CN206645006U - Aircraft - Google Patents
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- CN206645006U CN206645006U CN201621347570.9U CN201621347570U CN206645006U CN 206645006 U CN206645006 U CN 206645006U CN 201621347570 U CN201621347570 U CN 201621347570U CN 206645006 U CN206645006 U CN 206645006U
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- fuselage
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- motor
- wing
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Abstract
The utility model discloses a kind of aircraft, including fuselage, wing, motor and propeller, fuselage has a plane of symmetry, the axis of fuselage and the center of gravity of aircraft are respectively positioned on the plane of symmetry of fuselage, wing is arranged on fuselage, motor is connected with fuselage and/or wing, a propeller is connected on the output shaft of each motor, wherein at least one motor can be around the axis rotation perpendicular to the fuselage plane of symmetry, motor driven propeller rotational produces the power to aircraft, can be to longitudinal lift caused by aircraft and to mutually being changed between horizontal force caused by aircraft.
Description
Technical field
It the utility model is related to a kind of aircraft.
Background technology
Fixed Wing AirVehicle and multi-rotor aerocraft are generally comprised in the common aircraft of aviation field.
Fixed Wing AirVehicle promotes by engine, and engine driving produces the horizontal thrust parallel to fuselage axis, makes fixation
Rotor aircraft can high-speed flight in the air.But because engine can not produce the lift perpendicular to fuselage axis, so fixed
Rotor aircraft can only obtain lift by the relative motion between fixed-wing and air, to overcome the gravity of Fixed Wing AirVehicle,
There is positive correlation in the speed of related movement between the size and Fixed Wing AirVehicle and air of lift, speed of related movement is got over
Greatly, the lift that Fixed Wing AirVehicle is obtained is also bigger.However, Fixed Wing AirVehicle of the prior art is scarce there is two
Point：First, need longer runway Fixed Wing AirVehicle is obtained enough horizontal velocities when taking off, so that fixed-wing flies
Row device obtains enough lift and taken off；Second, the flying speed that Fixed Wing AirVehicle needs to keep after take off enough can just obtain
Enough to lift to overcome the gravity of itself.
Multi-rotor aerocraft makes propeller pass through propeller rotation around own axes rotation, multi-rotor aerocraft by engine
When with air produce relative motion obtain lift.Because lift caused by multi-rotor aerocraft directly drives propeller certainly by engine
Then produce, therefore multi-rotor aerocraft takes off need not have horizontal flight speed, that is, eliminates the reliance on runway, overcome fixed-wing
The shortcomings that aircraft is relied on compared with long runway.Meanwhile multi-rotor aerocraft also overcomes and needs to keep after Fixed Wing AirVehicle takes off
The shortcomings that enough flying speeds, multi-rotor aerocraft can be vertically moved up or down, hovering, forwards, backwards left and right flight, had and flown
The diversified advantage of row posture.But due to the mainly lift provided during propeller rotation in multi-rotor aerocraft, more rotations
The horizontal thrust parallel to fuselage axis that rotor aircraft obtains is smaller, so horizontal flight speed is slower.
In summary, in the prior art, or aircraft needs to rely on long runway, and need holding is enough to fly after taking off
Scanning frequency degree；Horizontal flight speed is slower.
Utility model content
Main purpose of the present utility model there is provided one kind and combine Fixed Wing AirVehicle and multi-rotor aerocraft structure
Composite aircraft, it solves existing aircraft and limited and the slow-paced defect of horizontal flight by landing site.
To achieve the above objectives, the utility model provides a kind of aircraft, including fuselage, wing, motor and propeller,
The fuselage has a plane of symmetry, and the center of gravity of the axis of the fuselage and the aircraft is respectively positioned on the plane of symmetry of the fuselage
On, the wing is arranged on the fuselage, and the motor is connected with the fuselage and/or the wing, each electricity
A propeller is connected on the output shaft of machine, motor described in wherein at least one can be around perpendicular to the fuselage
The axis of the plane of symmetry rotates.
Further, the motor can connect the fuselage or the wing by support, and the support includes the first rotation
Bar and the second swingle, described first swingle one end are connected with the fuselage or the wing, and first swingle is another
End is connected with second swingle, and the motor is arranged on second swingle.
Further, the motor is connected with the wing, wherein first swingle and second swingle are hinge
Connect, the axis of first swingle is parallel to each other with the fuselage axis, the axis and the fuselage of second swingle
The plane of symmetry be parallel to each other.
