CN110723284A - Vertical lifting fixed wing aircraft with tiltable ducted fan - Google Patents
Vertical lifting fixed wing aircraft with tiltable ducted fan Download PDFInfo
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- CN110723284A CN110723284A CN201810780992.2A CN201810780992A CN110723284A CN 110723284 A CN110723284 A CN 110723284A CN 201810780992 A CN201810780992 A CN 201810780992A CN 110723284 A CN110723284 A CN 110723284A
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- aircraft
- ducted
- ducted fan
- wing
- fans
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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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
Abstract
The invention discloses a vertical lifting fixed wing aircraft with tiltable ducted fans, wherein the tiltable ducted fans 5 and 9 are respectively arranged above the outer sides of the rear edges of the left front wing and the right front wing of the aircraft, the tiltable ducted fan 6 is arranged in the middle of the outer side tail wing at the edge of the tail part, and the ducted fans 5, 6 and 9 are electrically driven; when the axes of the ducted fans 5, 6 and 9 are in the vertical direction, the magnitude of the lift force determines the ascent or descent of the aircraft in the vertical direction; when the aircraft takes off vertically, the ducted fans rising to a preset height start to rotate obliquely and synchronously to generate forward component force, the aircraft flies horizontally forwards, when the ducted fans rotate to the horizontal direction, the fixed wings generate lift force, the ducted fans provide thrust, and the aircraft flies in a cruising way; when the aircraft vertically lands, the ducted fans synchronously rotate in the vertical direction, the horizontal flying speed is gradually reduced to zero, and the output aircraft of the ducted fans is controlled and reduced to start to land.
Description
Technical Field
The invention relates to a vertical lifting fixed wing aircraft, in particular to a vertical lifting fixed wing aircraft adopting a tiltable rotary ducted fan.
Background
The fixed wing aircraft and the rotor helicopter have various characteristics, the aircraft combining the rotor for vertical lifting and the fixed wing is applied, the vertical lifting fixed wing aircraft is developed by benefiting from the perfection of flight control technology, and the aircraft capable of vertical lifting and cruising and flying has the advantages of two aircrafts.
One type of the vertical lifting fixed wing aircrafts is a tailstock type vertical lifting fixed wing aircraft, the aircraft is in a vertical state when taking off, the aircraft is turned into flat flight after rising to a certain height, the aircraft body is required to be turned into a vertical state from the flat flight state when landing, the gravity center position of the whole aircraft is changed when the aircraft body is changed in posture, and the application is limited.
The vertical lifting fixed wing aircraft has the advantages that the horizontal rotors are assembled on the fixed wings, mainly work in the ascending and descending stages of the aircraft, the propellers at the tail of the aircraft push the aircraft to rotate into flat flight, the horizontal rotors stop working or are only used for posture adjustment when the aircraft is in the flat flight, and the horizontal rotors rely on the fixed wings to obtain lift force in the flat flight stage of the aircraft, so that the aircraft type can realize longer flight time and is mainly used for small-sized aircraft.
The rotary wing and the fixed wing which can rotate obliquely are combined to have more applications, the taking-off and landing characteristics of the rotary wing aircraft and the basic advantages of the fixed wing aircraft are better reflected, the conversion of the rotary wing fixed wing aircraft with the oblique rotation between vertical taking-off and landing and flat flying can be well transited, and the aircraft has good application prospect; the common aircraft with the rotors to independently rotate in an inclined mode changes the lift force and adjusts the posture by controlling the rotation speed of the rotors in the taking-off and landing stages, the inclination angle of the rotors is changed in the lifting and flat flying conversion stages, the vertical component force and the forward component force are changed accordingly, when the aircraft enters flat flying, the rotors rotate in an inclined mode to the forward flying direction, the rotors mainly generate forward thrust, and the fixed wings generate the lift force; there is also an aircraft in which a rotor rotates obliquely together with a fixed wing.
The defects that the small and medium-sized rotor aircrafts are easy to collide and damage blades because the rotor wing position is lower, and even safety accidents occur because personnel approach, and many aircrafts are additionally provided with rotor wing protection rings; the protection of the rotors of tiltably rotatable rotor fixed-wing aircraft is difficult due to the need for tilting.
The rotor of the medium and large rotor aircraft has a large diameter, and can not rotate to the position of horizontal thrust during takeoff, so that the fixed wing is difficult to realize running takeoff.
