Ducted power device, separable distributed ducted aircraft and working method of separable distributed ducted aircraft

Abstract

The invention relates to a ducted power device which comprises a fan casing, and a ducted power unit, a fixed rudder and a slip flow rudder which are sequentially arranged in a duct of the fan casing from an inlet to an outlet of the duct, and further comprises an undercarriage mounted on the fan casing at the outlet of the duct, and the undercarriage is used for supporting and buffering when the ducted power device vertically ascends and descends; the invention further provides a separable distributed ducted aircraft provided with the ducted power device and two working methods of the aircraft. The aircraft is simple in structure, the front-end aircraft body part, the wing aircraft body part and the duct power system of the aircraft all adopt modular separable design, duct array groups and fixed wings are combined to form a duct tailstock type layout, and the aircraft has two flight modes of hovering flight and high-speed cruising flight; the maneuverability and flexibility of vertical take-off and landing can be guaranteed, and the unmanned aerial vehicle is suitable for executing a long-distance cruise flight task and has the advantages of high efficiency, large load, low cost, high-speed long-endurance flight and the like.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and particularly to a distributed ducted aircraft. Background Art

[0002] The ducted tail-sitter vertical takeoff and landing aircraft combines the advantages of fixed-wing and rotary-wing UAVs, and has both hovering flight and high-speed cruise flight modes. It can not only ensure the mobility and flexibility of vertical takeoff and landing, but also be suitable for performing long-distance cruise flight missions.

[0003] Compared with the compound fixed-rotary-wing layout and the tilt-rotor layout, the ducted tail-sitter layout has no redundant drag and weight, and no complex tilting mechanism, so the flight efficiency is relatively high. Most of the existing ducted tail-sitter aircraft adopt a single-ducted power system. Such aircraft are limited by the thrust of the ducted power system during the vertical takeoff stage, and the weight of the payload carried is relatively low; since the thrust required for the horizontal flight of the aircraft is much smaller than the thrust required for vertical takeoff and landing, the utilization rate of the ducted power system and the control efficiency of the slipstream rudder are relatively low during horizontal flight; the front fuselage is inseparable from the wing fuselage and cannot perform air delivery flight missions; the ducted power system is inseparable from the aircraft body, which is not convenient for maintenance and repair. Summary of the Invention

[0004] The purpose of the present invention is to avoid the deficiencies of the prior art and provide a separable distributed ducted aircraft that can improve the payload weight of the ducted tail-sitter aircraft, improve the horizontal flight efficiency, reduce the use cost, expand the application flexibility, and increase the cost-effectiveness of the aircraft's mission execution.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is: a ducted power device, including a fan casing, and in the duct of the fan casing, there is successively arranged from the duct inlet to the outlet a ducted power group composed of an airborne equipment compartment, a fuel tank, an engine, and a propeller coaxially connected, as well as a mounting ring; One end of the fixed rudder is fixedly connected to the inner wall of the duct, and the other end of the fixed rudder is fixedly connected to the mounting ring. And a plurality of fixed rudders are evenly arranged in the circumferential direction of the duct, which are used to offset the counter torque of the propeller and for rectification; The slipstream rudder is located in the duct corresponding to the rectification outlet end of the fixed rudder; the servo is installed in the circumferential direction of the duct corresponding to the slipstream rudder, and is used to control the deflection of the slipstream rudder; It further includes a first support rod for strengthening the connection strength between the fan casing and the ducted power group. One end of the first support rod is fixedly connected to the inner wall of the duct, and the other end of the first support rod is fixedly connected to the fuel tank; And a landing gear installed on the fan casing at the duct outlet, and the landing gear is used for support and buffering during the vertical takeoff and landing of the ducted power device; Among them, a flight controller and sensors are provided in the airborne equipment compartment for the flight control and navigation of the ducted power plant; the fuel in the fuel tank supplies the engine, which in turn drives the propeller to rotate. The propeller is used to provide the power required for the vertical takeoff and landing and horizontal flight of the aircraft. The slipstream at the propeller flows through the slipstream rudder, and the servo controls the deflection of the slipstream rudder to achieve the control of the flight attitude of the ducted power plant.

[0006] Furthermore, the slipstream rudder is correspondingly arranged with the fixed rudder through the second support rod. The second support rod passes through the inside of the slipstream rudder and is fixed to the mounting ring. One end of the slipstream rudder is fixed to the corresponding servo, and the maximum deflection angle of the servo driving the slipstream rudder is ±30°; an anti-interference chamfer is provided at the other end of the slipstream rudder to avoid mutual interference when multiple slipstream rudders deflect cooperatively. At the same time, the radius of the mounting ring is 25% of the radius of the fan casing, and the clearance between the propeller tip and the inner wall of the duct is 4 - 6 mm to ensure the efficiency improvement brought by the duct.

[0007] The present invention also provides a separable distributed ducted aircraft provided with the ducted power plant, including a fuselage with airborne equipment and a fuel tank loaded inside, and wings on both sides of the fuselage for providing flight lift and roll motion control of the aircraft. The front fuselage can be detachably installed at the front end of the fuselage for loading payloads. Multiple ducted power plants are provided at the trailing edge of the wing and the rear end of the fuselage. The multiple ducted power plants are evenly installed at the trailing edge of the wing in the wingspan direction, forming a wing ducted power group for providing power and flight control during the vertical takeoff and vertical-horizontal conversion stages of the aircraft. The multiple ducted power plants are evenly arranged circumferentially around the fuselage axis at the rear end of the fuselage, forming a tail ducted power group for providing power and flight control during the entire flight stage of the aircraft.

[0008] Furthermore, the connection head fixed on the ducted power group of the ducted power plant is coaxially arranged with the duct of the fan casing; connection ports matching the connection head are respectively provided on the wing and the rear end of the fuselage, and the ducted power plant is installed on the wing and the rear end of the fuselage through the cooperation of the connection head and the connection port. At the same time, an oil delivery hole is provided on the connection head, one end of the oil delivery pipeline is communicated with the fuel tank in the fuselage, and the other end of the oil delivery pipeline is connected to the fuel tank of the ducted power plant for realizing the delivery of the fuel in the aircraft to the ducted power plant.

