A high-speed monoplane aircraft and a combined unmanned aircraft

Abstract

The application belongs to the technical field of unmanned aerial vehicles, and particularly relates to a high-speed single-body aircraft and a combined unmanned aerial vehicle. The aircraft is composed of a front fuselage, a support, a duct body, a wing, an aileron, a tail wing, a rudder surface, a propeller, an electric motor, a guide vane and a rear fuselage. The front fuselage is connected to the duct body through the support, the wing is installed on both sides of the duct body, the wing is provided with the aileron, the electric motor is fixedly installed at the tail of the front fuselage, the propeller is installed on the electric motor, the tail of the duct body is provided with the guide vane, the rear fuselage is connected to the duct body through the guide vane, the tail of the rear fuselage is connected to the tail wing, four groups of rudder surfaces are installed on the tail wing, the high-speed and low-speed use requirements are considered, and the aircraft can be combined in multiple bodies.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of unmanned aerial vehicles, and particularly relates to a high-speed single-body aircraft and a combined unmanned aerial vehicle. BACKGROUND

[0002] Both fixed-wing unmanned aerial vehicles and rotary-wing unmanned aerial vehicles can play an important role, but also have obvious use defects, and it is difficult to take into account different use scenarios. Future use scenarios present complex and diversified characteristics, and often require combined application of multiple types of unmanned aerial vehicles, increasing the use difficulty and support burden of the unmanned aerial vehicles, and a combined aircraft with good task versatility and environmental adaptability needs to be designed to meet different task use requirements. SUMMARY

[0003] To solve the problems in the background art, the application provides a high-speed single-body aircraft and a combined unmanned aerial vehicle, which takes into account high-speed and low-speed use requirements and can be combined in multiple bodies.

[0004] To achieve the above-mentioned purpose, the application adopts the following technical solutions.

[0005] In a first aspect, the application provides a high-speed single-body aircraft, which is composed of a front fuselage 1, a support 2, a duct body 3, a wing 4, an aileron 5, a tail fin 6, a rudder surface 7, a propeller 8, an electric motor 9, a guide vane 10, and an aft fuselage 11.

[0006] The front fuselage 1 is connected to the duct body 3 through the support 2, the wing 4 is installed on both sides of the duct body 3, the wing 4 is provided with the aileron 5, the electric motor 9 is fixedly installed at the tail of the front fuselage 1, the propeller 8 is installed on the electric motor 9, the duct body 3 is provided with the guide vane 10 at the tail, the aft fuselage 11 is connected to the duct body 3 through the guide vane 10, the aft fuselage 11 is connected to the tail fin 6 at the tail, and four groups of rudder surfaces 7 are installed on the tail fin 6.

[0007] Further,

[0008] The front fuselage 1 is not connected to the front part of the aft fuselage 11, and the interiors of the front fuselage 1 and the aft fuselage 11 are used to arrange flight control, avionics, power supply, and task load equipment.

[0009] The duct body 3 has a ring structure, and the unfolded cross section is similar to an airfoil, has a lip and a diffusion section.

[0010] The guide vane 10 adopts an airfoil cross section.

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

[0012] Further,

[0013] The high-speed monomer aircraft has five flight modes, i.e. vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight and vertical landing.

[0014] Further,

[0015] In the vertical take-off and vertical landing, the high-speed monomer aircraft balances the gravity by the propeller thrust, the propeller is driven by the motor, the propeller thrust can be changed by adjusting the motor speed, the vertical movement of the aircraft is adjusted, four groups of independently deflectable rudders 7 on the tail 6 are in the propeller 8 tail flow, the deflected rudders 7 generate control force and moment relative to the center of gravity of the aircraft to realize the yaw, roll and pitch control of the aircraft.

[0016] Further,

[0017] In the vertical take-off and landing mode, four groups of rudders are deflected downward at the same time to generate upward combined force, which generates a low head pitch moment relative to the center of gravity; similarly, four groups of rudders are deflected upward at the same time to generate downward combined force, which generates a high head pitch moment relative to the center of gravity.

[0018] In the vertical take-off and landing mode, four groups of rudders are deflected to the left at the same time to generate right combined force, which generates a left roll roll moment relative to the center of gravity; similarly, four groups of rudders are deflected to the right at the same time to generate left combined force, which generates a right roll roll moment relative to the center of gravity.

