CN112498660B - Duck wing high-speed tilt rotor aircraft and control method thereof - Google Patents
Duck wing high-speed tilt rotor aircraft and control method thereof Download PDFInfo
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- CN112498660B CN112498660B CN202011555418.0A CN202011555418A CN112498660B CN 112498660 B CN112498660 B CN 112498660B CN 202011555418 A CN202011555418 A CN 202011555418A CN 112498660 B CN112498660 B CN 112498660B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Abstract
The invention belongs to the technical field of aircrafts, and discloses a canard high-speed tilt rotor aircraft and an operation method thereof, wherein the canard high-speed tilt rotor aircraft comprises the following steps: the aircraft comprises an aircraft body, a front canard wing, a rear wing, a front rotor wing, a rear tilting rotor wing and a tilting mechanism; the front canard wing and the front rotor wing are arranged at the front part of the fuselage, wherein the front rotor wing is arranged in a through hole of the front canard wing, and the rear wing is arranged at the rear part of the fuselage; the rear tilt rotor wing is installed at the rear part of the center of gravity of the aircraft body through a tilt mechanism and is positioned in front of the rear wing. Compared with helicopters, autorotation gyroplanes and multi-rotor aircrafts, the aircraft body posture does not need to be additionally inclined by adjusting the inclination angle of the tilting thrust rotor, and the front rotor on the front canard under the horizontal flying mode is closed to form the canard fixed wing aircraft, so that the front flying resistance is small, and the speed is obviously improved; the thrust of the invention comes from the retroverted rotor in the flat flying mode, the diameter of the rotor is smaller than that of the tilt rotor aircraft, the resistance is small in the forward flying process, and the speed is higher.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a canard high-speed tilt rotor aircraft and an operation method thereof.
Background
In a helicopter type aircraft, a conventional helicopter and a coaxial helicopter both obtain forward flight thrust by inclining an angle of a main rotor, forward flight resistance can be increased when the main rotor inclines, a fuselage is required to incline downwards to further increase a forward inclination angle of the main rotor to obtain more thrust when the forward flight speed is high, and flight resistance can be further increased when the fuselage is too low, so that the forward flight speed of the helicopter is low, the fuselage is in a head-down state when the helicopter flies forwards, and the riding comfort is also insufficient.
The combined helicopter is characterized in that a propulsion paddle is additionally arranged on the basis of a conventional helicopter or a coaxial helicopter to enhance thrust, the inclination angle of a main rotor is reduced, so that the speed is increased greatly, the forward inclination angle of a helicopter body is also relieved, but because the combined helicopter adopts two pairs of main rotors, the resistance cannot be further reduced, the high-speed potential is limited, the size of the main rotor of the helicopter is large, the requirement on the size of a take-off and landing site is high, and meanwhile, the take-off and landing safety is also influenced by exposed blades.
The self-rotating gyroplane has low rotating speed and low noise because the rotor is in a self-rotating state; however, the size of the rotor wing is large, the requirements on taking-off and landing sites are larger, and a part of models also need short-distance running taking-off; and the large-size rotor wing has large resistance, the flying speed is lower than that of the conventional helicopter, and the timeliness is poorer.
Many rotor crafts class aircraft make the frontal area grow lead to the resistance to increase because of body slope makes before flying, and body slope too greatly can influence the balanced event of flight and can't provide bigger thrust, it flies the thrust and receives the restriction before it, many rotor unmanned aerial vehicle fly the resistance before big and preceding thrust not enough, preceding flight speed is low, many rotor aircraft of combined type make the resistance reduce to some extent through increasing the propulsion oar, but because many rotor aircraft's exposed screw is many, body configuration resistance is big, so no matter be unmanned aerial vehicle or manned vehicle, speed all is about 100 km/h.
Because the propulsion device of the tilt rotor unmanned aerial vehicle needs to take the take-off, landing and forward flying states into consideration, the diameter of the rotor of the propulsion device is large, the resistance is large in the forward flying mode, and the further improvement of the forward flying speed is influenced; because the propelling device is arranged on the wing, the action point of the total lifting force is only at the position of the wing, the adjustable range of the center of gravity of the whole aircraft along the axial direction of the aircraft body is small, and the requirement on the position of the center of gravity of the loaded task equipment is high.
Conventional fixed wing configuration tiltrotor aircraft realizes fixed wing aircraft and four rotor aircraft's combination through increasing four rotor mechanisms in fixed wing both sides, implements simply, nevertheless has the big problem of configuration resistance, so high-speed performance is poor, only is applied to on the unmanned aerial vehicle at present.
And, many rotor unmanned aerial vehicle and above-mentioned two kinds of rotor below organism support piece that vert rotor unmanned aerial vehicle are connected to the organism, can produce the hindrance to the downward air current of rotor for advancing device's the efficiency reduction of taking off and land and hovering.
