-12-06 | 2018-05-04 | 邹家勇 | Multi-functional flight equipment |
| CN208530842U (en) * | 2018-02-13 | 2019-02-22 | 北京航空航天大学 | Composite rotor aircraft |
| CN108569399A (en) * | 2018-04-10 | 2018-09-25 | 西北工业大学 | A kind of short take-off and landing unmanned plane using distributed duct power |
| CN109263903A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of multifunction aircraft |
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Application publication date: 20191115 |