Further, the motor is embedded in second swingle, and the output shaft of the motor passes second rotation
Bull stick is connected with the propeller.
Further, two motors are connected with the wing, two motors are respectively along the symmetrical of the fuselage
Face is symmetrical arranged, and two motors are located at the front side of the wing respectively.
Further, a motor is connected with the fuselage, the motor is arranged on the 3rd swingle, described
3rd swingle and the front end of the fuselage or rear end are hinged, and the axis of the 3rd swingle is located at the plane of symmetry of the fuselage
On.
Further, in other embodiments, in addition to empennage, the empennage include two connecting rods, two support plates and a connecting plate,
Two connecting rods are connected with the wing respectively, and two connecting rods are symmetrical arranged respectively along the plane of symmetry of the fuselage, often
The support plate is connected on the individual connecting rod, a connecting plate is connected between two support plates.
Further, the plane of symmetry of two support plates respectively with the fuselage is parallel to each other, the connecting plate and the support plate
It is arranged in a mutually vertical manner, and the connecting plate is located at the upside of the connecting rod.
Further, the distance between two described connecting rods are equal with the distance between two first swingles, and are located at
The connecting rod of described fuselage plane of symmetry the same side and first swingle are integrated.
Further, photoelectric nacelle is provided with the downside of the fuselage, camera is provided with the photoelectric nacelle.
According to preferred embodiment, the utility model offers the advantage that：
(1) aircraft of the present utility model combines the structure of Fixed Wing AirVehicle and multi-rotor aerocraft, wherein motor
Can be around the axis rotation perpendicular to the fuselage plane of symmetry, when propeller rotational is to when facing upward or downward setting, motor driven spiral shell
Revolve oar to rotate, longitudinal lift is produced to aircraft, when propeller rotational is to forward or when setting backwards, motor driven propeller turns
It is dynamic, lateral thrust or pulling force are produced to aircraft.
(2) aircraft of the present utility model has hovering ability, excellent without dependence, and zero velocity takeoff and anding etc. to runway
Point, and there is higher horizontal flight speed, and there is bigger voyage.
The utility model is further illustrated below in conjunction with drawings and Examples.
Brief description of the drawings
Fig. 1 is the stereogram of aircraft described in the utility model.
Embodiment
Describe to be used to disclose the utility model so that those skilled in the art can realize the utility model below.Retouch below
Preferred embodiment in stating is only used as illustrating, it may occur to persons skilled in the art that other obvious modifications.Retouched following
The general principle of the present utility model defined in stating can apply to other embodiments, deformation program, improvement project, etc. Tongfang
Case and the other technologies scheme without departing from spirit and scope of the present utility model.
Refering to accompanying drawing 1, a kind of aircraft according to the utility model preferred embodiment is shown, wherein the flight
Device can be piloted vehicle or unmanned vehicle.Especially, the aircraft be one combine fixed-wing flight
The structure of device and multi-rotor aerocraft, and possess Fixed Wing AirVehicle and the aircraft of multi-rotor aerocraft advantage respectively, such as,
The aircraft can longitudinally be taken off in a manner of multi-rotor aerocraft, be had to runway without dependence, possess hovering ability and
The advantages that zero velocity takeoff and anding, and can the horizontal flight in a manner of Fixed Wing AirVehicle, there is higher horizontal flight speed,
And there is bigger voyage.
The aircraft includes fuselage 1, wing 2, motor and propeller 4, and fuselage 1 has a plane of symmetry, the axis of fuselage 1
It is respectively positioned on the center of gravity of aircraft on the plane of symmetry of fuselage 1, wing 2 is set on the fuselage 1, the plane of symmetry of the wing 2 along fuselage 1
It is symmetrical arranged, motor is connected with fuselage 1 and/or wing 2, a propeller 4 is connected on the output shaft of each motor, its
In at least one motor can around perpendicular to the plane of symmetry of fuselage 1 axis rotation.The anglec of rotation can be 0 °~360 °, turn
During dynamic, when propeller 4 faces upward or downward setting, motor driven propeller 4 is rotated, and longitudinal lift is produced to aircraft,
When propeller 4 is facing forward or sets backwards, motor driven propeller 4 is rotated, and lateral thrust or pulling force are produced to aircraft.