The lift body configuration tilt rotor aircraft realizes the conversion of vertical take-off and landing and horizontal forward flight through the tilt tail duct, and further closes the lift duct when the aircraft flies forward at a high speed, so the resistance of the whole aircraft is small, but the tail tilt duct is arranged behind the aircraft wing and is far away from the gravity center, so the tilt thrust occupies a small ratio in the whole lift, and the further improvement of the flight speed is influenced; meanwhile, the tail duct is installed at the rear part of the wing, the installation part is weak in structure, the force transmission characteristic is to be improved, and if the tail duct is independently reinforced, the weight of the whole aircraft is increased, so that the weight efficiency of the whole aircraft is influenced.
Disclosure of Invention
Aiming at the problems in the background technology, the technical scheme of the invention provides a method for operating a canard wing high-speed tilt rotor aircraft, and compared with helicopters, autorotation rotor aircraft and multi-rotor aircraft, the inclination angle of a tilt thrust rotor is adjusted to ensure that the aircraft body does not need to be additionally tilted in flight, and the front rotor on the front canard wing in a flat flight mode is closed to form the canard wing type fixed wing aircraft, so that the front flight resistance is small, and the speed is remarkably improved; the thrust of the aircraft comes from the backward-tilting rotor in the flat flight mode, the diameter of the rotor is smaller than that of the aircraft with the tilting rotor, the resistance is small during forward flight, and the speed is higher. Furthermore, the canard wing adopts an active jet flow control technology, so that the lift force can be increased, and the resistance of the rear wing is reduced. And can realize VTOL and low-speed flight under the folding condition of wing and canard for the aircraft more adapts to narrow and small space's use.
In order to achieve the purpose, the invention adopts the following technical scheme to realize.
The first technical scheme is as follows:
the utility model provides a high-speed rotor craft that verts of duck wing which characterized in that includes: the aircraft comprises an airframe 1, a front canard wing 2, a rear wing 3, a front rotary wing 4, a rear tilting rotary wing 5 and a tilting mechanism 6;
the front canard wing 2 and the front rotor wing 4 are arranged at the front part of the fuselage 1, the front rotor wing 4 is positioned at the inner side of the front canard wing 2, and the rear wing 3 is arranged at the rear part of the fuselage 1; the rear tilt rotor wing 5 is arranged at the rear part of the gravity center of the fuselage 1 through a tilt mechanism 6 and is positioned in front of the rear wing 3;
the front duck wing is of an elliptical wing shape, and when the front duck wing adopts active jet flow control to close a rotor duct of the front duck wing, the tail chord length of the front duck wing is increased, so that the lift center of the front duck wing is consistent with that of the front duck wing during vertical take-off and landing.
The technical scheme of the invention has the characteristics and further improvements that:
(1) The aircraft further comprises: a front duck wing spout 7, a rear control surface 8 and a tail wing 9;
wherein, the front duck wing spout 7 is arranged on the front duck wing 2, the rear rudder surface 8 is arranged on the rear wing 3, and the tail wing 9 is arranged on the rear wing 3.
(2) The front duck wing jet flow port 7 comprises four groups of jet flow ports, the four groups of jet flow ports are respectively positioned on the front edge of the wing section of the front duck wing, the position 5% -10% behind the maximum thickness of the wing section, the chord length position 70% -80% of the wing section and the tail part of the wing section, each group of jet flow ports are connected with a flow guide hole in a duct of the front rotor wing through a pipeline, jet flow is generated by air entraining from the front duct, and the size and the angle of the jet flow are controlled through a valve in the pipeline.
Specifically, the front rotor 4 is located on the inner side of the front duck wing 2, the front duck wing jet flow ports are divided into 4 groups and can be increased and decreased according to specific use requirements, the typical 4 groups of jet flow ports are respectively located on the front edge of the wing profile of the front duck wing, 5% -10% of the position behind the maximum thickness of the wing profile, 70% -80% of chord length of the wing profile and the tail of the wing profile, the jet flow ports are connected with the flow guide holes 42 in the duct of the front rotor 4 through a pipeline, jet flow is generated by air bleed from the front duct, the size and the angle of the jet flow are controlled through a valve in the pipeline, the chord length increase, the resistance decrease and the wing profile curvature change, namely, the duck wing deflection effect is generated, and the pitching operation effect is realized. The active control effect of the flow field of the jet flow realizes the deflection effect of the control surface of the duck wing, so that the duck wing can adopt an elliptical wing shape to shorten the actual chord length of the duck wing, the weight is reduced, the thickness of the duct is increased on the basis of the same chord length to improve the lift increasing effect of the duct, and the lift efficiency is improved. In addition, according to the technical scheme of the invention, the increase of the tail chord length of the duck wing is realized by actively controlling the jet flow when the rotor duct of the front duck wing is closed, so that the lift center of the duck wing in vertical take-off and landing is consistent with that of the front fly wing, and the flight attitude of the whole aircraft is easier to control.