The ducted fan is an aviation power source, benefits from the improvement of modern flight control technology, and the replacement of a rotor wing by the ducted fan capable of rotating obliquely provides a feasible technical scheme for the design of a novel aircraft.
Hybrid/distributed electric drive is the development direction of future aircrafts, the electric ducted fans which can be flexibly distributed can increase the equivalent ducted ratio of the turbine generator, and the adoption of the electric ducted fans is an important technical direction.
Disclosure of Invention
In order to overcome the defect that the tiltable rotor fixed wing aircraft is difficult to run and take off, the ducted fan is selected as the power of the aircraft, and because the blades of the ducted fan are arranged in the duct, the blades of the fan are protected, and the approaching personnel are safer,
the ducted fan is designed to be capable of obliquely rotating, and is combined with the fixed-wing aircraft, so that the fixed-wing aircraft can run and take off and land in a short distance by utilizing the fixed wings when bearing a large load, and the aircraft can save energy by utilizing the lifting force of the fixed wings during cruising, and the range of the aircraft is increased.
The invention is realized by the following technical scheme:
the invention selects to arrange the ducted fan on the upper part of the outer side of the rear edge of the front wing on the left side and the right side of the aircraft body, and arrange the ducted fan on the upper part of the outer side of the rear edge of the tail, and the center of lift force generated by the ducted fan is basically coincident with the center of gravity of the aircraft and the center of lift force of the front fixed wing and the rear fixed wing during vertical take-off and landing, so that the stability of the aircraft is good, and the safety is improved.
Rotating shafts are arranged at two ends of the waist of the ducted fan, and the rotating shaft at one end controls the ducted fan to rotate obliquely through an output shaft of a machine body and positions an initial angle; because the load of the aircraft is transmitted to the ducted fan providing the lift force through the rotating shaft, the mass of the fixed wing is also the load of the ducted fan when the aircraft vertically takes off and lands, if the rotating shaft of the ducted fan is designed to be a single-end cantilever, the single-end cantilever rotating shaft can bear larger bending moment, and in order to reduce the bending moment borne by the rotating shaft, a supporting frame is arranged on the main wing to provide support for the rotating shaft at the other end of the ducted fan, and the reinforced main wing shares the load of the rotating shaft of the ducted fan.
Preferably, the ducted fan which can be obliquely rotated and is selected by the invention is driven by electric power, and the layout and the regulation of the ducted fan are flexible.
Preferably, the tiltable ducted fan is arranged above the outer sides of the rear edges of the left and right front wings, and when the ducted fan inclines forwards and is parallel to the fuselage in cruising flight, the air inlet of the ducted fan is positioned above the main wing without air inlet obstacle; the air flow at the air outlet avoids the main wing and the airframe, and no air flow disturbance exists.
Preferably, the ducted fan which is arranged on the upper part of the outer sides of the rear edges of the left and right front wings and can rotate obliquely is vertical to the fuselage when the aircraft is vertically lifted and landed, the air inlet of the ducted fan is positioned above the main wing without air inlet obstacles, the air outlet of the ducted fan is positioned on the outer side of the rear edge of the main wing, and the air flow of the air outlet avoids the main wing without air flow disturbance.
Preferably, the spatial position of the obliquely rotatable ducted fan arranged above the outer sides of the rear edges of the left and right front wings ensures that the air inlet of the ducted fan has no air inlet obstacle in the oblique rotation angle range, and the air outlet of the ducted fan keeps away from the fuselage and the front and rear wings.
Preferably, when the ducted fan arranged at the tail part of the aircraft is inclined forwards to be parallel to the aircraft body during cruising flight, the air inlet of the ducted fan is positioned above the tail part of the aircraft body, no air inlet obstacle exists, the air outlet is positioned outside the tail part of the aircraft body, and the air flow avoids the aircraft tail.
Preferably, the ducted fan arranged at the tail part of the aircraft rotates upwards to be vertical to the aircraft body when the aircraft vertically takes off and lands, the air inlet is free of air inlet obstacles, the air outlet is positioned outside the tail part of the aircraft body, and the air flow at the air outlet avoids the aircraft tail.
Preferably, the spatial position of the tiltable ducted fan arranged on the upper part of the outer side of the rear edge of the tail ensures that an air inlet of the ducted fan has no air inlet obstacle in the tilting and rotating angle range, and an air outlet of the tiltable ducted fan keeps away from and faces the fuselage and the front and rear wings.
