CN115195988A - Novel aerodynamic layout of VTOL fixed wing unmanned aerial vehicle - Google Patents
Novel aerodynamic layout of VTOL fixed wing unmanned aerial vehicle Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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Abstract
The invention discloses a novel vertical take-off and landing fixed wing unmanned aerial vehicle aerodynamic layout, which comprises a machine head, a machine body, a machine tail and wings in a lower single-wing layout, wherein the machine body comprises a machine body front section, a machine body middle section and a machine body rear section, the machine body middle section comprises a central body in the upper half part and an engine room in the lower half part, and the cross section of the central body shrinks towards the direction of the machine tail, so that the whole unmanned aerial vehicle presents a streamline; install air inlet unit, duct fan and exhaust apparatus in the aircraft cabin, aircraft nose both sides smooth transition to fuselage middle section, air inlet unit back lip and fuselage smooth connection guide the air current to get into along the fuselage in the air inlet unit, the duct fan is located central body below and arranges along the fuselage flow direction, and the required air current of air drive fan gets into air inlet unit with different modes along the fuselage both sides when VTOL, transition flight and high-speed flat flight, and the duct fan all works under all flight states, provides suitable thrust and lift for unmanned aerial vehicle, does not have unnecessary dead weight.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a novel aerodynamic layout of a vertical take-off and landing fixed wing unmanned aerial vehicle.
Background
Vertical/short take-off and landing aircraft with vector propulsion capability is one of the important trends in future aircraft development. The vertical take-off and landing technology can reduce or even completely get rid of the dependence on the runway, and can greatly reduce the facility requirements of the aircraft on the take-off and landing area. Therefore, the vtol aircraft has a greater working area adaptability compared to conventional take-off and landing aircraft, which has a large application space under conditions of small take-off and landing area and complex terrain environment, but the conventional rotary-wing vtol aircraft provides lift and thrust by the rotors during both vertical take-off and vertical flight, resulting in high fuel consumption. The fixed wing aircraft has wings with large lift-drag ratio, main lift force comes from relative motion of the wings and air, and the fixed wing aircraft has the characteristics of high flying speed, long voyage, low oil consumption and the like based on the principle. However, the conventional fixed-wing aircraft needs a large takeoff speed, so that the requirement on the length of a take-off and landing runway is high.
The power device of the conventional fixed-wing VTOL aircraft comprises several forms of a lift fan, a ducted fan, a tilt rotor and a direct jet flow. The wing-arranged lifting force fan is adopted by the XV-5 verification machine of the Regan company, the aircraft utilizes the lifting force generated by the fan to realize vertical take-off, and the feasibility of the fixed-wing vertical take-off and landing aircraft which is arranged on the wing by utilizing the lifting force fan is successfully verified. However, if the takeoff weight of the XV-5 verification machine needs to be increased continuously, the diameter of a fan needs to be increased, so that the area and the length of the wing are increased, the strength of the wing needs to be increased, the head of the large wing is thicker to obtain higher lift force in order to meet the aerodynamic requirement, and meanwhile, the flight resistance is increased and the cost of larger structure size is brought; in addition, the combined power system of the main engine and the front lifting force fan of the F-35B combined attack fighter adopting the lifting force fan in the United states has the best comprehensive performance in the current similar design. The feasibility of the layout that the lift fans are arranged on the wings and the fuselage together is successfully verified, but the lift fans do not work when cruising at a high speed, so that the dead weight of the lift fan aircraft in a cruising state is larger, and the lift fans arranged on the wings and the fuselage together occupy too much aircraft space, so that the effective load is small.
From the above, it can be seen that the wing arrangement of the lift fan for a large takeoff weight leads to an excessively large structural size. The lift fan arranged by the wing and the fuselage occupies too much aircraft space and has dead weight problem when flying flatly. Therefore, a novel aerodynamic layout of the vertical take-off and landing fixed-wing unmanned aerial vehicle is urgently needed to solve the problems.
Disclosure of Invention
The invention provides a novel aerodynamic layout of a vertical take-off and landing fixed wing unmanned aerial vehicle, which solves the problems in the prior art.