(3) Behind the center of gravity of the fuselage 1, the retroverted rotor 5 is tiltable between a lift direction and a thrust direction by the driving of the tilting mechanism 6; the ratio of the distance from the center of lift of the rear tilting rotor 5 to the center of gravity of the aircraft to the distance from the center of lift of the front rotor 4 to the center of gravity of the aircraft is 1.
Defining the vertical direction of the fuselage to be 0 degree, the forward tilting angle to be positive, the backward tilting angle to be negative, the forward tilting to the horizontal direction to be 90 degrees, and the backward tilting to the horizontal direction to be-90 degrees; the tilting range of the retroverted rotor 5 is-15 degrees to 105 degrees.
(4) The backward-tilting rotor wing 5 is positioned in a cross space of the back wing and the fuselage, the backward-tilting of the fuselage 1 and the back wing 3 just avoids the down-wash airflow of the backward-tilting rotor wing 5, and most of the jet flow of the backward-tilting rotor wing 5 is at the top of the back wing 3 in the forward-flying state, so that the wing lift can be effectively improved. The sweep angle of the aft wing 3 ranges between 20 degrees and 60 degrees.
(5) The front rotor 4 is covered by a cover plate mechanism to form a whole duck wing, and the openable air-entraining port 43 reserved at the top when the duct of the front rotor is closed is used for continuously generating jet flow to realize active control of a flow field when the duct of the front rotor flies forwards, so that the utilization efficiency of the front rotor 4 can be improved, the front rotor 4 can continuously play a role when the duct flies forwards, and the lift and the drag reduction of the whole machine are realized.
The second technical scheme is as follows:
a fast aircraft operation method is applied to the aircraft in the first technical scheme, when the aircraft vertically takes off and lands or hovers and flies at a low speed, the axis of a retroversion rotor wing 5 tilts to be vertical to the axis of a fuselage 1 to generate downward thrust, the retroversion rotor wing and a front rotor wing 4 jointly provide lift force, the vertical taking off and landing or hovering and the low-speed flight of the aircraft are realized, and the forward and backward movement of the aircraft are realized by adjusting the tilting angle of the retroversion rotor wing 5.
The second technical scheme of the invention has the characteristics and further improvements that:
(1) When the aircraft vertically takes off and lands or hovers and flies at low speed, the mode of the aircraft for adjusting the flight attitude is as follows:
the pitching attitude is adjusted through the increase and decrease of the thrust of the front rotor 4 and the backward tilting rotor 5;
the course attitude is adjusted through the torque differential of the front rotor 4 and the backward-tilting rotor 5;
the roll attitude is adjusted by the difference in left and right lift of the front rotor 4 and the rear tilt rotor 5.
(2) When the aircraft flies horizontally, the axis of the backward tilting rotor 5 is kept parallel to the axis of the fuselage 1 and generates backward thrust; and the front rotor 4 is covered by a cover plate mechanism to form an integral duck wing; thereby adopting a duck wing type aircraft mode to fly.
(3) When the aircraft flies flatly, the flying attitude of the aircraft is adjusted in the following way:
the pitching attitude is adjusted through the jet deflection of the front duck wing jet orifice 7 and the deflection matching of the rear control surface 8;
when head-lowering flight is needed, jet flow of the front duck wing jet flow openings 7 is deflected upwards, and then the rear control surface 8 is deflected downwards, and when head-raising flight is needed, jet flow of the front duck wing jet flow openings 7 is deflected downwards, and then the rear control surface 8 is deflected upwards;
the course attitude is adjusted by the thrust difference of the backward-tilting rotor wings 5 at the two sides of the fuselage 1;
the rolling attitude is adjusted by reversely deflecting the jet flow of the front duck wing jet flow opening 7 and the left and right sides of the rear rudder surface 8 upwards or downwards.
(4) When the aircraft is switched between the vertical take-off and landing mode and the flat flying mode, the thrust direction of the backward-tilting rotor wing 5 is adjusted through the tilting mechanism 6, and the thrust direction is combined with the lift force of the front rotor wing 4 to realize the switching.