Motor can connect fuselage 1 or wing 2, support 5 by support 5 includes the first swingle 6 and the second swingle 7, the
The one end of one swingle 6 is connected with fuselage 1 or wing 2, and the other end of the first swingle 6 is connected with the second swingle 7, and motor can be set
On the second swingle 7, in addition, motor can be also embedded in the second swingle 7, and the output shaft of motor passes the second swingle 7
It is connected with propeller 4.
In the present embodiment, motor is connected with wing 2, wherein the first swingle 6 and the second swingle 7 are be hinged, first
The axis of swingle 6 is parallel to each other with fuselage axis, and the axis of the second swingle 7 and the plane of symmetry of fuselage 1 are parallel to each other, i.e., and
Two swingles 7 can be 0 °~180 ° around the axis rotation perpendicular to the plane of symmetry of fuselage 1, the rotational angle.
In other embodiments, motor is connected with fuselage 1, wherein the plane of symmetry phase of the axis of the first swingle 6 and fuselage 1
Mutually vertical, the axis of the axis of the second swingle 7 and the first swingle 6 is mutually perpendicular to, and the second swingle 7 can be around first
The axis of swingle 6 rotates, and the anglec of rotation can be 0 °~360 °.
In the present embodiment, two motors are connected with wing 2, two motors are symmetrical along the plane of symmetry of fuselage 1 respectively
Set, and two motors can be located at the front side of wing 2 respectively.
In other embodiments, two motors can be located at the rear side of wing 2 respectively.
In the present embodiment, a motor is connected with fuselage 1, the motor may be provided on the 3rd swingle 13, and the 3rd
The rear end of swingle 13 and fuselage 1 is hinged, and wherein the axis of the 3rd swingle 13 is located on the plane of symmetry of fuselage 1, i.e., and the 3rd
Swingle 13 can be 0 °~180 ° around the axis rotation perpendicular to the plane of symmetry of fuselage 1, the rotational angle.In addition, motor is also
It can be embedded in the 3rd swingle 13, and the output shaft of motor passes the 3rd swingle 13 and is connected with propeller 4.
In the present embodiment, the 3rd swingle 13 can be mutually isostructural swingle with the second swingle 7.
In other embodiments, the motor connected on the fuselage 1 is located at the front end of fuselage 1.
The aircraft also includes empennage 9, and empennage 9 includes two connecting rods 10, two support plates 11 and a connecting plate 12, two connecting rods 10
It is connected respectively with wing 2, and two connecting rods 10 are symmetrical arranged respectively along the plane of symmetry of fuselage 1, are connected respectively on each connecting rod 10
There is support plate 11, a connecting plate 12 is connected between two support plates 11, wherein, two support plates 11 are mutually flat with the plane of symmetry of fuselage 1 respectively
OK, connecting plate 12 and support plate 11 are arranged in a mutually vertical manner, and the connecting plate 12 can be located at the upside of connecting rod 10.
In the present embodiment, the distance between two connecting rods 10 are equal with the distance between two first swingles 6, and are located at
The swingle 6 of connecting rod 10 and first of the plane of symmetry the same side of fuselage 1 can be integrated.
In other embodiments, the distance between two connecting rods 10 and the distance between two first swingles 6 are unequal.
Fuselage 1 can be package assembly with wing 2, specifically, the slot coordinated with wing 2, wing 2 are provided with fuselage 1
Embedded slot is connected with fuselage 1.The both ends of wing 2 can be respectively arranged with tapered wing winglet 3.
The downside of fuselage 1 is provided with photoelectric nacelle 8, and camera is provided with photoelectric nacelle 8.In addition, the inside of fuselage 1 may be used also
Lithium battery and flight control system etc. are provided with, the work such as lithium battery is camera, the first motor and second motor provides electric energy,
User can coordinate control aircraft flight by remote control and flight control system.
The blade of propeller 4 is two panels.
In other embodiments, aircraft also includes the common components such as elevator, aileron and rudder.
Foregoing motor operation, and the second swingle 7 can pass through remote control control around the rotation of the axis of the first swingle 6
System, the method for operating of the aircraft in the present embodiment is described below：
When taking off, the second swingle 7 is rotated, propeller 4 is faced upward or downward setting, then starts motor, motor driven
Propeller 4 is rotated, and upward longitudinal lift is provided for aircraft, when longitudinal lift caused by propeller 4 is more than the weight of aircraft
During power, aircraft starts to take off.
