High-speed single aircraft and combined unmanned aircraft

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a high-speed single aircraft and a combined unmanned aerial vehicle. The aircraft is composed of a front fuselage, supports, duct bodies, wings, ailerons, empennages, control surfaces, propellers, motors, flow deflectors and a rear fuselage. The front fuselage is connected to the duct body through the support, the wings are installed on the two sides of the duct body, ailerons are arranged on the wings, the motors are fixedly installed at the tail of the front fuselage, the propellers are installed on the motors, flow deflectors are arranged at the tail of the duct body, the rear fuselage is connected with the duct body through the flow deflectors, the tail of the rear fuselage is connected with the empennage, and four sets of control surfaces are installed on the empennage. High-speed and low-speed use requirements are considered, and multiple bodies can be combined.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a high-speed single-body aircraft and a combined unmanned aerial vehicle. Background Art

[0002] Both fixed-wing drones and rotary-wing drones can play an important role, but they also have obvious usage defects and are difficult to take into account in different usage scenarios. In the future, usage scenarios will be more complex and diversified, often requiring the combined application of multiple types of drones, which increases the difficulty of using drones and the burden of supporting them. It is necessary to design a combined aircraft with good mission versatility and environmental adaptability to meet the needs of different missions. Summary of the invention

[0003] In order to solve the problems in the background technology, the present invention provides a high-speed single-body aircraft and a combined unmanned aerial vehicle, which take into account the requirements of high-speed and low-speed use and can be combined in multiple bodies.

[0004] In order to achieve the above object, the present invention adopts the following technical solution to achieve it.

[0005] In a first aspect, the present invention provides a high-speed monohull aircraft, which is composed of a front fuselage 1, a bracket 2, a duct 3, a wing 4, an aileron 5, a tail 6, a control surface 7, a propeller 8, an electric motor 9, a guide vane 10, and a rear fuselage 11;

[0006] The front fuselage 1 is connected to the duct body 3 through a bracket 2, wings 4 are installed on both sides of the duct body 3, ailerons 5 are provided on the wings 4, the motor 9 is fixedly installed at the tail of the front fuselage 1, the propeller 8 is installed on the motor 9, a guide vane 10 is provided at the tail of the duct body 3, the rear fuselage 11 is connected to the duct body 3 through the guide vane 10, the tail of the rear fuselage 11 is connected to the tail wing 6, and four sets of rudder surfaces 7 are installed on the tail wing 6.

[0007] Furthermore,

[0008] There is no connection between the rear part of the front fuselage 1 and the front part of the rear fuselage 11; the interior of the front fuselage 1 and the rear fuselage 11 is used to arrange flight control, avionics, power supply and mission payload equipment;

[0009] The duct body 3 is an annular structure, and its cross section after unfolding is similar to an airfoil, and has a lip and a diffuser section;

[0010] The guide vane 10 adopts an airfoil profile;

[0011] The distance between the tip of the propeller 8 blade and the inner wall of the duct 3 is within 3% of the propeller radius.

[0012] Furthermore,

[0013] The high-speed single body aircraft has five flight modes, namely vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight and vertical landing.

[0014] Furthermore,

[0015] During vertical takeoff and vertical landing, the high-speed single-body aircraft uses propeller thrust to balance gravity. The propeller is driven by an electric motor. Adjusting the motor speed can change the propeller thrust to achieve vertical motion adjustment of the aircraft. Four sets of independently deflectable control surfaces 7 located on the tail wing 6 are in the wake of the propeller 8. The deflected control surfaces 7 generate control forces and torques relative to the center of gravity of the aircraft to achieve yaw, roll, and pitch control of the aircraft.

[0016] Furthermore,

[0017] In vertical takeoff and landing mode, the four sets of control surfaces deflect downward at the same time to generate an upward force, which produces a pitching moment relative to the center of gravity to lower the head; similarly, the four sets of control surfaces deflect upward at the same time to generate a downward force, which produces a pitching moment relative to the center of gravity to raise the head;

[0018] In vertical takeoff and landing mode, the four groups of control surfaces deflect to the left at the same time to generate a combined force to the right, and a rolling moment to the left relative to the center of gravity; similarly, the four groups of control surfaces deflect to the right at the same time to generate a combined force to the left, and a rolling moment to the right relative to the center of gravity;

[0019] In vertical takeoff and landing mode, the four sets of control surfaces deflect clockwise, generating counterclockwise lift on the tail wing and generating a right yaw moment relative to the center of gravity axis; similarly, the four sets of control surfaces deflect counterclockwise to generate a left yaw moment;

[0020] In vertical takeoff and landing mode, four sets of control surfaces are simultaneously involved in pitch, roll and yaw control;

[0021] In the vertical take-off and landing mode, the tail wing 6 is used as the landing gear of the aircraft.