Compared with helicopters, autorotation gyroplanes and multi-rotor aircrafts, the rapid aircraft and the control method thereof provided by the invention have the advantages that the attitude of the aircraft body in flight does not need to be additionally inclined by adjusting the inclination angle of the tilting thrust rotor, and the front rotor on the front canard wing under the flat flying mode is closed to form a canard wing type fixed wing aircraft, so that the front flying resistance is small, and the speed is obviously improved; the thrust of the invention comes from the retroverted rotor in the flat flying mode, the diameter of the rotor is smaller than that of the tilt rotor aircraft, the resistance is small in the forward flying process, and the speed is higher. The retroversion rotor wing of the canard configuration tilting rotor wing aircraft provided by the invention is close to the center of gravity in front of the wing, so that the thrust of the retroversion rotor wing is large in proportion, and the flying speed can be further improved. Furthermore, the canard wing adopts an active jet flow control technology, so that the lift force can be increased, and the resistance of the rear wing is reduced. And can realize VTOL and low-speed flight under the folding condition of wing and canard for the aircraft more adapts to narrow and small space's use.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft provided by an embodiment of the present invention;
FIG. 2 is a schematic diagram illustrating a takeoff and landing state of an aircraft provided by an embodiment of the invention;
FIG. 3 is a schematic view of a level flight state of an aircraft according to an embodiment of the present invention;
FIG. 4 is a schematic view of the active control of the front duck wing jets provided by an embodiment of the present invention;
FIG. 5 is a top view of an aircraft wing in a folded state provided by an embodiment of the present invention;
FIG. 6 is a front view of an aircraft wing in a folded state (front and rear wing folded conditions not shown, with the front canard shown on the left and rear wing hidden on the right);
wherein, 1-fuselage, 2-front canard wing, 3-rear wing, 4-front rotor wing, 41-through hole, 42-diversion hole, 43-air-bleed port, 5-back-tilting rotor wing, 6-tilting mechanism, 7-front canard wing jet-flow port, 8-back control plane, and 9-empennage.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The conventional helicopter is provided with a main rotor and a tail rotor, wherein the main rotor provides an upward lifting force, the tail rotor provides a lateral force to balance the torque generated by the rotation of the main rotor, the lifting operation is realized by adjusting the lifting force of the main rotor, the front-back, left-right flying is realized by inclining the plane of a paddle disk of the main rotor to obtain a horizontal component force in a corresponding direction, and the yawing operation is realized by adjusting the magnitude of the counter torque of the tail rotor; another coaxial helicopter realizes torque balance by assembling two pairs of main rotors rotating in opposite directions, each direction of flight control is similar to that of a conventional helicopter, and yaw control is realized by the torque difference of the two pairs of main rotors; the composite helicopter is characterized in that a propulsion paddle is additionally arranged on the basis of a conventional helicopter or a coaxial helicopter to strengthen the thrust, reduce the inclination angle of a main rotor and comprehensively realize the improvement of the flight speed, the speed level of the conventional helicopter such as S-76 and the coaxial helicopter such as card-28 is 300km/h, and the speed level of the composite helicopter such as X-2 and S-97 is 500km/h.
The autogyro is similar to a helicopter, but the main rotor of the autogyro is in a free windmill state when flying, lift force is generated by windward self-rotation, thrust is provided by a propelling propeller, direction control is realized by adjusting the inclination angle of the main rotor, and the autogyro has the advantages of simple mechanism and low cost because the size of the rotor is large, the speed is slightly lower than that of a common helicopter and is within 300km/h, and a German MTO autogyro is a typical autogyro.
Many rotor crafts mainly provide lift by 4 or more rotors, and the poor flight direction control who realizes unmanned aerial vehicle and fly forward through the lift between the rotor, realizes unmanned aerial vehicle's position steering control through the differential torque between the rotor. The multi-rotor aircraft mainly realizes forward flight and side flight by inclining the aircraft body to enable the lift force to provide forward flight component force; the combined type multi-rotor aircraft mainly has the advantages that the thrust is increased by additionally arranging the propelling propellers on the basis of the multi-rotor aircraft, the speed is increased by reducing the inclined angle of the aircraft body, the configuration speed of the multi-rotor aircraft is low, for example, the speed level of a Yifeng 184 manned aircraft and various small unmanned aerial vehicles is about 80km/h, and the speed level of the combined type multi-rotor aircraft is about 110km/h like a cis-rich manneray.
The tilt rotor aircraft is mainly characterized in that a tilt rotor propulsion device is arranged at the end part of a wing, and the conversion of flight attitude is carried out by adjusting the angle formed by the axis of the propulsion device and the axis of an aircraft body, namely, the axis of the propulsion device is vertical to the axis of the aircraft body during vertical take-off and landing; when flying horizontally, the axis of the propulsion device is parallel to the axis of the fuselage. The speed level of large tilting rotor aircrafts such as V-22 can reach more than 500km/h.
Conventional fixed wing configuration tiltrotor aircraft is then through increasing four rotor mechanisms in fixed wing both sides, realize fixed wing aircraft and four rotor aircraft's combination, the conversion that flies before the VTOL to the level is realized through the tiltrotor, power only leans forward 90 by anterior two rotors and provides when flying before, two rotors in rear portion stall when fixed wing flies in order to reduce fixed wing flight resistance, mainly be applied to small-size unmanned aerial vehicle if quantity TRON and intelligent navigation V330 etc. speed water average is about 120 kilometers/hour.
The lift body configuration tilt rotor aircraft is characterized in that two lift ducts are arranged in the front of a lift body, two tilt ducts are arranged at the tail of the lift body, the conversion of vertical take-off and landing and horizontal forward flight is realized through the tilt of the ducts, the lift ducts are closed when the lift ducts fly at high speed, the resistance of the whole aircraft is small, the resistance area of the tilt thrust ducts is small, the flight speed can be further improved on the basis of the tilt rotor aircraft, the aircraft of the configuration can be applied to small unmanned aerial vehicles and aerocars, and the prior patent application CN 107600405A in 2017 of an aviation industry helicopter design research institute and the patent application US 20200009974A1 in 2019 of time-keeping agility and boeing combined application are provided, and the speed level is over 600 km/h.