In order to achieve the purpose, the invention provides the following technical scheme: a novel aerodynamic layout of a vertical take-off and landing fixed wing unmanned aerial vehicle comprises a machine head, a machine body, a machine tail and wings in a lower single-wing layout, wherein the machine body comprises a machine body front section, a machine body middle section and a machine body rear section, the machine body middle section comprises a central body in the upper half part and an engine room in the lower half part, the cross section of the central body is contracted towards the machine tail direction, and the whole unmanned aerial vehicle is enabled to present a streamline;
the aircraft nose is characterized in that an air inlet device, a ducted fan and an exhaust device are installed in the aircraft cabin, the two sides of the aircraft nose are in smooth transition to the middle section of the aircraft body, a lip on the rear side of the air inlet device is in smooth connection with the aircraft body to guide airflow to enter the air inlet device along the aircraft body, and the ducted fan is located below the central body and arranged along the flow direction of the aircraft body.
Preferably, the central body and the air inlet device jointly form a three-dimensional effect to realize air inlet during level flight, wherein air inlet guide vanes are arranged on two sides of the center to be matched with the air inlet device to realize high-efficiency air inlet.
Preferably, the ducted fan is installed in the nacelle at an angle of 10 degrees from the horizontal, wherein the fan pressure ratio is pi, the air adiabatic index k, and the gasConstant g, air density rho, flow rate m, intake pressure Pin, exhaust pressure Pout, exhaust speed V, and exhaust expansion to atmospheric pressure P; exhaust Mach number
The thrust is equal to the maximum takeoff gravity, the flow is obtained by F = m V, and the fan diameter is obtained by the fan area A = pi d/4 and the flow m = ρ V A; the rotation speed is obtained from the rotation speed formula Rpm = V60/(3.14 × d).
Preferably, an inlet of the air inlet device is transited to a circular outlet and is provided with an inner channel with a variable cross section and a lip, air flow enters the inner channel through the lip in a constrained mode, and the cross section of the inlet is provided with an angle of 5 degrees in the direction of the airplane body.
Preferably, the exhaust device is installed at the rear half section of the cabin and comprises a transition section, an exhaust inlet, an exhaust outlet and a guide vane, wherein the exhaust device is provided with the transition section which is transited from the circular outlet of the fan to the exhaust port, the height of the transition section is 0.3-0.5 times of the diameter of the fan, the exhaust port and the axis of the machine body form an angle of 14 degrees, and the exhaust adjustable angle is arranged along with the installation angle of the exhaust device so as to realize vector thrust; the exhaust inlet is provided with a flange plate for mounting the exhaust inlet at the outlet of the ducted fan, and the shape of the exhaust inlet is the same as that of the outlet of the ducted fan; the exhaust outlet is used for installing a guide vane, the shape of the exhaust outlet is rectangular, the side length of the guide vane is calculated according to the exhaust area, the guide vane is used for changing the exhaust angle, and the adjustable angle of the guide vane is set according to the installation angle of the exhaust device;
wherein, the flow formula
The total pressure recovery of the exhaust device is delta e And delta in level flight e2 Delta from vertical take-off and landing e1 Small, the fan outlet area is A f The fan outlet flow function is q (M) af ) The area of the exhaust outlet is A e The exhaust outlet flow function is q (M) ae ) Push out the exhaust area A e ＝A f q(M af )/(q(M ae ) The gas state parameters during the horizontal flying and the vertical taking off and landing are substituted into an exhaust area calculation formula to obtain the vertical flyingWhen taking off and landing vertically A e1 ，δ e1 (ii) a Horizontal flight time A e2 ，δ e2 。
Preferably, the wing is provided with a sweep angle of 20 degrees and a dihedral angle of 3-5 degrees, and is arranged at the position of the center of gravity of the airplane.
Preferably, the rear section of the unmanned aerial vehicle is transited from the middle section of the unmanned aerial vehicle to the tail, and the lower half part of the unmanned aerial vehicle is distributed and is streamlined from the middle section of the unmanned aerial vehicle to the tail by the lip at the rear end of the air inlet device, so that the total flight resistance of the unmanned aerial vehicle is low, and the flow field is uniform.