[0009] Furthermore, the front fuselage is made of carbon fiber composite material, the head of the front fuselage is hemispherical, the main body of the front fuselage is formed by the transition from a circular tube to a square tube, and the rear end of the front fuselage is connected to the fuselage through a connecting piece.

[0010] Furthermore, the fuselage section of the fuselage is made of carbon fiber composite material, and the main body of the fuselage section is in the shape of a square tube protruding upward and downward in the middle; The protruding parts of the main body of the fuselage section are used to arrange the wings and set the variable pitch slide rails for adjusting the wings. Since the wings and the variable pitch slide rails do not pass through the interior of the fuselage, it is used to reduce the structural weight and facilitate the arrangement of airborne equipment, fuel tanks and servo motors for driving the wings to move on the variable pitch slide rails inside the fuselage; The structure protruding downward is used to increase the internal volume of the fuselage, and at the same time make the fuselage have a streamlined aerodynamic shape; a round tube fixing bracket protrudes from the tail of the fuselage. An airborne equipment compartment and a fuel tank are arranged inside the fuselage. A fuel supply pipeline is arranged inside the tail round tube and the connecting bracket, and a connecting port is arranged at the end of the connecting bracket for connecting the tail duct power unit.

[0011] Furthermore, the wing is made of carbon fiber composite material and adopts the form of combining a low-drag wing tip with a segmented main wing; The low-drag wing tip of the wing means that the chord length of the tip of the wing is 65-75% of the chord length of the root, and the relative thickness is 10% of the wing tip, which is used to suppress the generation of wing tip vortices and reduce energy loss; the segmented main wing of the wing is divided into a thick wing straight wing segment with a relative thickness of 15% near the wing root and an intermediate trapezoidal wing segment that is tangentially transitioned with the straight wing segment; At the same time, the overall wing is in a high-wing layout, without sweepback or dihedral. A plurality of ailerons are arranged at the trailing edge of the wing, which is used for the roll motion control of the aircraft during horizontal flight; a connection port for connecting the duct power device is arranged between two adjacent ailerons. Fuel tanks and fuel supply pipelines are arranged inside the wing, which is used to balance the center of gravity of the whole aircraft and reduce the bending stress of the wing.

[0012] Furthermore, a plurality of duct power devices of the wing duct power unit are symmetrically and evenly arranged along the span of the wing, and the combined center of gravity action point of the wing duct power unit is located inside the fuselage axis, 5% behind the center of gravity of the whole aircraft, which is used to reduce the influence on the flight center of gravity of the aircraft when the wing duct power unit is separated from the wing; A plurality of duct power devices are installed at the tail end of the fuselage through a connecting bracket. The connecting bracket includes a connecting strut on the fuselage axis. One end of the connecting strut is fixedly connected to the tail end of the fuselage. The other end of the connecting strut is provided with a plurality of rods extending radially towards the duct, and the rods are evenly distributed in the circumferential direction of the duct. A plurality of duct power devices are installed on the rods through connecting heads.

[0013] The present invention also provides a cruise working method for the separable distributed duct aircraft described above. The flight actions of the aircraft are realized by the deflection of the ailerons located at the trailing edge of the wing and the deflection of the slipstream rudders and the adjustment of the propeller speed of the duct power devices of the wing duct power unit and the tail duct power unit; at the same time, the flight control and navigation of the aircraft are realized by the central flight controller and sensors provided inside the fuselage; Among them, the central flight controller judges the current flight attitude and position as well as the target flight attitude and position based on the parameters obtained by the sensors, generates control instructions for the target attitude and position, controls the aileron deflection, and sends the control instructions to the flight controller in the airborne equipment compartment of the ducted propulsion device, thereby controlling the deflection angle of the corresponding slipstream rudder and the rotation speed of the propeller; Furthermore, the implemented flight operation method of the aircraft is as follows: In the vertical takeoff stage, the thrust generated by the wing ducted propulsion unit and the tail ducted propulsion unit is used to balance the gravity of the aircraft itself to complete vertical climb; In the vertical-to-horizontal conversion stage, the wing ducted propulsion unit and the tail ducted propulsion unit cooperate to control and generate a control moment to complete the mode conversion; At the end of the vertical-to-horizontal conversion stage, the wing ducted propulsion unit is separated from the wing, reducing the weight of the aircraft itself and improving the cruise efficiency of the aircraft; each ducted propulsion device in the separated wing ducted propulsion unit forms a formation through the control of the flight controller and autonomously returns to land at the recovery site; During the horizontal flight stage, the aircraft relies on the tail ducted propulsion unit to meet the thrust requirement for horizontal flight; After the aircraft completes its mission, due to the consumption of fuel in the fuselage and wings, the weight of the aircraft is further reduced, and it relies on the tail ducted propulsion unit to achieve flight in the horizontal-to-vertical conversion stage and the vertical landing stage. At this time, a flight mission is completed.

[0014] The present invention also provides a delivery operation method for the separable distributed ducted aircraft described above. The flight actions of the aircraft are achieved by the deflection of the ailerons located at the trailing edge of the wing and the deflection of the slipstream rudders and the adjustment of the rotation speed of the propellers of the ducted propulsion devices of the wing ducted propulsion unit and the tail ducted propulsion unit; at the same time, the flight control and navigation of the aircraft are achieved by the central flight controller and sensors provided inside the fuselage; Among them, the central flight controller judges the current flight attitude and position as well as the target flight attitude and position based on the parameters obtained by the sensors, generates control instructions for the target attitude and position, controls the aileron deflection, and sends the control instructions to the flight controller in the airborne equipment compartment of the ducted propulsion device, thereby controlling the deflection angle of the corresponding slipstream rudder and the rotation speed of the propeller; Furthermore, the implemented delivery operation method of the aircraft is as follows: In the vertical takeoff stage, the thrust generated by the wing ducted propulsion unit and the tail ducted propulsion unit is used to balance the gravity of the aircraft itself to complete vertical climb; In the vertical-to-horizontal conversion stage, the wing ducted propulsion unit and the tail ducted propulsion unit cooperate to control and generate a control moment to complete the mode conversion; At the end of the vertical-horizontal conversion stage, the wing duct power unit separates from the wing, reducing the weight of the aircraft and improving the cruise efficiency of the aircraft; each duct power device in the separated wing duct power unit forms a formation through the control of the flight controller and autonomously returns to land at the recovery site; When the aircraft flies to the predetermined delivery location, the front fuselage separates from the aircraft and descends to the predetermined location by parachute, thus realizing the delivery of the front fuselage; at this time, the aircraft trims by adjusting the position of the wing backward. A servo motor is arranged inside the fuselage to drive the wing to move backward along the variable pitch slide rail arranged on the upper part of the fuselage to realize the trimming of the aircraft; The aircraft then flies horizontally to the sky above the recovery site; The aircraft relies on the tail duct power unit to realize the flight in the horizontal-vertical conversion stage and the vertical landing stage, completing a delivery flight mission.