[0019] In the vertical take-off and landing mode, four groups of rudders are deflected clockwise, which generates counterclockwise lift on the tail, and generates a right yaw moment relative to the center of gravity axis; similarly, four groups of rudders are deflected counterclockwise to generate a left yaw moment.

[0020] In the vertical take-off and landing mode, four groups of rudders participate in pitch, roll and yaw control at the same time.

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

[0022] Further,

[0023] In horizontal flight, the high-speed monomer aircraft balances the gravity by the wing 4 lift, and balances the forward flight resistance by the propeller 8 thrust, the propeller is driven by the motor, the propeller thrust can be changed by adjusting the motor speed, the aircraft acceleration and deceleration are realized, the aileron 5 on the wing 4 provides roll control moment, and the four groups of rudders 7 on the tail 6 provide pitch and yaw control moments.

[0024] Further,

[0025] In horizontal flight, four groups of rudders are deflected downward at the same time to generate upward combined force, which generates a low head pitch moment relative to the center of gravity; similarly, four groups of rudders are deflected upward at the same time to generate downward combined force, which generates a high head pitch moment relative to the center of gravity.

[0026] In horizontal flight, four sets of rudders deflect to the left simultaneously to generate a resultant force to the right, which generates a yawing moment to the left relative to the center of gravity; similarly, four sets of rudders deflect to the right simultaneously to generate a resultant force to the left, which generates a yawing moment to the right relative to the center of gravity.

[0027] Further,

[0028] In vertical-horizontal conversion flight and horizontal-vertical conversion flight, the propeller 8 thrust and the wing 6 lift together balance the gravity, and the rudder 7 on the tail and the aileron 5 on the wing 4 together provide the control moment.

[0029] Further,

[0030] In vertical-horizontal conversion flight, the aircraft first performs vertical acceleration climb, and then manipulates the rudder 7 on the tail 6 of the aircraft to gradually turn the attitude angle of the aircraft from vertical to horizontal, gradually transition from the gravity balance by the propeller 8 thrust to the gravity balance by the lift on the wing 4, and gradually use the propeller 8 thrust to balance the forward flight resistance of the aircraft, and gradually increase the rolling moment effect of the aileron 5 on the wing 4 as the forward flight speed increases;

[0031] In horizontal-vertical conversion flight, the aircraft first accelerates, and then manipulates the rudder 7 on the tail 6 of the aircraft to gradually turn the attitude angle of the aircraft from horizontal to vertical, gradually transition from the gravity balance by the lift on the wing 4 to the gravity balance by the propeller 8 thrust, and gradually reduce the rolling moment effect of the aileron 5 on the wing 4 as the forward flight speed decreases, and gradually provide the pitch, roll and yaw control moments by the rudder on the tail 6.

[0032] In the second aspect, the application also provides a low-speed single aircraft, which is converted into a low-speed single aircraft by removing the wings 4 on both sides of the high-speed single aircraft of the first aspect;

[0033] The low-speed single aircraft balances the gravity of the aircraft by the propeller 8 in the duct body 3 providing thrust, and the wake generated by the propeller 8 acts on the rudder 7 on the tail 6, and deflecting the rudder 7 generates control force and moment relative to the center of gravity of the aircraft, realizing the pitch, roll and yaw control of the low-speed single aircraft, and realizing the forward and backward, left and right directions and turning of the aircraft.

[0034] Further,

[0035] Four sets of rudders deflect downward simultaneously to generate an upward resultant force, which generates a pitching moment to lower the head relative to the center of gravity, realizing the forward movement of the low-speed single aircraft; similarly, four sets of rudders deflect upward simultaneously to generate a downward resultant force, which generates a pitching moment to raise the head relative to the center of gravity, realizing the backward movement of the low-speed single aircraft;

[0036] The four groups of rudders are deflected clockwise, the lift of the tail wings is counterclockwise, a right yawing moment is generated relative to the gravity center axis, and the low-speed single-body aircraft is turned right; similarly, the four groups of rudders are deflected counterclockwise to generate a left yawing moment, and the low-speed single-body aircraft is turned left.

[0037] In a third aspect, the application provides a combined unmanned aerial vehicle, which is realized by the high-speed single-body aircraft in the first aspect, and a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, and the combined unmanned aerial vehicle is:

[0038] The wing tips of multiple high-speed single-body aircrafts are connected, and the parallel multi-body combined unmanned aerial vehicle with a large aspect ratio wing can be converted.