Preferably, the axes of the plurality of ducted fans which are capable of tilting and rotating are positioned at the same angle as the axis of the body when being installed, and synchronous tilting and rotating are ensured.
Preferably, the tiltable ducted fans can be respectively regulated by the motors to realize the attitude control of the aircraft. Compared with the prior art, the invention has the following advantages:
1. the lift force of the fixed-wing aircraft is fully utilized, so that the energy is saved, the range is increased, and the conversion between vertical take-off and landing and horizontal flight is realized through synchronous inclined rotation of the ducted fans;
2. the ducted fans arranged on the left and right sides of the aircraft body enable the left and right balance of the aircraft to be easily adjusted, and the ducted fans arranged on the tail of the aircraft body enable the front and back balance of the aircraft to be easily controlled, so that the stability of the aircraft is guaranteed;
3. because the ducted fans are positioned at the same angle and synchronously rotate in an inclined manner, the aircraft is always in a stable state in the transition process of vertical take-off and landing and horizontal flight conversion, and the safety of the aircraft is improved;
4. when the ducted fan and the fuselage keep a proper elevation angle, the aircraft can realize the gliding take-off and landing of the short runway under the heavy load.
Drawings
FIG. 1 is a vertical view of a ducted fan and a fuselage of an aircraft according to the present invention;
FIG. 2 is a diagram illustrating the ducted fan tilted during the transition between vertical take-off and landing and flat flight of the aircraft according to the present invention;
FIG. 3 is a view of the parallel state of the axial line of the ducted fan and the axial line of the aircraft body when the aircraft is cruising.
In the drawings: the aircraft comprises an aircraft body, an aircraft left front wing, an aircraft body, an aircraft right front wing, a supporting frame of a duct fan on the aircraft right front wing, a duct fan 5 on the aircraft right front wing, a duct fan 6 on the aircraft tail, a V-shaped empennage 7, a supporting frame of the duct fan on the aircraft tail and the V-shaped empennage 7, a duct fan 9 on the aircraft left front wing, a supporting frame of the duct fan on the aircraft left front wing 10, and an aircraft landing gear with pulleys 11.
Detailed Description
The present embodiment is carried out on the premise of the present invention with reference to the drawings, and the detailed description is given, but the scope of the present invention is not limited to the following embodiments.
As shown in FIG. 1, the invention firstly designs a left front wing 1 and a right front wing 3 at the front part of an aircraft body 2, and designs a V-shaped empennage 7 at the tail part of the aircraft body 2, thereby meeting the basic aerodynamic layout of the aircraft; the electrically driven ducted fans 5, 6 and 9 are adopted to provide flight power, in order to meet the requirements of the aircraft on vertical take-off and landing, the ducted fans 5, 6 and 9 are designed to rotate obliquely around a rotating shaft, in order to keep the aircraft in safe and stable transition in the processes of vertical take-off and landing and flat flight, the ducted fan 6 is arranged in the middle of the tail part of the aircraft body 2, and the positions of the ducted fans 5, 6 and 9 form 3-point type layout of the aircraft which is easy to balance and stable.
As shown in fig. 1, when the aircraft takes off vertically, the ducted fans 5, 6 and 9 rotate to the vertical position, when the ducted fans 5, 6 and 9 operate, negative pressure is formed at the air inlet at the front end of the ducted to generate suction, and air flow is ejected at the air outlet at the rear end of the ducted to generate thrust, when the ascending force generated thereby is greater than the total weight of the aircraft, the aircraft starts to ascend, and during the ascending process of the aircraft, the flight control system respectively changes the output forces of the ducted fans 5, 6 and 9 by adjusting the rotation speed of the motor, so as to maintain the balance of the aircraft.
When the aircraft descends vertically, the ducted fans 5, 6 and 9 are also at a position vertical to the fuselage 2, so that the output of the ducted fans 5, 6 and 9 is reduced, the balance of the aircraft is kept, and the aircraft descends stably.
As shown in fig. 2, when the aircraft ascends to a set altitude, the ducted fans 5, 6 and 9 start to rotate forwards and forwards synchronously, the force generated by the ducted fans 5, 6 and 9 is decomposed into lift force and forward thrust force, the aircraft obtains the power of the forward flight while maintaining the altitude, the aircraft gradually transits to horizontal flight, when the horizontal flight reaches a certain speed, the lift force generated by the fixed wings 1, 3 and 7 is large enough for the aircraft to enter cruise flight, and the ducted fans 5, 6 and 9 gradually rotate to provide the thrust force in a direction parallel to the fuselage 2.