[0015] The beneficial effects of the present invention are as follows: The separable distributed duct aircraft provided by the present invention adopts a modular separable design for its front fuselage part, wing fuselage part, and duct power system. The duct array group is combined with the fixed wing to form a duct tail-sitter layout, having both hovering flight and high-speed cruise flight modes.

[0016] By combining the duct power systems to form a vector duct array group, the payload loading capacity of the duct tail-sitter aircraft is greatly improved; at the end of the vertical-horizontal conversion stage, the wing duct power unit separates, which is beneficial to reducing the waste weight during cruise flight and improving the flight efficiency; the separated wing duct power unit can be autonomously recovered and reused, significantly reducing the usage cost; the front fuselage and the wing fuselage adopt a separable design, which is convenient for the aircraft to perform flight missions such as material delivery, broadening the application scenarios of such duct aircraft; Generally speaking, it can not only ensure the mobility and flexibility of vertical takeoff and landing, but also be suitable for performing long-distance cruise flight missions. Each part adopts a separable design, having advantages such as high efficiency, large load capacity, low cost, and high-speed long-endurance flight. Description of the Drawings

[0017] Figure 1 is the overall structural schematic diagram of the separable distributed duct aircraft of the present invention; Figure 2 is the front view structural schematic diagram of the separable distributed duct aircraft of the present invention; Figure 3 is the top view structural schematic diagram of the separable distributed duct aircraft of the present invention; Figure 4 is the right view structural schematic diagram of the separable distributed duct aircraft of the present invention; Figure 5 is the schematic diagram of the duct power device of the present invention; Figure 6 It is the vertical take-off configuration diagram of Embodiments 3 and 4 of the present invention; Figure 7 It is the horizontal flight configuration diagram of Embodiments 3 and 4 of the present invention; Figure 8 It is the vertical landing configuration diagram of Embodiments 3 and 4 of the present invention; Figure 9 It is the schematic diagram of the variable pitch slide rail and servo motor arrangement of the separable distributed ducted aircraft of the present invention; Figure 10 It is the method diagram of the aircraft performing cruise flight tasks in Embodiment 3 of the present invention; Figure 11 It is the method diagram of the aircraft performing delivery flight tasks in Embodiment 4 of the present invention.

[0018] In the figure, 1-separable front fuselage, 2-fuselage, 3-wing, 4-aileron, 5-connecting frame, 6-wing ducted power group, 7-tail ducted power group, 8-supporting rod, 9-fan casing, 10-carbon fiber landing gear, 11-connecting head, 12-airborne equipment compartment, 13-fuel tank, 14-engine, 15-propeller, 16-stabilizer, 17-slipstream rudder, 18-servo motor, 19-connecting ring, 20-variable pitch slide rail, 21-servo motor. Specific Embodiments

[0019] The principles and features of the present invention will be described below in conjunction with the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0020] To achieve the above object, the present invention provides the following specific embodiments: Embodiment 1: As Figure 5 shown, a ducted power device, in Figure 5 , includes a fan casing 9 and inside the duct of the fan casing 9, a ducted power group consisting of an airborne equipment compartment 12, a fuel tank 13, an engine 14, and a propeller 15 coaxially connected in sequence from the duct inlet to the outlet, and a mounting ring 19; One end of the fixed rudder 16 is fixedly connected to the inner wall of the duct, and the other end of the fixed rudder 16 is fixedly connected to the mounting ring 19, and a plurality of fixed rudders 16 are evenly arranged in the circumferential direction of the duct for canceling the reaction torque of the propeller 15 and rectifying; The slipstream rudder 17 is inside the duct corresponding to the rectifying outlet end of the fixed rudder 16; the servo motor 18 is installed in the circumferential direction of the duct corresponding to the slipstream rudder 17 for controlling the deflection of the slipstream rudder 17; It further includes a first supporting rod 8 for strengthening the connection strength between the fan casing 9 and the ducted power group. One end of the first supporting rod 8 is fixedly connected to the inner wall of the duct, and the other end of the first supporting rod 8 is fixedly connected to the fuel tank 13; And, a landing gear 10 is installed on the fan casing 9 at the exit of the duct. The landing gear 10 is used for support and buffering during the vertical takeoff and landing of the ducted power plant; Among them, a flight controller and sensors are provided in the airborne equipment compartment 12 for flight control and navigation of the ducted power plant; the fuel in the fuel tank 13 supplies the engine 14 to drive the propeller 15 to rotate. The propeller 15 is used to provide the power required for the vertical takeoff and landing and horizontal flight of the aircraft. The slipstream at the propeller 15 flows through the slipstream rudder 17, and the servo 18 controls the deflection of the slipstream rudder 17 to achieve control of the flight attitude of the ducted power plant.

[0021] The slipstream rudder 17 is arranged corresponding to the fixed rudder 16 through the second support rod. The second support rod passes through the inside of the slipstream rudder 17 and is fixedly connected to the mounting ring 19. One end of the slipstream rudder 17 is fixedly connected to the corresponding servo 18. The maximum deflection angle of the servo 18 driving the slipstream rudder 17 is ±30°; an anti-interference chamfer is provided at the other end of the slipstream rudder 17 to avoid mutual interference when multiple slipstream rudders 17 deflect cooperatively; Meanwhile, the radius of the mounting ring 19 is 25% of the radius of the fan casing 9, and the clearance between the tip of the propeller 15 and the inner wall of the duct is 4 - 6 mm, which is used to ensure the efficiency improvement brought by the duct.