Preferably, the bottom of the cabin begins to tilt upwards at an angle of 14 degrees after the center of gravity and reaches the tail of the fuselage, so that the exhaust device is ensured to have a certain installation angle.
Preferably, the rear section of the tail part of the fuselage is used for installing a driving core machine of the ducted fan.
Preferably, the tail comprises a horizontal tail and a vertical tail, and is mounted on the tail.
Compared with the prior art, the invention has the beneficial effects that: in the invention, the effective volume of the unmanned aerial vehicle is ensured by the design of the central body, and the design of the strake wings is matched to reduce the resistance generated by the air inlet device and ensure that the fan has enough air inlet area, wherein, the ducted fan is arranged along the flow direction of the fuselage, the airflow required by the ducted fan enters along the two sides of the fuselage when the unmanned aerial vehicle is vertically lifted and landed, flies in transition and flies at high speed and flies flatly, and the ducted fan works in all flight states to provide proper thrust and lift force for the unmanned aerial vehicle without redundant dead weight;
in addition, the inlet section of the air inlet device has a certain inclination angle, so that the effective air inlet area during vertical take-off and landing and high-speed flat flight can be ensured, the lip-assisted air inlet is formed, air flow can better enter the inner channel under the constraint of the lip, incoming flow in all directions can enter the air inlet device during vertical take-off and landing, and the overflow resistance during flat flight can also be weakened.
In the invention, the wings and the ducted fan are arranged near the gravity center of the airplane and are distributed by adopting the lower single wing, thereby improving the integral balance performance and the take-off and landing performance of the airplane and well shielding the noise of an engine.
According to the invention, the exhaust adjustable angle is arranged along with the installation angle of the exhaust device so as to realize vector thrust, the exhaust outlet is used for installing the guide vane, and the guide vane is used for changing the exhaust angle so as to change the effective exhaust area.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a block diagram of the drone of the present invention;
FIG. 2 is a front view of the drone of the present invention;
fig. 3 is a side view of the drone of the present invention;
fig. 4 is a bottom view of the drone of the present invention;
FIG. 5 is a schematic structural diagram of an air intake device of the unmanned aerial vehicle according to the invention;
FIG. 6 is a schematic view of the construction of the exhaust apparatus of the present invention;
FIG. 7 is a top view of the exhaust apparatus of the present invention;
FIG. 8 is a pneumatic flow path for vertical take-off and landing modes of the unmanned aerial vehicle of the present invention;
FIG. 9 is a high-speed flat flying mode pneumatic flow path of the unmanned aerial vehicle of the present invention;
reference numbers in the figures: 1. a machine head; 2. a front section of the fuselage; 3. a central body; 4. a ducted fan; 5. an air intake device; 5-1, lip; 5-2, an inner channel; 6. a rear section of the fuselage; 7. a vertical tail; 8. a tail; 9. a horizontal rear wing; 10. an exhaust device; 10-1, a transition section; 10-2, an exhaust inlet; 10-3, an exhaust outlet; 10-4, guide vanes; 11. an airfoil; 12. a nacelle.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it should be understood that they are presented herein only to illustrate and explain the present invention and not to limit the present invention.