After taking off, after aircraft flight to certain altitude, the second swingle 7 is rotated, makes propeller 4 forward or sets backwards
Put, the propeller 4 now rotated by motor driven, produce the horizontal thrust or horizontal pull to aircraft, enter aircraft
Level flight condition.When aircraft needs hovering, the second swingle 7 is rotated, propeller 4 is faced upward or downward setting, now,
The propeller 4 that motor driven rotates provides upward longitudinal lift, when lift is equal to aircraft gravity, aircraft for aircraft
In floating state.After this, it can be coordinated by multiple motors, aircraft is realized that pitching, rolling or driftage etc. act.
During landing, the rotating speed of motor is reduced, reduces the longitudinal lift upward to aircraft, when lift is less than aircraft
During gravity, aircraft starts to land.
Embodiment described above is merely to illustrate technological thought of the present utility model and feature, and its object is to make ability
Technical staff in domain can understand content of the present utility model and implement according to this, it is impossible to only limit this practicality with the present embodiment
New the scope of the claims uses, i.e., the equal change or modification that all spirit according to disclosed in the utility model is made, still falls at this
In the scope of the claims of utility model.
Claims (3)
- A kind of 1. aircraft, it is characterised in that including fuselage (1), wing (2), motor and propeller (4), fuselage (1) tool There is a plane of symmetry, the axis of the fuselage (1) and the center of gravity of the aircraft are respectively positioned on the plane of symmetry of the fuselage (1), institute State wing (2) to be arranged on the fuselage (1), be connected with the motor on the fuselage (1) and/or the wing (2), each A propeller (4) is connected on the output shaft of the motor, motor can be around vertical described in wherein at least one Rotated in the axis of the fuselage (1) plane of symmetry；Two motors are connected with the wing (2), are connected to two motors on the wing (2) respectively along institute The plane of symmetry for stating fuselage (1) is symmetrical arranged, and two motors are located at the front side of the wing (2), two institutes respectively The wing (2) can be connected by support (5) respectively by stating motor, and the support (5) includes the first swingle (6) and the second rotation Bar (7), axis and the fuselage axis of first swingle (6) are parallel to each other, the axis of second swingle (7) and The plane of symmetry of the fuselage (1) is parallel to each other, and described first swingle (6) one end is connected with the wing (2), first rotation Bull stick (6) other end is be hinged with second swingle (7), and the motor is arranged on second swingle (7)；A motor is connected with the fuselage (1), the motor being connected on the fuselage (1) is arranged on the 3rd rotation On bull stick (13), the front end or rear end of the 3rd swingle (13) and the fuselage (1) are hinged, the 3rd swingle (13) Axis be located on the plane of symmetry of the fuselage (1)；Also include empennage (9), the empennage (9) includes two connecting rods (10), two support plates (11) and a connecting plate (12), two companies Bar (10) is connected with the wing (2) respectively, and two connecting rods (10) symmetrically set respectively along the plane of symmetry of the fuselage (1) Put, be connected to the support plate (11) on each connecting rod (10), a company is connected between two support plates (11) Fishplate bar (12), the plane of symmetry of two support plates (11) respectively with the fuselage (1) are parallel to each other, the connecting plate (12) and described Support plate (11) is arranged in a mutually vertical manner, and the connecting plate (12) is located at the upside of the connecting rod (10), two connecting rods (10) it Between distance it is equal with the distance between two first swingles (6), and positioned at the fuselage (1) plane of symmetry the same side The connecting rod (10) and first swingle (6) are integrated.
- 2. aircraft as claimed in claim 1, it is characterised in that the motor is embedded in second swingle (7), and institute The output shaft for stating motor passes second swingle (7) and is connected with the propeller (4).
- 3. aircraft as claimed in claim 1, it is characterised in that be provided with photoelectric nacelle (8), institute on the downside of the fuselage (1) State in photoelectric nacelle (8) and be provided with camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621347570.9U CN206645006U (en) | 2016-12-09 | 2016-12-09 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621347570.9U CN206645006U (en) | 2016-12-09 | 2016-12-09 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206645006U true CN206645006U (en) | 2017-11-17 |
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ID=60282326
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621347570.9U Active CN206645006U (en) | 2016-12-09 | 2016-12-09 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206645006U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108557088A (en) * | 2018-06-12 | 2018-09-21 | 翟占超 | Aircraft |
-
2016
- 2016-12-09 CN CN201621347570.9U patent/CN206645006U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108557088A (en) * | 2018-06-12 | 2018-09-21 | 翟占超 | Aircraft |
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