When the aircraft finishes cruising flight and reaches a preset position, the aircraft reduces the flight speed, the aircraft enters a horizontal flying to vertical landing state, the ducted fans 5, 6 and 9 start to gradually rotate obliquely, the force generated by the ducted fans 5, 6 and 9 is decomposed into forward thrust and vertical lift force, the forward thrust is gradually reduced, the vertical lift force is increased, and finally the forward thrust and the vertical lift force are all converted into the vertical lift force, so that stable landing is realized.
When the aircraft enters cruise flight, as shown in fig. 3, the lift generated by the fixed wings 1, 3 and 7 is enough to bear the total weight of the aircraft, the axes of the ducted fans 5, 6 and 9 rotate parallel to the axis of the fuselage 2, and the aircraft can obtain a large thrust-weight ratio because the thrust generated by the ducted fans 5, 6 and 9 is large enough.
As shown in fig. 1, 2 and 3, the ducted fans 5, 6 and 9 are set in spatial positions within the angular range of the oblique rotation, so that air inlets of the ducted fans are free from air inlet obstacles, air outlets of the ducted fans are all kept away from the fuselage 2, and the air outlets are also kept away from the front wings 1 and 3 and the V-shaped empennage 7 completely.
10 is a supporting frame of the ducted fan 9 on the left front wing 1, and is used for supporting a rotating shaft at one end of the ducted fan 9; 4 is a supporting frame of the ducted fan 5 on the right front wing 3, which is used for supporting a rotating shaft at one end of the ducted fan 5; the reference numeral 8 denotes a support frame for the ducted fan 6 at the rear of the body 2, and the support frame 8 also serves as a support for the V-shaped empennage 7.
The ducted fans 5, 6 and 9 of the aircraft designed by the invention are controlled by a synchronous transmission device in the aircraft body to realize the same-angle positioning and synchronous inclined rotation, the ducted fan 5 is driven by a rotating shaft output from the right side of the aircraft body 2, the ducted fan 9 is driven by a rotating shaft output from the left side of the aircraft body 2, and the ducted fan 6 is driven by a rotating shaft output from one end of a supporting frame 8.
The ducted fans 5, 6 and 9 of the aircraft designed by the invention can respectively adjust the rotating speed of the motor, and are used for changing the thrust of the fan so as to realize the attitude control of the aircraft.
The aircraft designed by the invention is provided with the landing gear 11 with the pulley, and the aircraft can take off through short-distance running under heavy load, so that the problem that the load needs to be reduced when the aircraft takes off and lands vertically is solved.
Claims (10)
1. The utility model provides a vertical lift fixed wing aircraft of installation tiltable rotatory duct fan which characterized in that: the aircraft is provided with a ducted fan 9 capable of rotating obliquely above the outer side of the rear edge of the left main wing 1, the aircraft is provided with a ducted fan 5 capable of rotating obliquely above the outer side of the rear edge of the right main wing 3, the aircraft is provided with a ducted fan 6 capable of rotating obliquely above the outer side of the rear edge of the tail part of the fuselage 2, the axes of the ducted fans 5, 6 and 9 are arranged at the same angle relative to the axis of the fuselage and rotate obliquely synchronously, the lift force generated by the ducted fans 5, 6 and 9 is basically coincident with the gravity center of the aircraft and the lift force centers of the front and rear fixed wings during vertical take-off and landing, and the layout characteristics of the ducted fans 5, 6 and 9 comprise:
a. when the ducted fans 5 and 9 are obliquely and forwardly parallel to the fuselage 2, the air inlets of the ducted fans are positioned above the main wings 1 and 3, no air inlet obstacle exists, and the air flows at the air outlets of the ducted fans keep away from and face the fuselage 2, the front wings 1 and 3 and the V-shaped empennage 7;
b. when the ducted fans 5 and 9 rotate upwards and are vertical to the machine body 2, air inlets of the ducted fans are free of air inlet obstacles, air outlets of the ducted fans are positioned outside the rear edges of the main wings 1 and 3, air flow of the air outlets avoids the main wings 1 and 3, and the rear edges of the main wings 1 and 3 are designed into an arc shape matched with the ducted fans;
c. in the process of oblique rotation of the ducted fans 5 and 9, air inlets are free of air inlet obstacles, and air flows at air outlets avoid facing the fuselage 2, the front wings 1 and 3 and the V-shaped empennage 7;
d. when the ducted fan 6 rotates forwards to be parallel to the fuselage 2, the air inlet of the ducted fan is positioned above the tail part of the fuselage 2, no air inlet obstacle exists, and the air flow at the air outlet avoids and directly faces the fuselage 2 and the V-shaped empennage 7;
e. when the ducted fan 6 rotates upwards to be vertical to the fuselage 2, the air inlet of the ducted fan is positioned above the tail part of the fuselage 2, no air inlet obstacle exists, the air outlet of the ducted fan is positioned outside the rear edge of the tail part of the fuselage 2, the air flow of the air outlet avoids the tail part of the fuselage 2, and the rear edge of the wing is designed into an arc shape matched with the ducted fan;
f. in the process of oblique rotation of the ducted fan 6, air inlets are free of air inlet obstacles, and air flow at air outlets avoids and directly faces the machine body 2 and the V-shaped empennage 7.
2. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the ducted fans 5, 6 and 9 may each be of a construction in which a plurality of identical ducted fans are combined in parallel.
3. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the fans in the duct are all directly driven by the electric motor, and the rotating speed of the fans can be adjusted by the electric motor respectively to control airflow, so that the attitude of the aircraft can be adjusted.
4. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the tiltable axes of rotation of the ducted fans 5, 6 and 9 project on either side of their waists and are perpendicular to the axis of the ducted fan.
5. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the ducted fan 5 is driven by the rotating shaft output from the right side of the machine body 2, the ducted fan 9 is driven by the rotating shaft output from the left side of the machine body 2, and the ducted fan 6 is driven by the rotating shaft output from one end of the supporting frame 8.
6. The fixed-wing, vertical lift, tiltable ducted aircraft according to claim 5, wherein: the rotation shaft controlling the oblique rotation of the ducted fans 5, 6 and 9 ensures that the axes of the ducted fans 5, 6 and 9 are positioned at the same angle with the axis of the fuselage 2 and are rotated obliquely in synchronization.
7. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the main wings 1 and 3 are provided with support frames 4 and 10 for ducted fans, the right end rotation shaft of the ducted fan 5 is supported by the support frame 4 standing on the upper surface of the right main wing 3, and the left end rotation shaft of the ducted fan 9 is supported by the support frame 10 standing on the upper surface of the left main wing 1.
8. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the two sides of the supporting frame 8 at the tail part of the fuselage 2 are used as the supports of the shafts at the two ends of the ducted fan 6, wherein one side of the supporting frame provides the synchronous inclined rotation torque with the ducted fans 5 and 9 at the same time of supporting.
9. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the supporting frame 8 arranged at the tail part of the machine body 2 is used for supporting the ducted fan 6, and the supporting frame 8 is also used for supporting the V-shaped empennage 7.
10. The fixed-wing, vertical lift, tiltable ducted fan aircraft as in claim 1, wherein: the undercarriage 11 with pulleys is arranged under the fuselage and is used for short-distance running landing and taking off of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810780992.2A CN110723284A (en) | 2018-07-17 | 2018-07-17 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810780992.2A CN110723284A (en) | 2018-07-17 | 2018-07-17 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
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| CN110723284A true CN110723284A (en) | 2020-01-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810780992.2A Pending CN110723284A (en) | 2018-07-17 | 2018-07-17 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
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Cited By (5)
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| CN111516867A (en) * | 2020-05-13 | 2020-08-11 | 陈厚然 | Multi-power-mode fixed-wing aircraft |
| CN112498660A (en) * | 2020-12-24 | 2021-03-16 | 中国直升机设计研究所 | Duck wing high-speed tilt rotor aircraft and control method thereof |
| CN113022847A (en) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | High-speed helicopter with vector duct tail rotor |
| CN114194388A (en) * | 2021-11-23 | 2022-03-18 | 上海羽天航空科技有限公司 | Novel vertical take-off and landing fixed wing aircraft |
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
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| CN113022847A (en) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | High-speed helicopter with vector duct tail rotor |
| CN114194388A (en) * | 2021-11-23 | 2022-03-18 | 上海羽天航空科技有限公司 | Novel vertical take-off and landing fixed wing aircraft |
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
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Application publication date: 20200124 |