[0022] Furthermore,

[0023] During horizontal flight, the high-speed single-body aircraft uses the lift of the wing 4 to balance gravity, and the thrust of the propeller 8 to balance the forward flight resistance. The propeller is driven by an electric motor. Adjusting the motor speed can change the propeller thrust to achieve acceleration and deceleration of the aircraft. The aileron 5 on the wing 4 provides a rolling control torque, and the four sets of control surfaces 7 on the tail 6 provide pitch and yaw control torques.

[0024] Furthermore,

[0025] In horizontal flight, the four groups of control surfaces deflect downward at the same time to produce an upward force, which produces a pitching moment relative to the center of gravity to lower the head; similarly, the four groups of control surfaces deflect upward at the same time to produce a downward force, which produces a pitching moment relative to the center of gravity to raise the head;

[0026] During horizontal flight, the four sets of control surfaces deflect to the left at the same time to produce a resultant force to the right, which generates a yaw moment to the left relative to the center of gravity; similarly, the four sets of control surfaces deflect to the right at the same time to produce a resultant force to the left, which generates a yaw moment to the right relative to the center of gravity.

[0027] Furthermore,

[0028] During vertical-horizontal conversion flight and horizontal-vertical conversion flight, the thrust of the propeller 8 and the lift of the wing 6 jointly balance the gravity, and the control surface 7 on the tail wing and the aileron 5 on the wing 4 jointly provide the control torque.

[0029] Furthermore,

[0030] During vertical-horizontal conversion flight, the aircraft first accelerates to climb vertically, and then manipulates the control surface 7 on the aircraft tail 6 to gradually turn the aircraft attitude angle from vertical to horizontal, and gradually transitions from the propeller 8 thrust balancing gravity to the lift on the wing 4 balancing gravity. The propeller 8 thrust is gradually used to balance the forward flight resistance of the aircraft, and the roll moment effect generated by the aileron 5 on the wing 4 gradually increases with the increase of the forward flight speed;

[0031] During horizontal-to-vertical transition flight, the aircraft first accelerates, and then the control surfaces 7 on the aircraft's tail 6 are manipulated to gradually turn the aircraft's attitude angle from horizontal to vertical, and the lift on the wing 4 gradually transitions to balancing gravity with the thrust of the propeller 8. The effectiveness of the rolling moment generated by the aileron 5 on the wing 4 gradually decreases as the forward flight speed decreases, and the control surfaces on the tail 6 gradually provide pitch, roll and yaw control moments.

[0032] In a second aspect, the present invention further provides a low-speed monohull aircraft, which is converted into a low-speed monohull aircraft by removing the wings 4 on both sides of the high-speed monohull aircraft described in the first aspect;

[0033] The low-speed single-body aircraft provides thrust through the propeller 8 in the duct body 3 to balance the gravity of the aircraft. The wake generated by the propeller 8 acts on the control surface 7 on the tail 6, and the deflection of the control surface 7 generates a control force and torque relative to the center of gravity of the aircraft, thereby realizing the pitch, roll and yaw control of the low-speed single-body aircraft, and realizing the forward and backward, left and right directions and turns of the aircraft.

[0034] Furthermore,

[0035] The four sets of control surfaces deflect downward at the same time to generate an upward force, which generates a pitching moment relative to the center of gravity to achieve the forward movement of the low-speed single-body aircraft. Similarly, the four sets of control surfaces deflect upward at the same time to generate a downward force, which generates a pitching moment relative to the center of gravity to achieve the backward movement of the low-speed single-body aircraft.

[0036] The four sets of control surfaces deflect clockwise, generating counterclockwise lift on the tail wing, producing a right yaw moment relative to the center of gravity axis, and enabling the low-speed single-body aircraft to turn right; similarly, the four sets of control surfaces deflect counterclockwise to generate a left yaw moment, and enabling the low-speed single-body aircraft to turn left.