[0039] In a fourth aspect, the application also provides a combined unmanned aerial vehicle, which is realized by the high-speed single-body aircraft in the first aspect, and a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, and four joints are uniformly arranged on the duct body 3, two of which are used to install the wings, and the combined unmanned aerial vehicle is:

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

[0041] The high-speed single-body aircraft and the combined aerial vehicle provided by the application realize "one machine with multiple types" through modularization, can meet the use requirements of low speed / high speed and short range / long range, and can realize the complementary advantages between single machines through the multi-body combination mode, form overall gain, and obtain stronger use convenience and deployment flexibility than the existing unmanned aerial vehicle equipment. In addition, the modular design of the combined aerial vehicle can greatly reduce the production cost and realize the rapid iterative development of the equipment family. BRIEF DESCRIPTION OF DRAWINGS

[0042] Figure 1 A high-speed single-body aircraft structure schematic diagram provided for an embodiment of the application;

[0043] Figure 2 A high-speed single-body aircraft structure schematic diagram provided for an embodiment of the application Figure Two ;

[0044] Figure 3 A low-speed single-body aircraft structure schematic diagram provided for an embodiment of the application;

[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 with reference to 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, wings 4, ailerons 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 forward fuselage 1 is connected to the duct 3 via a bracket 2. Wings 4 are mounted on either side of the duct 3, each equipped with ailerons 5. An electric motor 9 is fixed to the rear of the forward fuselage 1, and a propeller 8 is mounted on the motor 9. A deflector 10 is installed at the rear of the duct 3. The rear fuselage 11 is connected to the duct 3 via the deflector 10. The rear of the rear fuselage 11 is connected to the empennage 6, which is equipped with four sets of control surfaces 7. The interiors of the forward and rear fuselages 1 and 11 accommodate flight control, avionics, power supplies, and payload 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 cross-section.

[0054] The propeller 8 has a wider blade tip, and the distance between the blade tip and the inner wall of the duct 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] In vertical take-off and landing mode, the high-speed monomer aircraft balances gravity with propeller thrust, the propeller is driven by motor, adjusting the motor speed can change the propeller thrust, to realize the vertical motion adjustment of the aircraft. Four groups of independently deflectable rudders 7 on the tail 6 are in the propeller 8 wake, deflecting the rudders 7 generates control force and moment relative to the center of gravity of the aircraft to realize the yaw, roll, pitch control of the aircraft.

[0057] The rudders 7 include four groups of rudders, arranged in clockwise order as 7-1, 7-2, 7-3 and 7-4.

[0058] In vertical take-off and landing mode, four groups of rudders deflect downward at the same time to generate upward combined force, relative to the center of gravity to generate a low head pitch moment; similarly, four groups of rudders deflect upward at the same time to generate downward combined force, relative to the center of gravity to generate a head-up pitch moment.

[0059] In vertical take-off and landing mode, four groups of rudders deflect left at the same time to generate right combined force, relative to the center of gravity to generate a left roll roll moment; similarly, four groups of rudders deflect right at the same time to generate left combined force, relative to the center of gravity to generate a right roll roll moment.

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

[0061] In vertical take-off and landing mode, four groups of rudders participate in pitch, roll and yaw control at the same time.

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

[0063] In horizontal flight, the high-speed monomer aircraft balances gravity with wing 4 lift, propeller 8 thrust balances forward flight resistance, the propeller is driven by motor, adjusting the motor speed can change the propeller thrust, to realize the acceleration and deceleration of the aircraft. The aileron 5 on the wing 4 provides roll control moment, and the four groups of rudders 7 on the tail 6 provide pitch and yaw control moments.

[0064] In horizontal flight, four groups of rudders deflect downward at the same time to generate upward combined force, relative to the center of gravity to generate a low head pitch moment; similarly, four groups of rudders deflect upward at the same time to generate downward combined force, relative to the center of gravity to generate a head-up pitch moment.

[0065] In horizontal flight, four groups of rudders deflect left at the same time to generate right combined force, relative to the center of gravity to generate a left yaw yaw moment; similarly, four groups of rudders deflect right at the same time to generate left combined force, relative to the center of gravity to generate a right yaw yaw moment.