The first embodiment is as follows:
the invention provides a duck wing high-speed tilting rotor craft, which adopts a tilting rotor craft configuration with duck wing layout, and as shown in figures 1-3, the tilting rotor craft comprises a craft body 1, a front duck wing 2, a rear wing 3, a front rotor wing 4, a backward tilting rotor wing 5, a tilting mechanism 6, a front duck wing jet flow port 7, a rear control surface 8 and a tail wing 9, wherein the front duck wing 2 and the front rotor wing 4 are arranged at the front part of the craft body 1, the front rotor wing 4 is arranged in a through hole 41 of the front duck wing 2 and can be covered by a cover plate mechanism of the type of a sliding cover, a shutter or a rotary lens shutter and the like to form an integral duck wing; the rear wing 3 is arranged at the rear part of the fuselage 1, and the rear wing 3 is provided with a tail wing 9; retroversion rotor 5 install at fuselage 1 rear portion through tilting mechanism 6, the position is before back wing 3, after full quick-witted focus, retroversion rotor 5 can vert and leave the angle regulation scope between lift direction and thrust direction through the drive of tilting mechanism 6 to the vertical direction is 0 degrees, the angle of verting forward is positive, the angle of verting backward is negative, it is 90 degrees to the horizontal direction to vert promptly, retroversion rotor 5's the scope of verting should be able to satisfy-15 degrees to 105 degrees scope demands.
The front duck wing spout ports 7 are arranged on the front duck wing 2 and are divided into 4 groups which can be increased and decreased according to specific use requirements, typical 4 groups of spout ports are respectively positioned on the front edge of the wing section of the front duck wing, the position 5-10% behind the maximum thickness of the wing section, the position 70-80% of chord length of the wing section and the tail part of the wing section, and the spout ports are connected with the diversion holes 42 in the duct of the front rotor wing 4 through pipelines.
As shown in fig. 4, the front duct is used for introducing air to generate jet flow, and the size and the angle of the jet flow are controlled by a valve in the duct, so that the chord length increase, the resistance reduction and the wing section curvature change of the front duck wing, namely, the duck wing deflection effect is generated, and the pitching operation effect is realized; the rear control surface 8 is arranged on the rear wing 3; the lower part of the fuselage or the wing can be provided with various configurations of undercarriages according to the taking-off and landing requirements.
As shown in fig. 5-6, the front canard 2 and the rear wing 3 can be folded to reduce the size of the whole airplane for more fields during parking and vertical take-off and landing.
The second embodiment:
when the aircraft needs to take off and land vertically or hover and fly at a low speed, the axis of the backward tilting rotor 5 tilts to be perpendicular to the axis of the fuselage 1 to generate downward thrust to provide lift together with the front rotor 4, so that the vertical take off and land or hover of the aircraft is realized, and forward and backward thrust can be realized through the angle tilting adjustment of the backward tilting rotor 5.
When the unmanned aerial vehicle flies flatly, the axis of the backward-tilting rotor wing 5 and the axis of the fuselage 1 are kept near a parallel state and generate backward thrust; meanwhile, the front rotor 4 is covered by a cover plate mechanism to form an integral duck wing; at the moment, the lift force is mainly provided by the rear wing 3 and the front canard wing 2, and the canard wing type aircraft flies in a canard wing type aircraft mode.
The conversion between the vertical take-off and landing mode and the horizontal flying mode is realized by adjusting the thrust direction of the backward-tilting rotor wing 5 through the tilting mechanism 6 and combining the adjustment of the lift force of the front rotor wing 4.
Under the vertical take-off and landing mode and the hovering mode, the flight attitude of the aircraft is adjusted in a manner that the pitching attitude adjustment is realized by the increase and decrease of the thrust of the front rotor 4 and the rear tilting rotor 5; the course attitude is adjusted by the torque differential of the front rotor 4 and the rear-inclined rotor 5; the roll attitude is adjusted by the difference in the right and left lift of the front rotor 4 and the rear rotary rotor 5.
In the flat flying mode, the flying attitude of the aircraft is adjusted in a manner that the pitching attitude is adjusted by asynchronously deflecting the airflow of the front duck wing jet orifice 7 and the rear control surface 8, when head-down flying is needed, the airflow of the front duck wing jet orifice 7 is deflected upwards, the rear control surface 8 is deflected downwards, and when head-up flying is needed, the airflow of the front duck wing jet orifice 7 is deflected downwards, and the rear control surface 8 is deflected upwards; the adjustment of course attitude is realized by the thrust difference of the backward-tilting rotor wings 5 at the two sides of the fuselage 1, and can also be realized by additionally arranging a vertical stabilizing surface on the empennage 9; the rolling attitude is adjusted by adjusting the airflow of the front canard jet nozzle 7 and the upward or downward reverse deflection of the left and right sides of the rear control surface 8.