[0037] In a third aspect, the present invention provides a combined unmanned aerial vehicle, which is implemented by the high-speed single-body aircraft described in the first aspect, and a quick connection device is provided on the wing tip of each high-speed single-body aircraft. The combined unmanned aerial vehicle is:

[0038] By connecting the wingtips of multiple high-speed single-body aircraft, they can be converted into a parallel multi-body combined unmanned aerial vehicle with wings of large aspect ratio.

[0039] In a fourth aspect, the present invention further provides a combined unmanned aerial vehicle, which is implemented by the high-speed single-body aircraft described in the first aspect, each high-speed single-body aircraft is provided with a quick connection device on the wing tip, and four joints are evenly arranged on the duct body 3, two of which are used to install the wing, and the combined unmanned aerial vehicle is:

[0040] Four high-speed single-body aircraft are combined into a rectangular hybrid multi-body combined aircraft, which are respectively recorded as aircraft one, aircraft two, aircraft three, and aircraft four in clockwise direction. The wing tips of aircraft one and aircraft two are connected to each other, the wing tips of aircraft three and aircraft four are connected to each other, the joints of aircraft two and aircraft three are connected to each other, and the joints of aircraft one and aircraft four are connected to each other. A payload cabin is installed in the middle space between the four high-speed single-body aircraft.

[0041] The high-speed single-body aircraft and combined aircraft provided by the present invention realize "one machine with multiple types" through modular means, which can take into account the use requirements of low speed / high speed, short range / long range, and can realize the complementary advantages between single machines through multi-body combination, forming an overall gain, and obtaining stronger convenience of use and deployment flexibility than existing UAV equipment. In addition, the modular design of the combined aircraft can also greatly reduce the production cost and realize the rapid iterative development of equipment family. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 A schematic diagram of the structure of a high-speed single body aircraft provided by an embodiment of the present invention;

[0043] Figure 2 A high-speed single body aircraft structure schematic diagram provided by an embodiment of the present invention Figure 2 ;

[0044] Figure 3 A schematic diagram of the structure of a low-speed single body aircraft provided by an embodiment of the present invention;

[0045] Figure 4 A schematic diagram of the structure of a parallel combined aircraft provided by an embodiment of the present invention;

[0046] Figure 5 A schematic diagram of the structure of a hybrid combined aircraft provided by an embodiment of the present invention;

[0047] Figure 6 A schematic diagram of an aircraft flight mode provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0048] The technical solution of the present invention is described in detail below in conjunction with the accompanying drawings.

[0049] The embodiment of the present invention provides a high-speed single body aircraft, such as Figure 1 and Figure 2 As shown, the aircraft is composed of a front fuselage 1, a bracket 2, a duct 3, a wing 4, an aileron 5, a tail wing 6, a control surface 7, a propeller 8, an electric motor 9, a guide vane 10, and a rear fuselage 11;

[0050] The front fuselage 1 is connected to the duct 3 through a bracket 2, the wings 4 are installed on both sides of the duct 3, the wings 4 are provided with ailerons 5, the motor 9 is fixedly installed at the tail of the front fuselage 1, the propeller 8 is installed on the motor 9, the tail of the duct 3 is provided with a guide vane 10, the rear fuselage 11 is connected to the duct 3 through the guide vane 10, the tail of the rear fuselage 11 is connected to the tail 6, and four sets of control surfaces 7 are installed on the tail 6. The front fuselage 1 and the rear fuselage 11 can be arranged inside the flight control, avionics, power supply and mission payload and other equipment.

[0051] It should be noted that there is no connection between the rear fuselage and the motor, or between the rear fuselage and the front fuselage.

[0052] The duct body 3 is an annular structure, and its cross-section after unfolding is similar to an airfoil, with a typical lip and diffuser section.

[0053] The guide vane 10 has an airfoil section.

[0054] The propeller 8 has a wider blade tip, and the distance between the blade tip and the inner wall of the duct body 3 is controlled within 3% of the propeller radius.

[0055] The high-speed single body aircraft has five flight modes, namely vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight and vertical landing.