[0066] In vertical-horizontal conversion flight, the propeller 8 thrust and the wing 6 lift balance the gravity, and the rudder surface 7 on the tail 6 and the aileron 5 on the wing 4 provide the control moment together.

[0067] In vertical-horizontal conversion flight, the aircraft first vertically accelerates and climbs, and then the rudder surface 7 on the tail 6 is controlled to gradually change the aircraft attitude angle from vertical to horizontal. The gravity is originally balanced by the propeller 8 thrust, and gradually transitions to be balanced by the lift on the wing 4. The propeller 8 thrust is gradually used to balance the forward flight resistance of the aircraft, and the roll moment effect of the aileron 5 on the wing 4 gradually increases with the increase of the forward flight speed.

[0068] In horizontal-vertical conversion flight, the aircraft first accelerates, and then the rudder surface 7 on the tail 6 is controlled to gradually change the aircraft attitude angle from horizontal to vertical. The gravity is originally balanced by the lift on the wing 4, and gradually transitions to be balanced by the propeller 8 thrust. The roll moment effect of the aileron 5 on the wing 4 gradually decreases with the decrease of the forward flight speed, and the pitch, roll and yaw control moments are gradually provided by the rudder surface on the tail 6.

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

[0070] The low-speed single aircraft balances the gravity of the aircraft by the propeller 8 in the duct 3. The wake generated by the propeller 8 acts on the rudder surface 7 on the tail 6. The deflection of the rudder surface 7 can generate control force and moment relative to the center of gravity of the aircraft, so as to realize the pitch, roll and yaw control of the low-speed single aircraft, and realize the forward and backward movement, left and right movement and turning of the aircraft.

[0071] The four groups of rudder surfaces are deflected downward at the same time to generate upward resultant force, and relative to the center of gravity to generate pitch moment of lowering head, so as to realize the forward movement of the low-speed single aircraft. Similarly, the four groups of rudder surfaces are deflected upward at the same time to generate downward resultant force, and relative to the center of gravity to generate pitch moment of raising head, so as to realize the backward movement of the low-speed single aircraft.

[0072] The four groups of rudder surfaces are deflected clockwise at the same time to generate counterclockwise lift on the tail, and relative to the center of gravity axis to generate right yaw moment, so as to realize the right turning of the low-speed single aircraft. Similarly, the four groups of rudder surfaces are deflected counterclockwise at the same time to generate left yaw moment, so as to realize the left turning of the low-speed single aircraft.

[0073] The embodiment of the present application also provides a parallel combined unmanned aircraft, such as Figure 4As shown, the high-speed single-body aircraft is used to realize that a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, the combined unmanned aircraft is:

[0074] The wing tips of multiple high-speed single-body aircrafts are connected to convert into a parallel multi-body combined unmanned aircraft with a large aspect ratio wing.

[0075] The embodiment of the application also provides a hybrid combined unmanned aircraft, as shown in Figure 5 As shown, the high-speed single-body aircraft is used to realize that a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, the combined unmanned aircraft is:

[0076] Four high-speed single-body aircrafts are combined into a hybrid multi-body combined aircraft with a rectangular structure, and are sequentially clockwise recorded as aircraft one, aircraft two, aircraft three and aircraft four, the wing tips of the aircraft one and the aircraft two are connected to each other, the wing tips of the aircraft three and the aircraft four are connected to each other, the joints of the aircraft two and the aircraft three are connected to each other, the joints of the aircraft one and the aircraft four are connected to each other, and a load cabin is arranged in the middle space between the four high-speed single-body aircrafts.

[0077] The application provides a combined unmanned aircraft scheme which can meet the use requirements of high speed and low speed and can be combined into a multi-body. Figure 1 The combined aircraft includes multiple configurations: a high-speed single-body aircraft ( Figure 3 ), a low-speed single-body aircraft ( Figure 4 ), a parallel multi-body combined aircraft ( Figure 5 ) and a hybrid multi-body combined aircraft.

[0078] The high-speed single-body aircraft ( Figure 1 ) has the vertical take-off, hovering and low-speed forward flight capability, reduces the dependence on the take-off site and take-off equipment, and can perform high-speed and long-distance flight in a horizontal flight mode.

[0079] The high-speed single-body aircraft ( Figure 1 ) can be converted into a low-speed single-body aircraft ( Figure 3 ) by removing the wings on both sides. The low-speed single-body aircraft has excellent vertical take-off, hovering and low-speed flight capability, and has a more compact structure and is safer to use, and can be quickly deployed and put into use.