[0022] Embodiment 2: As Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 9 shown, the present invention also provides a separable distributed ducted aircraft provided with a ducted power plant. In Figure 1 、 Figure 2 、 Figure 3 it includes a fuselage 2 internally loaded with airborne equipment and fuel tanks, and wings 3 on both sides of the fuselage 2 for providing flight lift and roll motion control for the aircraft; The front fuselage 1 can be detachably installed at the front end of the fuselage 2 for loading payloads; A plurality of ducted power plants are provided at the trailing edge of the wing 3 and the rear end of the fuselage 2; A plurality of ducted power plants are evenly installed on the trailing edge of the wing 3 in the span direction of the wing 3 to form a wing ducted power group 6 for providing power and flight control during the vertical takeoff and vertical-horizontal conversion stages of the aircraft; A plurality of ducted power plants are evenly arranged circumferentially around the axis of the fuselage 2 at the tail end of the fuselage 2 to form a tail ducted power group 7 for providing power and flight control during the entire flight stage of the aircraft.

[0023] The connector 11 fixedly connected to the ducted power unit of the ducted power device is coaxially arranged with the duct of the fan casing 9; connection ports matching the connector 11 are respectively provided on the wing 3 and the tail end of the fuselage 2, and the ducted power device is installed on the wing 3 and the tail end of the fuselage 2 through the cooperation of the connector 11 and the connection ports. Meanwhile, an oil delivery hole is provided on the connector 11. One end of the oil delivery pipeline is communicated with the fuel tank in the fuselage 2, and the other end of the oil delivery pipeline is communicated with the fuel tank 13 of the ducted power device, so as to realize the delivery of the fuel in the aircraft to the ducted power device.

[0024] As Figure 4 shown, the front fuselage 1 is made of carbon fiber composite material. The head of the front fuselage 1 is hemispherical, the main body of the front fuselage 1 is formed by the transition from a circular tube to a square tube, and the tail of the front fuselage 1 is connected to the fuselage 2 through a connecting piece.

[0025] As Figure 4 shown, the fuselage section of the fuselage 2 is made of carbon fiber composite material, and the main body of the fuselage section is in the shape of a square tube with upper and lower protrusions in the middle. As Figure 9 shown, the protruding parts of the main body of the fuselage section are used to arrange the wing 3 and the variable pitch slide rail 20 for adjusting the wing. Since the wing 3 and the variable pitch slide rail 20 do not pass through the interior of the fuselage, it is used to reduce the structural weight and facilitate the arrangement of the on-board equipment, fuel tank and the servo motor 21 for driving the wing 3 to move on the variable pitch slide rail 20 inside the fuselage 2. The structure with the lower protrusion is used to increase the internal volume of the fuselage 2, and at the same time make the fuselage 2 have a streamlined aerodynamic shape; a round tube fixed connection frame extends from the tail of the fuselage 2. An on-board equipment compartment and a fuel tank are arranged inside the fuselage 2. An oil supply pipeline is arranged inside the tail round tube and the connection frame, and a connection port is arranged at the end of the connection frame for connecting the tail ducted power unit 7.

[0026] As Figure 1 shown, the wing 3 is made of carbon fiber composite material and adopts the form of combining a low-drag wing tip and a segmented main wing. The low-drag wing tip of the wing 3 means that the chord length of the tip of the wing 3 is 65-75% of the chord length of the root, and the relative thickness is 10% of the wing tip, which is used to suppress the generation of wing tip vortices and reduce energy loss. The segmented main wing of the wing 3 is divided into a thick wing straight wing section with a relative thickness of 15% near the wing root and an intermediate trapezoidal wing section that is tangentially transitioned with the straight wing section. Meanwhile, as Figure 2As shown, the overall wing 3 is in a high-wing layout, without sweepback or dihedral. Multiple ailerons 4 are provided at the trailing edge of the wing 3 for controlling the roll motion of the aircraft during horizontal flight. Connection ports for connecting the ducted power units are provided between every two ailerons 4. Fuel tanks and fuel supply pipelines are arranged inside the wing to balance the center of gravity of the whole aircraft and reduce the bending stress of the wing.

[0027] As Figures 1 - 3 shown, multiple ducted power units of the wing ducted power group 6 are symmetrically and evenly arranged along the span of the wing 3, and the center of gravity of the combined gravity of the wing ducted power group 6 is located inside the fuselage axis, 5% behind the center of gravity of the whole aircraft, which is used to reduce the influence on the flight center of gravity of the aircraft when the wing ducted power group 6 is separated from the wing 3; Multiple ducted power units are installed at the tail end of the fuselage 2 through the connecting frame 5. The connecting frame 5 includes a connecting strut on the axis of the fuselage 2. One end of the connecting strut is fixedly connected to the tail end of the fuselage 2, and the other end of the connecting strut is provided with multiple rods extending radially towards the duct, and the rods are evenly distributed in the circumferential direction of the duct. Multiple ducted power units are installed on the rods through the connecting heads 11.