[0056] During vertical takeoff and vertical landing, the high-speed single aircraft uses propeller thrust to balance gravity. The propeller is driven by a motor. Adjusting the motor speed can change the propeller thrust to achieve vertical motion adjustment of the aircraft. Four sets of independently deflectable control surfaces 7 located on the tail 6 are in the wake of the propeller 8. The deflecting control surfaces 7 generate control forces and torques relative to the center of gravity of the aircraft to achieve yaw, roll, and pitch control of the aircraft.

[0057] The rudder surfaces 7 include four groups of rudder surfaces, which are arranged clockwise as 7-1, 7-2, 7-3, and 7-4.

[0058] In the vertical takeoff and landing mode, the four sets of control surfaces deflected downward at the same time can generate an upward force, which can produce a pitching moment relative to the center of gravity to lower the head; similarly, the four sets of control surfaces deflected upward at the same time can generate a downward force, which can produce a pitching moment relative to the center of gravity to raise the head.

[0059] In the vertical takeoff and landing mode, the four sets of control surfaces deflecting to the left at the same time can generate a resultant force to the right, and the relative center of gravity can generate a rolling moment for rolling to the left; similarly, the four sets of control surfaces deflecting to the right at the same time can generate a resultant force to the left, and the relative center of gravity can generate a rolling moment for rolling to the right.

[0060] In the vertical take-off and landing mode, the four sets of control surfaces deflect clockwise, which can generate counterclockwise lift on the tail wing and a right yaw moment relative to the center of gravity axis; similarly, the four sets of control surfaces deflect counterclockwise to generate a left yaw moment.

[0061] In vertical take-off and landing mode, four sets of control surfaces are simultaneously involved in pitch, roll and yaw control.

[0062] In vertical take-off and landing mode, the tail wing 6 can be used as the landing gear of the aircraft.

[0063] In horizontal flight, the high-speed single aircraft uses the lift of the wing 4 to balance the gravity, and the thrust of the propeller 8 to balance the forward flight resistance. The propeller is driven by a motor. Adjusting the motor speed can change the propeller thrust to achieve acceleration and deceleration of the aircraft. The aileron 5 on the wing 4 provides a rolling control torque, and the four sets of control surfaces 7 on the tail 6 provide pitch and yaw control torques.

[0064] During horizontal flight, the four sets of control surfaces deflecting downward at the same time can produce a combined upward force, which can produce a pitching moment relative to the center of gravity to cause the aircraft to lower its head. Similarly, the four sets of control surfaces deflecting upward at the same time can produce a combined downward force, which can produce a pitching moment relative to the center of gravity to cause the aircraft to raise its head.

[0065] During horizontal flight, the four sets of control surfaces deflecting to the left at the same time can generate a resultant force to the right, which can generate a yaw moment to the left relative to the center of gravity; similarly, the four sets of control surfaces deflecting to the right at the same time can generate a resultant force to the left, which can generate a yaw moment to the right relative to the center of gravity.

[0066] During vertical-horizontal conversion flight and horizontal-vertical conversion flight, the thrust of the propeller 8 and the lift of the wing 6 jointly balance the gravity, and the control surface 7 on the tail wing and the aileron 5 on the wing 4 jointly provide the control torque.

[0067] During vertical-horizontal transition flight, the aircraft first performs vertical acceleration climb, and then manipulates the control surface 7 on the aircraft's tail wing 6 to gradually turn the aircraft's attitude angle from vertical to horizontal. The original balance of gravity by the thrust of the propeller 8 gradually transitions to the balance of gravity by the lift on the wing 4. The thrust of the propeller 8 is gradually used to balance the forward flight resistance of the aircraft, and the rolling moment effect generated by the aileron 5 on the wing 4 gradually increases with the increase of the forward flight speed.

[0068] During horizontal-vertical conversion flight, the aircraft first accelerates, and then the control surfaces 7 on the aircraft's tail 6 are manipulated to gradually turn the aircraft's attitude angle from horizontal to vertical. The lift on the wing 4 originally balances the gravity, and gradually transitions to the thrust of the propeller 8 balancing the gravity. The rolling moment generated by the aileron 5 on the wing 4 gradually decreases as the forward flight speed decreases, and the control surfaces on the tail 6 gradually provide pitch, roll and yaw control moments.

[0069] The embodiment of the present invention also provides a low-speed single-body aircraft, such as Figure 3 As shown, the high-speed single body aircraft is converted into a low-speed single body aircraft after removing the wings 4 on both sides.