Example (b): as shown in fig. 1-4, a novel aerodynamic layout of a vertical take-off and landing fixed wing unmanned aerial vehicle comprises a nose 1, a fuselage (a fuselage front section 2, a central body 3, a fuselage rear section 6, a cabin 12), a tail 8 and wings 11 in a lower single wing layout, wherein the symmetrical surface of the whole unmanned aerial vehicle is in a wing shape, and the flying resistance of the fuselage is small. The front section 2 of the machine body is transited to the middle section of the machine body and the engine room 12 from the machine head 1 in order to ensure the efficient air intake of the air intake device; the midship section is divided into a central body 3 in the upper half and a nacelle 12 in the lower half. Central body 3 can provide sufficient volume for unmanned aerial vehicle, can also compromise the air intake performance when guaranteeing the VTOL, reduces air inlet unit's flow separation. An air inlet device 5, a ducted fan 4 and an exhaust device 10 are arranged in the engine room 12; the fuselage back end 6 provides installation space for the drive arrangement of duct fan 4, and unmanned aerial vehicle design weight of taking off is about 1 ton, and design cruise mach number is about 0.8Ma. Ducted fan 4 all works under all flight conditions, both can provide the lift of VTOL for unmanned aerial vehicle and can provide the thrust when flat flying again, does not have unnecessary dead weight, and wherein, the centrum forms three-dimensional effect jointly with air inlet unit and realizes admitting air when flat flying, and the installation of center both sides is admitted air stator cooperation air inlet unit and is realized high-efficient admitting air.
Referring to fig. 1, the ducted fan 4 is installed in the cabin 12 at an angle of 10 degrees with respect to the horizontal, has a low design pressure ratio (about pi =1.07 in vertical take-off and landing) and a large flow rate, and has a diameter of about 1 meter and a rotation speed of about 3500ram (preventing supersonic speed of airflow at the tip of the blade) calculated according to the take-off weight, and can obtain large power output with low oil consumption by matching with a driving device.
The derivation process of the fan diameter is as follows: the fan pressure ratio is pi, the air adiabatic index k, the gas constant g, the air density rho, the flow rate is m, the air inlet pressure is Pin, the exhaust pressure is Pout, the exhaust speed is V, and the exhaust expands to the atmospheric pressure P; exhaust Mach number
A take-off weight of 1000Dan required, two ducted fans, an average of the force F per ducted fan of 500Dan, from F = m V, giving the flow, the fan area a = pi d/4, from m = ρ V a, giving the fan diameter of about 1 meter(ii) a Let the tip linear speed be less than 300m/s, have rotational speed formula Rpm = V60/(3.14 d), derive the rotational speed and be about 3500Rpm.
Referring to fig. 1, the wingspan of the wing 11 is 2.7 meters, the wing 11 is provided with a 20-degree sweepback angle and a 3-degree dihedral angle, and the aerodynamic center of the wing 11 is slightly behind the gravity center of the airplane so as to ensure the static stability of the airplane. The tail includes a horizontal tail 9 and a vertical tail 7. The vertical tail 7 is installed above the tail 8, and the horizontal tail 9 is installed on both sides of the tail 8.
Wherein the optimum sweep angle of the wings 11 for an aircraft flying at 0.8Ma cruise speed is between 10 ° and 15 °, as determined by design references. The invention sets the sweep angle of the wing 11 to be 20 degrees according to the limitation of gravity and lift force center. To increase lateral stability, a typical dihedral value for the lower singlet at a 20 ° sweep angle is about 3 ° to 7 °. The horizontal rear wing 9 is thus mounted on the nacelle 12, arranged at the centre of gravity of the aircraft, and is set at a 3 dihedral angle that provides the majority of the lift for the aircraft during flat flight.
Referring to fig. 5, 8 and 9, the air intake device 5 is mounted in the nacelle 12 with its inlet at an angle of 5 degrees to the horizontal. The air inlet device 5 comprises a lip 5-1 and an inner channel 5-2, air flow is restricted by the lip to enter the inner channel, the total pressure recovery coefficient is about 0.98, and the air inlet flow is equal to the flow required by the fan. In the vertical take-off and landing state, the air inlet device sucks air from all directions by means of the lip, the air inlet guide vane and the central body, and the exhaust device exhausts air vertically downwards; the intake during flat flight and the exhaust horizontally aft exhaust are better achieved by the three-dimensional effect of the centerbody 12 shield. The rear lip can reduce or even inhibit flow separation in the air inlet device during flat flight, and flow loss is reduced.