The attitude adjustment method in the transition state is similar to that in the vertical take-off and landing mode, and the attitude adjustment method adopting the level flight mode can be adopted and is executed by combining the two methods.
Example three:
the embodiment of the invention provides a canard wing high-speed tilt rotor craft, as shown in fig. 1, a configuration of a canard wing arranged tilt rotor craft is adopted, the aircraft comprises a fuselage 1, a front canard wing 2, a rear wing 3, a front rotor wing 4, a backward tilt rotor wing 5 and a tilt mechanism 6, the front canard wing 2 and the front rotor wing 4 are arranged at the front part of the fuselage 1, wherein the front rotor wing 4 is arranged in a through hole 41 of the front canard wing 2 and can be sealed and covered by a cover plate mechanism of the type of a sliding cover or a rotary lens shutter and the like to form an integral canard wing; the rear wing 3 is arranged at the rear part of the fuselage 1; retroversion rotor 5 install at fuselage 1 rear portion through tilting mechanism 6, the position is before back wing 3, after full quick-witted focus, retroversion rotor 5 can vert and leave the angle regulation scope between lift direction and thrust direction through the drive of tilting mechanism 6 to the vertical direction is 0 degrees, the angle of verting forward is positive, the angle of verting backward is negative, it is 90 degrees to the horizontal direction to vert promptly, retroversion rotor 5's the scope of verting should be able to satisfy-15 degrees to 105 degrees scope demands.
During high-speed flight, a front duck wing jet flow port 7, a rear control surface 8 and an empennage 9 need to be assembled, wherein the front duck wing jet flow port 7 is installed on the front duck wing 2, the rear control surface 8 is installed on the rear wing 3, and the empennage 9 is installed on the rear wing 3.
The front rotor 4 and the rear tilting rotor 5 of the embodiment of the invention improve the pneumatic efficiency, increase the safety and reduce the noise by additionally arranging the duct shell.
The front canard 2 and the rear wing 3 can be folded to reduce the size of the whole aircraft during parking, vertical take-off and landing and low-speed flight, so that the aircraft is suitable for more fields.
The flight characteristics of the rapid aircraft provided by the embodiment of the invention are as follows:
when the aircraft needs to take off and land vertically or hover and fly at a low speed, the axis of the backward tilting rotor 5 tilts to be perpendicular to the axis of the fuselage 1 to generate downward thrust to provide lift together with the front rotor 4, so that the vertical take off and land or hover of the aircraft is realized, and forward and backward thrust can be realized through the angle tilting adjustment of the backward tilting rotor 5.
When the unmanned aerial vehicle flies flatly, the axis of the backward-tilting rotor wing 5 and the axis of the fuselage 1 are kept near a parallel state and generate backward thrust; meanwhile, the front rotor 4 is covered by a cover plate mechanism to form an integral duck wing; at the moment, the lift force is mainly provided by the rear wing 3 and the front canard wing 2, and the canard wing type aircraft flies in a canard wing type aircraft mode.
The conversion between the vertical take-off and landing mode and the horizontal flying mode is realized by adjusting the thrust direction of the backward-tilting rotor wing 5 through the tilting mechanism 6 and combining the adjustment of the lift force of the front rotor wing 4.
The embodiment of the invention provides a rapid aircraft attitude adjustment method, which is characterized in that:
under the vertical take-off and landing mode and the hovering mode, the flight attitude of the aircraft is adjusted in a manner that the pitching attitude adjustment is realized by the increase and decrease of the thrust of the front rotor wing 4 and the backward-tilting rotor wing 5; the course attitude is adjusted through the torque differential of the front rotor 4 and the rear tilting rotor 5; the roll attitude is adjusted by the difference in the right and left lift of the front rotor 4 and the rear rotary rotor 5.
In the flat flying mode, the flying attitude of the aircraft is adjusted in a manner that the pitching attitude is adjusted by asynchronously deflecting the airflow of the front duck wing jet orifice 7 and the rear control surface 8, when head-down flying is needed, the airflow of the front duck wing jet orifice 7 is deflected upwards, the rear control surface 8 is deflected downwards, and when head-up flying is needed, the airflow of the front duck wing jet orifice 7 is deflected downwards, and the rear control surface 8 is deflected upwards; the adjustment of course attitude is realized by the thrust difference of the backward-tilting rotor wings 5 at the two sides of the fuselage 1, and can also be realized by additionally arranging a vertical stabilizing surface on the empennage 9; the rolling attitude is adjusted by adjusting the airflow of the front canard wing jet flow port 7 and the upward or downward reverse deflection of the left and right sides of the rear control surface 8.
The attitude adjustment method in the transition state is similar to that in the vertical take-off and landing mode, and the attitude adjustment method adopting the level flight can be adopted at the same time, and the attitude adjustment method and the vertical take-off and landing mode are combined and executed through two methods.