[0028] Embodiment 3: As Figure 6 、 7 shown in Figures 8 and 10, the present invention also provides a patrolling flight working method for a separable distributed ducted aircraft. The flight actions of the aircraft are realized by the deflection of the ailerons 4 located at the trailing edge of the wing 3 and the deflection of the slipstream rudders 17 and the adjustment of the rotation speed of the propellers 15 of the ducted power units of the wing ducted power group 6 and the tail ducted power group 7; at the same time, the flight control and navigation of the aircraft are realized by the central flight controller and sensors provided inside the fuselage 2; Among them, the central flight controller judges the current flight attitude and position and the target flight attitude and position based on the parameters obtained by the sensors, generates control instructions for the target attitude and position, controls the deflection of the ailerons 4, and sends the control instructions to the flight controller in the on-board equipment compartment 12 of the ducted power unit, so as to control the deflection angle of the corresponding slipstream rudders 17 and the rotation speed of the propellers 15; Furthermore, the realized patrolling flight working method of the aircraft, as Figure 10 shown, specifically is: In the vertical take-off stage, as Figure 6 shown in the figure, the thrust generated by the wing ducted power group 6 and the tail ducted power group 7 is used to balance the gravity of the aircraft itself to complete vertical climb; In the vertical-horizontal conversion stage, the wing ducted power group 6 and the tail ducted power group 7 cooperate to control to generate a control moment to complete the mode conversion; When the vertical-horizontal conversion stage ends, as Figure 7In [description], the wing duct power unit 6 is separated from the wing 3, reducing the self-weight of the aircraft and improving the cruise efficiency of the aircraft. Each duct power device in the separated wing duct power unit 6 forms a formation through the control of the flight controller and autonomously returns to land at the recovery site. During the horizontal flight phase of the aircraft, the tail duct power unit 7 is relied on to meet the thrust requirement for horizontal flight. After the aircraft completes its mission, such as Figure 8 In [description], due to the consumption of fuel in the fuselage 2 and the wing 3, the self-weight of the aircraft is further reduced. The tail duct power unit 7 is relied on to achieve flight in the horizontal-vertical conversion phase and the vertical landing phase. At this time, a cruise mission is completed.

[0029] Embodiment 4: As shown in Figure 6 、 7 、8, and 11, the present invention also provides a delivery working method for a separable distributed duct aircraft. The flight actions of the aircraft are achieved by the deflection of the ailerons 4 located at the trailing edge of the wing 3 and the deflection of the slipstream rudders 17 and the adjustment of the rotational speed of the propellers 15 of the duct power devices of the wing duct power unit 6 and the tail duct power unit 7. At the same time, the flight control and navigation of the aircraft are achieved by the central flight controller and sensors provided inside the fuselage 2. Among them, the central flight controller judges the current flight attitude and position and the target flight attitude and position based on the parameters obtained by the sensors, generates control commands for the target attitude and position, controls the deflection of the ailerons 4, and sends the control commands to the flight controller in the airborne equipment compartment 12 of the duct power device, thereby controlling the deflection angle of the corresponding slipstream rudders 17 and the rotational speed of the propellers 15. Furthermore, the delivery working method of the aircraft achieved is as shown in Figure 11 and specifically is: During the vertical takeoff phase, Figure 6 In [description], the thrust generated by the wing duct power unit 6 and the tail duct power unit 7 is used to balance the self-gravity of the aircraft to complete vertical climb. During the vertical-horizontal conversion phase, the wing duct power unit 6 and the tail duct power unit 7 cooperate to control and generate a control moment to complete the mode conversion. When the vertical-horizontal conversion phase ends, Figure 7 In [description], the wing duct power unit 6 is separated from the wing 3, reducing the self-weight of the aircraft and improving the cruise efficiency of the aircraft. Each duct power device in the separated wing duct power unit 6 forms a formation through the control of the flight controller and autonomously returns to land at the recovery site. When the aircraft flies to the predetermined delivery location, the front fuselage 1 separates from the aircraft and descends to the predetermined location by parachute, thus realizing the delivery of the front fuselage 1; at this time, the aircraft trims by adjusting the position of the wing 3 backward. A servo motor 21 is arranged inside the fuselage 2 to drive the wing 3 to move backward along the variable pitch slide rail 20 arranged on the upper part of the fuselage 2 to achieve aircraft trimming. The aircraft then flies horizontally to the sky above the recovery field. As Figure 8 shown, the aircraft relies on the tail duct power unit 7 to achieve flight in the horizontal-vertical conversion stage and the vertical landing stage, completing a delivery flight mission.

[0030] The technical solutions and effects of the present invention will be further described below in conjunction with the accompanying drawings: As Figure 1 shown, the present invention provides a separable distributed duct aircraft, which includes a separable front fuselage 1, a fuselage 2, wings 3, ailerons 4, a connecting frame 5, a wing duct power unit 6, and a tail duct power unit 7. As Figure 5 shown, the duct power system includes an aluminum alloy support rod 8, a duct 9, a carbon fiber landing gear 10, a connecting head 11, an airborne equipment compartment 12, a fuel tank 13, an engine 14, a propeller 15, a stabilizer 16, a slipstream rudder 17, a servo 18, and a connecting ring 19.

[0031] As Figures 1 - 4 shown, the separable front fuselage 1 is fixed in front of the fuselage 2 for loading payloads; the front part of the fuselage 2 is arranged with an airborne equipment compartment, and the middle and rear parts are arranged with fuel tanks; the wings 3 are fixed above the fuselage 2, and connection ports are arranged at the rear ends of both wings for connecting the wing duct power unit 6, and fuel tanks and fuel supply pipelines are arranged inside the wings; the ailerons 4 are arranged at the trailing edges of both wings for controlling the rolling motion during the horizontal flight of the aircraft; the connecting frame 5 is connected to the fuselage 2 through a round tube, and fuel supply pipelines are arranged inside it, and a connection port is arranged at each end of the connecting frame; the wing duct power unit 6 is fixed behind the wing through the connection port located at the rear end of the wing, and the center of gravity of the wing duct power unit is near the center of gravity of the whole aircraft; the tail duct power unit 7 is fixed behind the connecting frame through the connection port located at the end of the connecting frame.

[0032] Both the wing duct power unit 6 and the tail duct power unit 7 are composed of Figure 5It is composed of the ducted power systems shown. The aluminum alloy support rod 8 is used to connect the body of the ducted power system and the duct; the duct 9 is a ring-shaped outer shell that forms an enclosure around the upper part of the propeller 15, the stabilizer 16, and the slipstream rudder 17, and has the functions of lift augmentation, protection, and noise reduction; the carbon fiber landing gear 10 is arranged below the duct 9 and is used for the support and buffering during the vertical takeoff and landing of the aircraft or the duct; the connector 11 is located at the top of the body of the ducted power system and is used to connect the aircraft body and the ducted power system. An oil receiving port is arranged inside it for receiving fuel supply from the fuel tank inside the aircraft body; the on-board equipment compartment 12 contains sensors and a flight controller, which are used to measure the flight state and generate control commands; the fuel tank 13 is used to load fuel to ensure the fuel supply during the independent flight of the ducted power system; the engine 14 receives the fuel from the fuel tank 13 and provides power for the propeller 15; the propeller 15 provides the thrust required for the flight of the ducted power system and the aircraft; the stabilizer 16 is arranged below the propeller 15 and is used to counteract the anti-torque during the rotation of the propeller 15 and rectify the propeller slipstream; the slipstream rudder 17 can generate roll, pitch, and yaw moments through combined deflection and is used to control the flight attitude; the servo 18 is arranged inside the duct 9 and is used to drive the deflection of the slipstream rudder; the connecting ring 19 connects the stabilizer 16 and can effectively increase the structural strength.