[0070] The low-speed single-body aircraft provides thrust through the propeller 8 in the duct body 3 to balance the gravity of the aircraft. The wake generated by the propeller 8 acts on the control surface 7 on the tail 6. The deflected control surface 7 can generate control force and torque relative to the center of gravity of the aircraft, thereby realizing the pitch, roll and yaw control of the low-speed single-body aircraft, and realizing the forward and backward, left and right directions and turns of the aircraft.

[0071] The simultaneous downward deflection of the four sets of control surfaces can generate an upward resultant force, which can produce a pitching moment relative to the center of gravity to achieve forward movement of the low-speed single-body aircraft. Similarly, the simultaneous upward deflection of the four sets of control surfaces can generate a downward resultant force, which can produce a pitching moment relative to the center of gravity to achieve backward movement of the low-speed single-body aircraft.

[0072] When the four sets of control surfaces are deflected clockwise, counterclockwise lift can be generated on the tail wing, and a right yaw moment can be generated relative to the center of gravity axis, enabling the low-speed single-body aircraft to turn right; similarly, when the four sets of control surfaces are deflected counterclockwise, a left yaw moment can be generated, enabling the low-speed single-body aircraft to turn left.

[0073] The embodiment of the present invention also provides a parallel combined unmanned aerial vehicle, such as Figure 4As shown, the high-speed single-body aircraft is used to realize the above-mentioned, each high-speed single-body aircraft is provided with a quick connection device on the wing tip, and the combined unmanned aerial vehicle is:

[0074] By connecting the wingtips of multiple high-speed single-body aircraft, they can be converted into a parallel multi-body combined unmanned aerial vehicle with wings of large aspect ratio.

[0075] The embodiment of the present invention also provides a hybrid combined unmanned aerial vehicle, such as Figure 5 As shown, the high-speed single-body aircraft is used to realize the above-mentioned implementation. A quick connection device is provided on the wing tip of each high-speed single-body aircraft. Four joints are evenly arranged on the duct body 3, two of which are used to install the wing. The combined unmanned aerial vehicle is:

[0076] Four high-speed single-body aircraft are combined into a rectangular hybrid multi-body combined aircraft, which are respectively recorded as aircraft one, aircraft two, aircraft three, and aircraft four in clockwise direction. The wing tips of aircraft one and aircraft two are connected to each other, the wing tips of aircraft three and aircraft four are connected to each other, the joints of aircraft two and aircraft three are connected to each other, and the joints of aircraft one and aircraft four are connected to each other. A payload cabin is installed in the middle space between the four high-speed single-body aircraft.

[0077] The present invention proposes a combined unmanned aerial vehicle solution that takes into account both high-speed and low-speed use requirements and can be combined into multiple bodies. The combined aircraft includes a variety of configurations: high-speed single-body aircraft ( Figure 1 ), low-speed single-body aircraft ( Figure 3 ), parallel multi-body combined aircraft ( Figure 4 ), hybrid multi-body combined aircraft ( Figure 5 ).

[0078] High-speed single-body aircraft ( Figure 1 ) has the ability to take off and land vertically, hover, and fly forward at low speed, reducing its dependence on take-off and landing sites and equipment, and can perform high-speed, long-distance flight in horizontal flight.

[0079] High-speed single-body aircraft ( Figure 1 ) Remove the wings on both sides and convert it into a low-speed single-body aircraft ( Figure 3 The low-speed single-body aircraft has excellent vertical take-off and landing, hovering and low-speed flight capabilities, and its structure is more compact, safer to use, and can be quickly deployed and put into use.

[0080] By connecting the wing tips of multiple high-speed single-body aircraft, it can be converted into a parallel multi-body combined aircraft with a large aspect ratio wing ( Figure 4). The parallel multi-body combined aircraft increases the wing aspect ratio, which can effectively improve the cruise lift-to-drag ratio and endurance of the whole aircraft. The ailerons on the center wing of the parallel multi-body combined aircraft can be used as flaps during flight, which can increase the maximum lift coefficient of the aircraft and improve the low-speed flight capability of the aircraft. The parallel multi-body combined aircraft can realize a variety of functional combinations, clearly distinguish the functions undertaken by each single aircraft, and form a low-cost and highly coordinated mechanism. For example, combining dedicated energy supply aircraft, attack drones, and communication relay drones can not only ensure long-duration hovering missions, but also expand the use functions.