Referring to fig. 4, 6 and 7, the exhaust device 10 is installed at the rear half section of the nacelle 12, and includes a transition section 10-1, an exhaust inlet 10-2, an exhaust outlet 10-3 and a guide vane 10-4, wherein the exhaust device 10 is provided with the transition section 10-1 that is transited from a circular outlet of a fan to an exhaust port, the height of the transition section is 0.3 to 0.5 times the diameter of the fan, the exhaust port and the axis of the fuselage form an angle of 14 degrees, and the exhaust adjustable angle is set according to the installation angle of the exhaust device to realize vector thrust; the exhaust inlet 10-2 is provided with a flange plate for mounting the exhaust inlet at the outlet of the ducted fan, and the shape of the exhaust inlet is the same as that of the outlet of the ducted fan; the exhaust outlet 10-3 is used for installing a guide vane 10-4, the shape of the exhaust outlet is rectangular, the side length of the guide vane is calculated according to the exhaust area, the guide vane 10-4 is used for changing the exhaust angle, and the adjustable angle of the guide vane is set according to the installation angle of the exhaust device.
Referring to fig. 5, the rear fuselage section transitions from the middle fuselage section to the tail 7, the lower half portion of the rear fuselage section and the lip at the rear end of the air inlet device make the middle fuselage section to the tail 7 in a streamline form, so that the overall flight resistance of the unmanned aerial vehicle is low, the flow field is uniform, the tail of the fuselage section is used for installing the driving core machine of the ducted fan, and the cabin 12 at the exhaust outlet is upwardly contracted at an inclination angle of 14 degrees to ensure that the exhaust device 10 has a certain installation angle, thereby facilitating the adjustment of the exhaust direction of the air-driven fan. The exhaust area derivation process is as follows (subscript 1 represents vertical take-off and landing, and subscript 2 represents flat flight): formula of flow
Let the total pressure recovery system of the exhaust device be delta e And delta in flat flight e2 Delta than during vertical take-off and landing e1 Slightly smaller, the fan outlet area is A f The fan outlet flow function is q (M) af ) The area of the exhaust outlet is A e The exhaust outlet flow function is q (M) ae ) Push out the exhaust area A e ＝A f q(M af )/(q(M ae )). Substituting the gas state parameters during level flight and vertical take-off and landing into an exhaust area calculation formula to obtain: vertical take-off and landing A e1 ＝0.521m 2 ，δ e1 =0.985; when flying in level A e2 ＝0.1794m 2 ，δ e2 ＝0.975。
And (3) a dip angle derivation process: and setting theta as an included angle between the exhaust port and the horizontal plane, setting the area of the exhaust device as A, and pushing out: vertical take-off and landing A e1 = Acos θ, flat flight time a e2 = Asin theta, the final solution is given as equation set [0.6,12 [ ]]Nearby solution is a =0.543m 2 θ =19 °. Since body contraction is too fast with θ =19 °, exhaust and body restriction are combined, setting θ to 14 °.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides a novel VTOL fixed wing unmanned aerial vehicle aerodynamic configuration which characterized in that: the unmanned aerial vehicle comprises a machine head, a machine body, a machine tail and wings in a lower single-wing layout, wherein the machine body comprises a machine body front section, a machine body middle section and a machine body rear section;
the aircraft nose is characterized in that an air inlet device, a ducted fan and an exhaust device are installed in the aircraft cabin, the two sides of the aircraft nose are in smooth transition to the middle section of the aircraft body, a lip on the rear side of the air inlet device is in smooth connection with the aircraft body to guide airflow to enter the air inlet device along the aircraft body, and the ducted fan is located below the central body and arranged along the flow direction of the aircraft body.
2. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the central body and the air inlet device jointly form a three-dimensional effect to realize air inlet during level flight, wherein air inlet guide vanes are arranged on two sides of the central body and matched with the air inlet device to realize high-efficiency air inlet.
3. The novel aerodynamic layout of VTOL fixed-wing UAVs of claim 1, characterized in that: the ducted fan is arranged in the engine room at an angle of 10 degrees with the horizontal direction, wherein the pressure ratio of the fan is pi, the air heat insulation index k, the gas constant g, the air density rho, the flow rate m, the air inlet pressure Pin, the air exhaust pressure Pout, the air exhaust speed V and the exhaust expansion are carried out to the atmospheric pressure P; exhaust Mach number
The thrust is equal to the maximum takeoff gravity, the flow is obtained by F = m V, and the fan diameter is obtained by the fan area A = pi d/4 and the flow m = ρ V A; the rotation speed is obtained from the rotation speed formula Rpm = V60/(pi x d).
4. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the inlet of the air inlet device is transited to the round outlet and is provided with an inner channel with a variable cross section and a lip, air flow enters the inner channel through the lip in a constrained mode, and the cross section of the inlet is provided with an angle of 5 degrees in the direction of the machine body.
5. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the exhaust device is arranged at the rear half section of the engine room and comprises a transition section, an exhaust inlet, an exhaust outlet and a guide vane, wherein the exhaust device is provided with the transition section which is transited from a circular outlet of the fan to an exhaust port, the height of the transition section is 0.3-0.5 times of the diameter of the fan, the exhaust port and the axis of the engine body form an angle of 14 degrees, and the exhaust adjustable angle is arranged along with the installation angle of the exhaust device so as to realize vector thrust; the exhaust inlet is provided with a flange plate for mounting the exhaust inlet at the outlet of the ducted fan, and the shape of the exhaust inlet is the same as that of the outlet of the ducted fan; the exhaust outlet is used for installing a guide vane, the shape of the exhaust outlet is rectangular, the side length of the guide vane is calculated according to the exhaust area, the guide vane is used for changing the exhaust angle, and the adjustable angle of the guide vane is set according to the installation angle of the exhaust device;
wherein, the flow formula
The total pressure recovery system of the exhaust device is delta e And delta in level flight e2 Delta than during vertical take-off and landing e1 Small, the fan outlet area is A f The fan outlet flow function is q (M) af ) The area of the exhaust outlet is A e The exhaust outlet flow function is q (M) ae ) Push out the exhaust area A e ＝A f q(M af )/(q(M ae ) Substituting the gas state parameters during level flight and vertical take-off and landing into an exhaust area calculation formula to obtain A during vertical take-off and landing e1 ，δ e1 (ii) a Horizontal flight time A e2 ，δ e2 。
6. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the wings are provided with a sweep angle of 20 degrees and a dihedral angle of 3-5 degrees and are arranged at the position of the center of gravity of the airplane.
7. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the rear section of the unmanned aerial vehicle is transited from the middle section of the unmanned aerial vehicle to the tail, and the lower half part of the unmanned aerial vehicle is distributed and the lip at the rear end of the air inlet device enables the middle section of the unmanned aerial vehicle to form a streamline shape with the tail, so that the total flight resistance of the unmanned aerial vehicle is low, and the flow field is uniform.
8. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the bottom of the cabin begins to warp upwards at an angle of 14 degrees after the center of gravity until reaching the tail of the fuselage, so that the exhaust device is ensured to have a certain installation angle.
9. The novel aerodynamic layout of VTOL fixed wing UAVs of claim 1, characterized in that: the rear section of the fuselage is used for installing a driving core machine of the ducted fan.
10. The novel aerodynamic layout of VTOL fixed-wing UAVs of claim 1, characterized in that: the empennage comprises a horizontal empennage and a vertical empennage and is arranged at the tail.
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| US20040232279A1 (en) * | 2003-05-22 | 2004-11-25 | Melkuti Attila J. | VTOL/STOL ducted propeller aircraft |
| CN103910060A (en) * | 2013-01-09 | 2014-07-09 | 赵润生 | Combined-type push/lift airplane |
| US20180170517A1 (en) * | 2016-12-20 | 2018-06-21 | Bio-Cellular Design Aeronautics, Inc. | Variable geometry airframe for vertical and horizontal flight |
| CN110239710A (en) * | 2019-07-17 | 2019-09-17 | 郭亮 | A kind of electric power unmanned plane for the inspection of natural calamity situation |
| CN112443423A (en) * | 2020-11-24 | 2021-03-05 | 南京航空航天大学 | Jet propulsion power system of air-driven ducted fan |
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