[0033] Three ailerons 4 are arranged at the rear ends on both sides of the wing 3 to provide a roll control moment during the horizontal flight of the aircraft.

[0034] A connection port is arranged on the inner side of each aileron 4, and the wing ducted power group 6 is composed of 6 sets of ducted power systems.

[0035] The connecting frame 5 is in a cross shape, and a connection port is arranged at each of its four ends. The tail ducted power group 7 is composed of 4 sets of ducted power systems.

[0036] The thrust of a single set of ducted power system is 60 kg.

[0037] The maximum takeoff weight of the separable distributed ducted aircraft is 500 kg, the cruise speed is 160 km / h, the ceiling is 6 km, the flight time is ≥20 h, the mission radius is ≥1600 km, the payload is ≥100 kg, the wind resistance characteristic is level 7, and the takeoff and landing preparation time is ≤30 min.

[0038] The separable front-end body 1, the fuselage 2, and the wing 3 are made of carbon fiber composite materials, which have the advantages of light weight, high strength, corrosion resistance, and wear resistance.

[0039] The head of the separable front fuselage 1 is hemispherical, transitioning from a circular tube shape to a square tube shape from the front to the rear, with a good streamlined aerodynamic shape and facilitating connection to the fuselage 2. Both the upper and lower parts of the fuselage 2 protrude smoothly. The upper protrusion is used to connect the wing 3, and the lower protrusion is used to increase the fuel tank capacity. Inside the fuselage 2, a central flight controller and sensors are arranged. The sensors are used to measure motion parameters such as the position, ground speed, airspeed, altitude, and attitude of the airship, and transmit the parameters to the central flight controller; the central flight controller judges the current flight attitude and position as well as the target flight attitude and position based on the obtained parameters, and generates control instructions for the target attitude and position; the control instructions are sent to the distributed flight controllers of the ailerons and the ducted power system, and the flight attitude of the aircraft is changed by the deflection of the ailerons, the combined deflection of the slipstream rudders of each ducted power system, and the adjustment of the propeller speed.

[0040] The skin of the duct 9 is made of carbon fiber composite material, the structural support is made of aviation aluminum alloy, and the internal support is made of a metal frame beam rib structure. While ensuring the rigidity and strength, the structural weight is reduced. The skin and crossbeam of the propeller 15 are made of carbon fiber composite material and filled with PMI foam inside, providing thrust inside the duct 9.

[0041] The gap between the inner wall of the duct and the propeller tip of the ducted power system is 5 mm, ensuring the efficiency improvement brought by the duct. The structure of the duct 9 is integrally formed with lightweight composite materials. The duct shell separates the propeller from the external environment, which can protect the safety of the operator and reduce the noise propagation. Further, the duct shell adopts an airfoil profile structure. The duct shell with a certain inverted cone angle can improve the airflow distribution in the propeller slipstream area, and at the same time, the duct wall can provide a part of additional lift during flight, having higher aerodynamic efficiency than ordinary rotor aircraft.

[0042] The following embodiments are used to illustrate the process of using the separable distributed ducted aircraft of the present invention to perform cruise and delivery flight tasks.

[0043] The figure of the separable distributed ducted aircraft performing cruise flight tasks is as Figure 10 shown. The vertical takeoff configuration of the separable distributed ducted aircraft is as Figure 6 shown. During the vertical takeoff stage, the thrust generated by the wing duct power unit 6 and the tail duct power unit 7 is used to balance the gravity of the aircraft itself to complete vertical climb. During the vertical-to-horizontal conversion stage, the wing duct power unit 6 and the tail duct power unit 7 cooperate to control to generate a control moment to complete the mode conversion. At the end of the vertical-to-horizontal conversion stage, the wing duct power unit 6 separates from the aircraft. Since the center of gravity of the wing duct power unit 6 is near the center of gravity of the whole aircraft, its separation has little impact on the center of gravity of the aircraft. Each set of ducted power systems has independent on-board equipment and power sources, and the separated ducted power systems can form a formation to autonomously return and land at the recovery field. The horizontal flight configuration of the separable distributed ducted aircraft is asFigure 7 As shown. The thrust required for the aircraft during the horizontal flight phase is much less than that required for vertical takeoff and landing. Therefore, relying on the tail duct power unit 7 can meet the thrust requirement for horizontal flight. At the same time, the separation of the wing duct power unit 6 can effectively reduce the self-weight of the aircraft and improve the cruise efficiency. The vertical landing configuration of the separable distributed duct aircraft is as Figure 8 shown. After the aircraft completes its mission, due to the consumption of fuel in the fuselage and wings, the self-weight of the airframe is further reduced. Relying on the tail duct power unit 7, it can achieve flight during the horizontal-vertical conversion phase and the vertical landing phase, completing a fly-and-loiter type flight mission.

[0044] The sectional view of the separable distributed duct aircraft performing a delivery type flight mission is as Figure 11 shown. During the vertical takeoff phase, the thrust generated by the wing duct power unit 6 and the tail duct power unit 7 is used to balance the self-gravity of the aircraft and complete vertical climb. During the vertical-horizontal conversion phase, the wing duct power unit 6 and the tail duct power unit 7 cooperate to control and generate a control moment to complete the mode conversion. At the end of the vertical-horizontal conversion phase, the wing duct power unit 6 is separated from the aircraft. The separated duct power system can form a formation and autonomously return to land at the recovery site. When the aircraft flies to the predetermined delivery location, the separable front fuselage 1 loaded with the payload is separated from the aircraft. The separated separable front fuselage 1 opens the parachute and lands at the predetermined location. The separated aircraft can trim the aircraft by adjusting the position of the wing backward, and then the aircraft flies horizontally to the sky above the recovery site. Due to the consumption of fuel in the fuselage and wings and the delivery of the payload, the self-weight of the airframe is further reduced. Relying on the tail duct power unit 7, it can achieve flight during the horizontal-vertical conversion phase and the vertical landing phase, completing a delivery type flight mission.