[0081] High-speed single-body aircraft can also be combined into 4 units to transform into a hybrid multi-body combined aircraft ( Figure 5 ), a load cabin is installed in the middle space between the aircraft to perform material transportation tasks. The hybrid multi-body combined aircraft has the ability to take off and land vertically and fly forward at high speed, and concentrates the load capacity of multiple bodies to improve the load capacity of the entire aircraft. The hybrid multi-body combined aircraft has 4 sets of propellers, and can also provide pitch, roll and yaw torques by differentially rotating the speed of the 4 sets of propellers to improve the control performance of the aircraft.

[0082] The quick connection device can be realized by a hinge-type connection structure.

[0083] The high-speed single body aircraft is mainly composed of a front fuselage 1, a bracket 2, a duct 3, a wing 4, an aileron 5, a tail wing 6, a control surface 7, a propeller 8, an electric motor 9, a guide vane 10, and a rear fuselage 11.

[0084] The high-speed single-body aircraft is powered by an electric motor 9, which directly drives the propeller 8 in the duct 3 to generate thrust. Eight guide vanes 10 are installed at the bottom outlet of the duct. The propeller 8 wake acts on the guide vanes with a certain installation angle, which can generate a torque to balance the anti-torque of the propeller. At the same time, the duct body 3 and the rear fuselage 11 are fixedly connected by the guide vanes.

[0085] The high-speed single-body aircraft has five flight modes: vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight, and vertical landing. Figure 6 shown.

[0086] During vertical takeoff and vertical landing, the high-speed single-body aircraft uses propeller thrust to balance gravity. Four sets of independently deflectable control surfaces 7 located on the tail wing 6 are in the wake of the propeller 8. The deflected control surfaces 7 can generate control forces and torques relative to the center of gravity of the aircraft to achieve yaw, roll, and pitch control of the aircraft.

[0087] During horizontal flight, the high-speed single-body aircraft uses the lift of the wings 4 to balance gravity, the thrust of the propeller 8 to balance the forward flight resistance, the ailerons 5 on the wings 4 provide rolling control torque, and the four sets of independently deflectable control surfaces 7 on the tail 6 provide pitch and yaw control torques.

[0088] During vertical-horizontal conversion flight and horizontal-vertical conversion flight, the thrust of the propeller 8 and the lift of the wing 6 jointly balance the gravity, and the control surface 7 on the tail wing and the aileron 5 on the wing 4 jointly provide the control torque.

[0089] A high-speed monocoque aircraft can be converted into a low-speed monocoque aircraft by removing the wings on both sides.

[0090] During vertical-horizontal transition flight, the aircraft first performs vertical acceleration climb, and then manipulates the control surface 7 on the aircraft's tail wing 6 to gradually turn the aircraft's attitude angle from vertical to horizontal. The original balance of gravity by the thrust of the propeller 8 gradually transitions to the balance of gravity by the lift on the wing 4. The thrust of the propeller 8 is gradually used to balance the forward flight resistance of the aircraft, and the rolling moment effect generated by the aileron 5 on the wing 4 gradually increases with the increase of the forward flight speed.

[0091] During horizontal-vertical conversion flight, the aircraft first accelerates, and then the control surfaces 7 on the aircraft's tail 6 are manipulated to gradually turn the aircraft's attitude angle from horizontal to vertical. The lift on the wing 4 originally balances the gravity, and gradually transitions to the thrust of the propeller 8 balancing the gravity. The rolling moment generated by the aileron 5 on the wing 4 gradually decreases as the forward flight speed decreases, and the control surfaces on the tail 6 gradually provide pitch, roll and yaw control moments.

[0092] By connecting the wingtips of multiple high-speed single-body aircraft, they can be converted into a parallel multi-body assembly with a large aspect ratio wing.

[0093] Four high-speed single-body aircraft are combined to transform into a hybrid multi-body combined aircraft, and a payload cabin is installed in the middle space between the aircraft.

[0094] Combined aircraft can realize "one machine with multiple types" through modular means, taking into account the use requirements of low speed / high speed, short range / long range, and can complement each other's advantages through multi-body combination, forming overall gain, and obtaining stronger convenience of use and deployment flexibility than existing UAV equipment. In addition, the modular design of combined aircraft can also greatly reduce production costs and realize the rapid iterative development of equipment family.