The invention has the following beneficial effects in the aspects of timeliness, flight efficiency, comfort, forced landing safety, taking-off and landing convenience, silence and the like: compared with helicopters, autorotation gyroplanes and multi-rotor aircrafts, the aircraft body posture does not need to be additionally inclined by adjusting the inclination angle of the tilting thrust rotor, and the front rotor on the front duck wing under the horizontal flying mode is closed to form the duck wing type fixed wing aircraft, so that the front flying resistance is small, and the speed is obviously improved; the thrust of the aircraft comes from the backward-tilting rotor in the flat flight mode, the diameter of the rotor is smaller than that of the aircraft with the tilting rotor, the resistance is small during forward flight, and the speed is higher.
The tilting duct of the lift body configuration tilting rotor aircraft is arranged at the rear part of the wing, and a tail tilting duct is arranged at the rear part of the wing and is far away from the gravity center, so that the lift force of the lift duct is relatively large in the lifting balance in the take-off and landing state, the tilting thrust is relatively small in the whole lift force, and the take-off and landing power is large in the whole flight state, so that the thrust of the tilting thrust duct is relatively small in the thrust of the whole aircraft, and the further lifting flight speed is influenced; the backward tilting rotor wing of the canard configuration tilting rotor wing aircraft provided by the invention is close to the center of gravity in front of the wing, so that the thrust of the backward tilting rotor wing is large, and the flying speed can be further improved.
The wing has a larger aspect ratio, and the induced resistance of the wing can be reduced, so that the maneuverability of the airplane can be improved, and the subsonic voyage can be increased; under the same condition, the wing with large aspect ratio has large lift force, and the takeoff and landing distances of the aircraft can be reduced.
The backward-tilting rotary wing is arranged in the front of the wing, the thrust center is arranged on the upper part of the wing, and airflow of the rotary wing can drive airflow on the upper part of the wing to flow when the rotary wing flies forwards, so that the flying efficiency of the wing can be improved, the flying range can be increased, or energy sources and multi-task loads can be carried less.
The rotor wing provided by the invention avoids the blocking effect of the body support piece on the lower washing flow of the rotor wing, so that the propelling efficiency is higher compared with that of a multi-rotor unmanned aerial vehicle and a tilt rotor unmanned aerial vehicle.
The retroversion rotor wing is arranged on the aircraft body, and the retroversion thrust duct of the rotorcraft is arranged at the weak position of the tail part of the aircraft wing relative to the lifting body.
The sweep angle of the wing has a wide selectable range, so that the applicable flight speed range is wider, and the popularization is better.
The front rotor wing and the rear rotor wing are more balanced in thrust, and are better in stability and maneuverability in vertical take-off and landing.
The ducted channel of the tilt rotor aircraft relative to the lifting body configuration is arranged at the rear part of the wing, and when the lift body configuration is in a leveling state, the gravity center is close to the back, and the lifting force action point is close to the front due to the configuration arrangement of the lifting body, so that the gravity center and the lifting force action point are close to each other, and the pitching stability of the front flight is influenced; the canard wing type configuration tilting rotor aircraft adopts a mode of rear wings, so that the lift force action point of the wings is close to the rear, the backward tilting rotor is arranged in front of the wings, the arrangement problem of the gravity center can be solved by increasing the lift force proportion of the rear rotors, the gravity center is positioned at the front position of the lift force action point, and the flat flight stability is better than that of a lifting body configuration tilting rotor aircraft.
The position of the control surface of the invention is far away from the gravity center, the control efficiency is higher, and the operability is better. The wing has the advantages of large area, large aspect ratio, capability of fully adopting a gliding forced landing mode, convenience, easiness and better safety.
According to the invention, the duck wing adopts an active jet flow control technology, so that the lift force can be increased, and the resistance of the rear wing can be reduced.
The invention can realize vertical take-off and landing and low-speed flight under the condition that wings and canard wings are folded, so that the aircraft is more suitable for use in narrow space.
The invention is suitable for additionally arranging a duct and can improve pneumatic efficiency, safety and mute effect.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (10)
1. The utility model provides a high-speed rotor craft that verts of duck wing which characterized in that includes: the aircraft comprises an aircraft body (1), a front canard wing (2), a rear wing (3), a front rotor wing (4), a rear tilting rotor wing (5) and a tilting mechanism (6);
the front canard wing (2) and the front rotor wing (4) are installed at the front part of the airframe (1), the front rotor wing (4) is positioned at the inner side of the front canard wing (2), and the rear wing (3) is installed at the rear part of the airframe (1); the backward-tilting rotor wing (5) is arranged in a cross space between the fuselage (1) and the rear wing (3) through a tilting mechanism (6);
the front duck wing is of an elliptical wing shape, and when the front duck wing adopts active jet flow control to close a rotor duct of the front duck wing, the tail chord length of the front duck wing is increased, so that the lift center of the front duck wing is consistent with that of the front duck wing during vertical take-off and landing.