[0045] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A ducted power device, characterized in that, It includes a fan casing (9), and inside the duct of the fan casing (9), there is a duct power unit successively arranged from the duct inlet to the outlet, which is composed of an airborne equipment compartment (12), a fuel tank (13), an engine (14), and a propeller (15) connected coaxially, as well as a mounting ring (19); One end of a fixed rudder (16) is fixedly connected to the inner wall of the duct, and the other end of the fixed rudder (16) is fixedly connected to the mounting ring (19). Moreover, a plurality of fixed rudders (16) are evenly arranged in the circumferential direction of the duct, which are used to offset the reaction torque of the propeller (15) and for flow rectification; A slipstream rudder (17) is arranged inside the duct corresponding to the rectification outlet end of the fixed rudder (16); a servo (18) is installed circumferentially inside the duct corresponding to the slipstream rudder (17), which is used to control the deflection of the slipstream rudder (17); It further includes a first support rod (8) for strengthening the connection strength between the fan casing (9) and the duct power unit. One end of the first support rod (8) is fixedly connected to the inner wall of the duct, and the other end of the first support rod (8) is fixedly connected to the fuel tank (13); In addition, a landing gear (10) is installed on the fan casing (9) at the duct outlet, and the landing gear (10) is used for support and buffering during the vertical takeoff and landing of the duct power device; Among them, a flight controller and sensors are arranged in the airborne equipment compartment (12), which are used for the flight control and navigation of the duct power device; the fuel in the fuel tank (13) supplies the engine (14) and then drives the propeller (15) to rotate. The propeller (15) is used to provide the power required for the vertical takeoff and landing and horizontal flight of the aircraft. The slipstream at the propeller (15) flows through the slipstream rudder (17), and the servo (18) controls the deflection of the slipstream rudder (17) to achieve the control of the flight attitude of the duct power device.

2. The ducted power device according to claim 1, characterized in that, The slipstream rudder (17) is arranged corresponding to the fixed rudder (16) through a second support rod. The second support rod passes through the inside of the slipstream rudder (17) and is fixedly connected to the mounting ring (19). One end of the slipstream rudder (17) is fixedly connected to the corresponding servo (18), and the maximum deflection angle of the servo (18) driving the slipstream rudder (17) is ±30°; an anti-interference chamfer is arranged at the other end of the slipstream rudder (17), which is used to avoid the mutual interference when multiple slipstream rudders (17) deflect cooperatively; Meanwhile, the radius of the mounting ring (19) is 25% of the radius of the fan casing (9), and the clearance between the tip of the propeller (15) and the inner wall of the duct is 4 - 6 mm, which is used to ensure the efficiency improvement brought by the duct.

3. A separable distributed ducted aircraft provided with the ducted power device as described in claims 1-2, characterized in that, It includes a fuselage (2) internally loaded with airborne equipment and a fuel tank, and wings (3) on both sides of the fuselage (2) for providing flight lift and roll motion control for the aircraft; The front-end fuselage (1) can be detachably installed at the front end of the fuselage (2), which is used to load payloads; A plurality of duct power devices are arranged at the trailing edge of the wing (3) and the rear end of the fuselage (2); A plurality of duct power devices are evenly installed on the trailing edge of the wing (3) in the span direction of the wing (3), forming a wing duct power group (6), which is used to provide power and flight control for the aircraft during the vertical takeoff and vertical-horizontal conversion stages; A plurality of ducted power devices are evenly arranged circumferentially around the axis of the fuselage (2) at the tail end of the fuselage (2), forming a tail ducted power group (7) for providing power and flight control for the aircraft during the entire flight stage.

4. The separable distributed ducted aircraft according to claim 3, wherein, A connector (11) fixedly connected to the ducted power group of the ducted power device is coaxially arranged with the duct of the fan casing (9); connection ports matching the connector (11) are respectively provided on the wing (3) and the tail end of the fuselage (2), and the ducted power device is installed on the wing (3) and the tail end of the fuselage (2) through the cooperation of the connector (11) and the connection port. Meanwhile, an oil delivery hole is provided on the connector (11), one end of the oil delivery pipeline is communicated with the fuel tank in the fuselage (2), and the other end of the oil delivery pipeline is connected to the fuel tank (13) of the ducted power device, for realizing the delivery of the fuel in the aircraft to the ducted power device.

5. The separable distributed ducted aircraft according to claim 3, characterized in that, The front fuselage (1) is made of carbon fiber composite material, the head of the front fuselage (1) is hemispherical, the main body of the front fuselage (1) is formed by the transition from a circular tube to a square tube, and the tail of the front fuselage (1) is connected to the fuselage (2) through a connecting piece.

6. The separable distributed ducted aircraft according to claim 3, characterized in that, The fuselage section of the fuselage (2) is made of carbon fiber composite material, and the main body of the fuselage section is in the shape of a square tube with upper and lower protrusions in the middle. The protruding parts of the main body of the fuselage section are used for arranging the wing (3) and setting the variable pitch slide rail (20) for adjusting the wing. Since the wing (3) and the variable pitch slide rail (20) do not pass through the interior of the fuselage, it is used to reduce the structural weight and facilitate the arrangement of the on-board equipment, fuel tank and the servo motor (21) for driving the wing (3) to move on the variable pitch slide rail (20) inside the fuselage (2). The lower protruding structure is used to increase the internal volume of the fuselage (2), and at the same time makes the fuselage (2) have a streamlined aerodynamic shape; a circular tube fixed connection frame extends from the tail of the fuselage (2), an on-board equipment cabin and a fuel tank are arranged inside the fuselage (2), an oil supply pipeline is arranged inside the tail circular tube and the connection frame, and a connection port is arranged at the end of the connection frame for connecting the tail ducted power group (7).