Claims

1. A high-speed single-body aircraft, characterized in that: The aircraft is composed of a front fuselage (1), a bracket (2), a duct (3), a wing (4), an aileron (5), a tail wing (6), a control surface (7), a propeller (8), an electric motor (9), a guide vane (10), and a rear fuselage (11); The front fuselage (1) is connected to the duct body (3) through a bracket (2), the wings (4) are installed on both sides of the duct body (3), the wings (4) are provided with ailerons (5), the motor (9) is fixedly installed at the tail of the front fuselage (1), the propeller (8) is installed on the motor (9), the tail of the duct body (3) is provided with a guide vane (10), the rear fuselage (11) is connected to the duct body (3) through the guide vane (10), the tail of the rear fuselage (11) is connected to the tail wing (6), and four groups of control surfaces (7) are installed on the tail wing (6).

2. A high-speed monohull aircraft according to claim 1, characterized in that: The interior of the front fuselage (1) and the rear fuselage (11) is used to arrange flight control, avionics, power supply and mission payload equipment; The duct body (3) is an annular structure, and its cross section after unfolding is similar to an airfoil, and has a lip and a diffuser section; The guide vane (10) adopts an airfoil profile; The distance between the tip of the propeller blade (8) and the inner wall of the duct body (3) is within 3% of the propeller radius.

3. A high-speed monohull aircraft according to claim 1, characterized in that: The high-speed single body aircraft has five flight modes, namely vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight and vertical landing.

4. A high-speed monohull aircraft according to claim 3, characterized in that: During vertical takeoff and vertical landing, the high-speed single-body aircraft uses propeller thrust to balance gravity. The propeller is driven by a motor. The propeller thrust can be changed by adjusting the motor speed to achieve vertical movement adjustment of the aircraft. Four sets of independently deflectable control surfaces (7) located on the tail wing (6) are in the wake of the propeller (8). The deflected control surfaces (7) generate control forces and torques relative to the center of gravity of the aircraft to achieve yaw, roll and pitch control of the aircraft.

5. A high-speed monohull aircraft according to claim 4, characterized in that: In vertical takeoff and landing mode, the four sets of control surfaces deflect downward at the same time to generate an upward force, which produces a pitching moment relative to the center of gravity to lower the head; similarly, the four sets of control surfaces deflect upward at the same time to generate a downward force, which produces a pitching moment relative to the center of gravity to raise the head; In vertical takeoff and landing mode, the four groups of control surfaces deflect to the left at the same time to generate a combined force to the right, and a rolling moment to the left relative to the center of gravity; similarly, the four groups of control surfaces deflect to the right at the same time to generate a combined force to the left, and a rolling moment to the right relative to the center of gravity; In vertical takeoff and landing mode, the four sets of control surfaces deflect clockwise, generating counterclockwise lift on the tail wing and generating a right yaw moment relative to the center of gravity axis; similarly, the four sets of control surfaces deflect counterclockwise to generate a left yaw moment; In vertical takeoff and landing mode, four sets of control surfaces are simultaneously involved in pitch, roll and yaw control; In the vertical take-off and landing mode, the tail wing (6) is used as the landing gear of the aircraft.

6. A high-speed monohull aircraft according to claim 4, characterized in that: During horizontal flight, the high-speed single-body aircraft uses the lift of the wing (4) to balance the gravity, and the thrust of the propeller (8) to balance the forward flight resistance. The propeller is driven by a motor, and the propeller thrust can be changed by adjusting the motor speed to achieve acceleration and deceleration of the aircraft. The aileron (5) on the wing (4) provides a rolling control torque, and the four groups of control surfaces (7) on the tail wing (6) provide pitch and yaw control torques.

7. A high-speed monohull aircraft according to claim 6, characterized in that: In horizontal flight, the four groups of control surfaces deflect downward at the same time to produce an upward force, which produces a pitching moment relative to the center of gravity to lower the head; similarly, the four groups of control surfaces deflect upward at the same time to produce a downward force, which produces a pitching moment relative to the center of gravity to raise the head; During horizontal flight, the four sets of control surfaces deflect to the left at the same time to produce a resultant force to the right, which generates a yaw moment to the left relative to the center of gravity; similarly, the four sets of control surfaces deflect to the right at the same time to produce a resultant force to the left, which generates a yaw moment to the right relative to the center of gravity.