2. The canard high-speed tiltrotor aircraft of claim 1, further comprising: a front duck wing spout (7), a rear control surface (8) and a tail wing (9);
wherein, the front duck wing spout (7) is arranged on the front duck wing (2), the rear rudder surface (8) is arranged on the rear wing (3), and the tail wing (9) is arranged on the rear wing (3).
3. The canard high-speed tiltrotor aircraft of claim 2,
the front duck wing jet flow ports (7) comprise four groups of jet flow ports, the four groups of jet flow ports are respectively positioned at the wing section front edge of the front duck wing, the position 5% -10% behind the maximum thickness of the wing section, the chord length position 70% -80% of the wing section and the tail part of the wing section, each group of jet flow ports are connected with the flow guide holes in the duct of the front rotor wing through pipelines, jet flow is generated by air bleed from the front duct, and the size and the angle of the jet flow are controlled through a valve in the pipelines.
4. The canard high-speed tiltrotor aircraft of claim 1,
behind the center of gravity of the fuselage (1), the backward tilting rotor (5) can tilt between the lift direction and the thrust direction through the driving of the tilting mechanism (6); the ratio of the distance from the lift center of the backward tilting rotor (5) to the gravity center of the aircraft to the distance from the lift center of the front rotor (4) to the gravity center of the aircraft is 1;
defining the vertical direction of the airplane body as 0 degree, the forward tilting angle as positive, the backward tilting angle as negative, the forward tilting to the horizontal direction as 90 degrees, and the backward tilting to the horizontal direction as-90 degrees; the tilting range of the backward tilting rotor (5) is-15 degrees to 105 degrees.
5. The canard wing high-speed tiltrotor aircraft as claimed in claim 1, wherein a bleed port (43) is arranged at the top of the front rotor, the front rotor (4) is covered by a cover plate mechanism to form an integral canard wing, and when a duct of the front rotor is closed, the bleed port bleeds air when flying in front so as to generate jet flow to realize active control of a flow field.
6. A method of operating a canard high-speed tiltrotor aircraft, the method being applied to an aircraft according to any one of claims 1 to 5,
when the aircraft vertically takes off and lands or hovers and flies at a low speed, the axis of the backward tilting rotor (5) tilts to be vertical to the axis of the fuselage (1) to generate downward thrust, and the forward tilting rotor provide lift together with the front rotor (4), so that the vertical taking off and landing or hovering and the low-speed flying of the aircraft are realized, and the forward moving and the backward moving of the aircraft are realized by adjusting the tilting angle of the backward tilting rotor (5).
7. The method of operating a canard high-speed tiltrotor aircraft according to claim 6,
when the aircraft vertically takes off and lands or hovers and flies at low speed, the aircraft performs flight attitude adjustment in the following way:
the pitching attitude is adjusted through the increase and decrease of the thrust of the front rotor (4) and the backward-tilting rotor (5);
the course attitude is adjusted through the torque differential of the front rotor (4) and the backward-tilting rotor (5);
the rolling attitude is adjusted by the left-right lift difference of the front rotor (4) and the rear tilting rotor (5).
8. The method of operating a canard high-speed tiltrotor aircraft according to claim 7,
when the aircraft flies horizontally, the axis of the backward-tilting rotor wing (5) and the axis of the aircraft body (1) are kept in a parallel state and generate backward thrust; the front rotor (4) is covered by a cover plate mechanism to form an integral duck wing; thereby adopting a duck wing type aircraft mode to fly.
9. The method of operating a canard high-speed tiltrotor aircraft of claim 8,
when the aircraft flies flatly, the flying attitude of the aircraft is adjusted in the following way:
the pitching attitude is adjusted through jet flow deflection of the front duck wing jet flow port (7) and deflection of the rear control surface (8);
when the aircraft needs to fly with the head lowered, jet flow of the front duck wing jet flow openings (7) is deflected upwards, and then the rear control surface (8) is deflected downwards, and when the aircraft needs to fly with the head raised, jet flow of the front duck wing jet flow openings (7) is deflected downwards, and then the rear control surface (8) is deflected upwards;
the course attitude is adjusted through the thrust difference of the backward-tilting rotor wings (5) at the two sides of the fuselage (1);
the rolling attitude is adjusted by reversely deflecting the jet flow of the front duck wing jet flow port (7) and the left and right sides of the rear control surface (8) upwards or downwards.
10. The method of operating a canard high-speed tiltrotor aircraft of claim 9,
when the aircraft is switched between the vertical take-off and landing mode and the horizontal flying mode, the thrust direction of the backward-tilting rotary wing (5) is adjusted through the tilting mechanism (6), and the thrust direction is combined with the lift force of the front rotary wing (4) to realize the switching.
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| CN113086195A (en) * | 2021-04-19 | 2021-07-09 | 哈尔滨职业技术学院 | High-voltage line damage detection unmanned aerial vehicle |
| CN114348252B (en) * | 2022-03-01 | 2023-12-01 | 成都纵横大鹏无人机科技有限公司 | Multi-rotor aircraft |
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