7. The separable distributed ducted aircraft according to claim 3, wherein The wing (3) is made of carbon fiber composite material and adopts the form of combining a low-drag wing tip with a segmented main wing. The low-drag wing tip of the wing (3) means that the chord length of the tip of the wing (3) is 65-75% of the chord length of the root, and the relative thickness is 10% of the wing tip, which is used to suppress the generation of wing tip vortices and reduce energy loss. The segmented main wing of the wing (3) is divided into a thick wing straight wing section with a relative thickness of 15% near the wing root and an intermediate trapezoidal wing section tangent to the straight wing section. Meanwhile, the overall wing (3) is in the upper single-wing layout, without sweepback and dihedral. A plurality of ailerons (4) are arranged at the trailing edge of the wing (3) for controlling the rolling motion of the aircraft during horizontal flight; connection ports for connecting the ducted power device are arranged between every two ailerons (4), and a fuel tank and an oil supply pipeline are arranged inside the wing for balancing the center of gravity of the whole aircraft and reducing the bending stress of the wing.

8. The separable distributed ducted aircraft according to any one of claims 3-7, characterized in that A plurality of ducted power devices of the wing ducted power group (6) are symmetrically and uniformly arranged along the span of the wing (3), and the center of gravity of the combined gravity of the wing ducted power group (6) is located within the fuselage axis, 5% behind the center of gravity of the whole aircraft, so as to reduce the influence on the flight center of gravity of the aircraft when the wing ducted power group (6) is separated from the wing (3); The plurality of ducted power devices are installed at the tail end of the fuselage (2) through a connecting frame (5). The connecting frame (5) includes a connecting strut on the axis of the fuselage (2). One end of the connecting strut is fixedly connected to the tail end of the fuselage (2), and the other end of the connecting strut is provided with a plurality of rods extending radially towards the duct, and the rods are evenly distributed in the circumferential direction of the duct. The plurality of ducted power devices are installed on the rods through connecting heads (11).

9. A cruise flight working method of a separable distributed ducted aircraft as described in claims 3-8, characterized in that, The flight actions of the aircraft are achieved by the deflection of the ailerons (4) located at the trailing edge of the wing (3) and the deflection of the slipstream rudders (17) and the speed regulation of the propellers (15) of the ducted power devices of the wing ducted power group (6) and the tail ducted power group (7); meanwhile, the flight control and navigation of the aircraft are achieved by a central flight controller and sensors provided inside the fuselage (2); Among them, the central flight controller judges the current flight attitude and position and the target flight attitude and position based on the parameters obtained by the sensors, generates control commands for the target attitude and position, controls the deflection of the ailerons (4), and sends the control commands to the flight controller in the on-board equipment compartment (12) of the ducted power device, so as to control the deflection angle of the corresponding slipstream rudders (17) and the speed of the propellers (15); Furthermore, the working method of the aircraft's loiter flight achieved is as follows: In the vertical take-off stage, the thrust generated by the wing ducted power group (6) and the tail ducted power group (7) is used to balance the gravity of the aircraft itself to complete vertical climb; In the vertical-to-horizontal conversion stage, the wing ducted power group (6) and the tail ducted power group (7) cooperate to control the generation of a control moment to complete the mode conversion; At the end of the vertical-to-horizontal conversion stage, the wing ducted power group (6) is separated from the wing (3), reducing the weight of the aircraft itself and improving the cruise efficiency of the aircraft; each ducted power device in the separated wing ducted power group (6) forms a formation through the control of the flight controller and autonomously returns to land at the recovery site; The aircraft relies on the tail ducted power group (7) to meet the thrust requirement for horizontal flight during the horizontal flight stage; After the aircraft completes its mission, due to the consumption of fuel in the fuselage (2) and the wing (3), the weight of the aircraft is further reduced, and the flight in the horizontal-to-vertical conversion stage and the vertical landing stage is achieved by relying on the tail ducted power group (7). At this time, a loiter flight mission is completed.

10. A delivery working method of the separable distributed ducted aircraft as described in claims 3-8, characterized in that, The flight actions of the aircraft are achieved by the deflection of the ailerons (4) located at the trailing edge of the wing (3) and the deflection of the slipstream rudders (17) and the speed regulation of the propellers (15) of the ducted power devices of the wing ducted power group (6) and the tail ducted power group (7); meanwhile, the flight control and navigation of the aircraft are achieved by a central flight controller and sensors provided inside the fuselage (2); Among them, the central flight controller judges the current flight attitude and position as well as the target flight attitude and position based on the parameters obtained by the sensors, generates control instructions for the target attitude and position, controls the deflection of the aileron (4), and sends the control instructions to the flight controller in the duct power unit airborne equipment compartment (12), thereby controlling the deflection angle of the corresponding slipstream rudder (17) and the rotation speed of the propeller (15); Furthermore, the implemented aircraft delivery working method is as follows: In the vertical takeoff stage, the thrust generated by the wing duct power unit (6) and the tail duct power unit (7) is used to balance the gravity of the aircraft itself and complete vertical climb; In the vertical-horizontal conversion stage, the wing duct power unit (6) and the tail duct power unit (7) cooperate to control the generation of a control moment to complete the mode conversion; At the end of the vertical-horizontal conversion stage, the wing duct power unit (6) is separated from the wing (3), reducing the self-weight of the aircraft and improving the cruise efficiency of the aircraft; each duct power device in the separated wing duct power unit (6) forms a formation through the control of the flight controller and autonomously returns to land at the recovery site; When the aircraft flies to the predetermined delivery location, the front fuselage (1) is separated from the aircraft and descends to the predetermined location by means of a parachute, that is, the delivery of the front fuselage (1) is realized; at this time, the aircraft trims by adjusting the position of the wing (3) backward. A servo motor (21) is arranged in the fuselage (2) to drive the wing (3) to move backward along the variable pitch slide rail (20) arranged on the upper part of the fuselage (2) to realize the trimming of the aircraft; The aircraft then flies horizontally to the sky above the recovery site; The aircraft relies on the tail duct power unit (7) to realize the flight in the horizontal-vertical conversion stage and the vertical landing stage, completing a delivery flight mission.

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