8. A high-speed monohull aircraft according to claim 4, characterized in that: During vertical-horizontal conversion flight and horizontal-vertical conversion flight, the thrust of the propeller (8) and the lift of the wing (6) jointly balance the gravity, and the control surface (7) on the tail wing and the aileron (5) on the wing (4) jointly provide the control torque.

9. A high-speed monohull aircraft according to claim 8, characterized in that: During vertical-horizontal conversion flight, the aircraft first accelerates to climb vertically, and then manipulates the control surface (7) on the tail wing (6) of the aircraft to gradually turn the attitude angle of the aircraft from vertical to horizontal, and gradually transitions from balancing gravity with the thrust of the propeller (8) to balancing gravity with the lift on the wing (4). The thrust of the propeller (8) is gradually used to balance the forward flight resistance of the aircraft, and the rolling moment effect generated by the aileron (5) on the wing (4) gradually increases as the forward flight speed increases; During horizontal-vertical conversion flight, the aircraft is first accelerated, and then the control surface (7) on the tail wing (6) of the aircraft is manipulated to gradually turn the attitude angle of the aircraft from horizontal to vertical, and the lift on the wing (4) gradually transitions to the propeller (8) thrust balancing the gravity. The roll moment effect generated by the aileron (5) on the wing (4) gradually decreases as the forward flight speed decreases, and the control surface on the tail wing (6) gradually provides the pitch, roll and yaw control moments.

10. A low-speed single-body aircraft, characterized in that: A high-speed monohull aircraft according to any one of claims 1 to 9 is converted into a low-speed monohull aircraft after removing the wings (4) on both sides; The low-speed single-body aircraft provides thrust through a propeller (8) in a duct (3) to balance the gravity of the aircraft. The wake generated by the propeller (8) acts on a control surface (7) on a tail wing (6), and the deflection of the control surface (7) generates a control force and torque relative to the center of gravity of the aircraft, thereby achieving pitch, roll and yaw control of the low-speed single-body aircraft, and achieving the front and rear direction, left and right direction and turning of the aircraft.

11. A low-speed single-body aircraft according to claim 10, characterized in that: The four sets of control surfaces deflect downward at the same time to generate an upward force, which generates a pitching moment relative to the center of gravity to achieve the forward movement of the low-speed single-body aircraft. Similarly, the four sets of control surfaces deflect upward at the same time to generate a downward force, which generates a pitching moment relative to the center of gravity to achieve the backward movement of the low-speed single-body aircraft. The four sets of control surfaces deflect clockwise, generating counterclockwise lift on the tail wing, producing a right yaw moment relative to the center of gravity axis, and enabling the low-speed single-body aircraft to turn right; similarly, the four sets of control surfaces deflect counterclockwise to generate a left yaw moment, and enabling the low-speed single-body aircraft to turn left.

12. A combined unmanned aerial vehicle, characterized in that: The high-speed single-body aircraft according to any one of claims 1 to 9 is used, each high-speed single-body aircraft has a quick connection device on the wing tip, and the combined unmanned aerial vehicle is: By connecting the wingtips of multiple high-speed single-body aircraft, they can be converted into a parallel multi-body combined unmanned aerial vehicle with wings of large aspect ratio.

13. A combined unmanned aerial vehicle, characterized in that: The high-speed monobody aircraft according to any one of claims 1 to 9 is used for implementation, each high-speed monobody aircraft is provided with a quick connection device on the wing tip, four joints are evenly arranged on the duct body (3), two of which are used for installing the wing, and the combined unmanned aerial vehicle is: Four high-speed single-body aircraft are combined into a rectangular hybrid multi-body combined aircraft, which are respectively recorded as aircraft one, aircraft two, aircraft three, and aircraft four in clockwise direction. The wing tips of aircraft one and aircraft two are connected to each other, the wing tips of aircraft three and aircraft four are connected to each other, the joints of aircraft two and aircraft three are connected to each other, and the joints of aircraft one and aircraft four are connected to each other. A payload cabin is installed in the middle space between the four high-speed single-body aircraft.

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