[0080] The wing tips of multiple high-speed single-body aircrafts are connected to convert into a parallel multi-body combined aircraft with a large aspect ratio wing. Figure 4Parallel multi-body combined aircraft increases the wing aspect ratio, which can effectively improve the cruise lift-drag ratio and endurance of the whole machine. The aileron on the center wing of the parallel multi-body combined aircraft can be used as a flap during flight, which can improve the maximum lift coefficient of the aircraft and improve the low-speed flight capability of the aircraft. Parallel multi-body combined aircraft can realize multiple function combinations, clearly distinguish the functions of each single aircraft, and form a highly collaborative mechanism with low cost. For example, combining dedicated energy supply aircraft, attack unmanned aerial vehicles, and communication relay unmanned aerial vehicles together can not only ensure long endurance and air tasks, but also expand the use functions.

[0081] High-speed single-body aircraft can also be combined into a 4-machine combination to convert into a hybrid multi-body combined aircraft Figure 5 ), which installs a load cabin in the middle space between the aircraft for performing material transportation tasks. Hybrid multi-body combined aircraft has vertical take-off and high-speed forward flight capability, and concentrates the load capacity of the multi-body to improve the load capacity of the whole machine. Hybrid multi-body combined aircraft has 4 propellers, and can also provide pitch, roll, and yaw moments by differentiating the rotation speed of the 4 propellers to improve the control performance of the aircraft.

[0082] The quick connection device can be achieved through a hinged connection structure.

[0083] The high-speed single-body aircraft is mainly composed of a front fuselage 1, a support 2, a duct body 3, a wing 4, an aileron 5, a tail 6, a rudder 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 one electric motor 9, which directly drives the propeller 8 in the duct 3 to generate thrust. Eight guide vanes 10 are installed at the outlet of the bottom of the duct, and the propeller 8 tail flow acts on the guide vanes with a certain installation angle to generate a moment that balances the counter-torque of the propeller. At the same time, the duct body 3 and the rear fuselage 11 are fixedly connected through 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, as shown in Figure 6 .

[0086] During vertical take-off and vertical landing, the high-speed single-body aircraft balances gravity with propeller thrust, and four independently deflectable rudder surfaces 7 are located in the propeller 8 tail flow on the tail 6. Deflecting the rudder surface 7 can generate control force and moment relative to the center of gravity of the aircraft to achieve aircraft yaw, roll, and pitch control.

[0087] In horizontal flight, the high-speed monomer aircraft is balanced by the wing 4 lift force to balance the gravity, the propeller 8 thrust to balance the forward flight resistance, the aileron 5 on the wing 4 provides roll control moment, and the four groups of independently deflectable rudders 7 on the tail 6 provide pitch and yaw control moments.

[0088] In vertical-horizontal conversion flight and horizontal-vertical conversion flight, the propeller 8 thrust and the wing 6 lift force jointly balance the gravity, and the rudders 7 on the tail and the aileron 5 on the wing 4 jointly provide control moments.

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

[0090] In vertical-horizontal conversion flight, the aircraft first performs vertical acceleration climb, and then the rudders 7 on the tail 6 of the aircraft are manipulated to gradually change the attitude angle of the aircraft from vertical to horizontal. The gravity is originally balanced by the propeller 8 thrust, and gradually transitions to being balanced by the lift on the wing 4. 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 as the forward flight speed increases.

[0091] In horizontal-vertical conversion flight, the aircraft first accelerates, and then the rudders 7 on the tail 6 of the aircraft are manipulated to gradually change the attitude angle of the aircraft from horizontal to vertical. The gravity is originally balanced by the lift on the wing 4, and gradually transitions to being balanced by the propeller 8 thrust. The roll moment effect generated by the aileron 5 on the wing 4 gradually decreases as the forward flight speed decreases, and gradually provides pitch, roll, and yaw control moments by the rudders on the tail 6.

[0092] The wing tips of multiple high-speed monomer aircrafts are connected to convert into a parallel multi-body combined type with a large aspect ratio wing.

[0093] Four high-speed monomer aircrafts are combined to convert into a hybrid multi-body combined type aircraft, and a load cabin is installed in the middle space between the aircrafts.

[0094] The combined aircraft realizes "one machine with multiple types" through modularization, can meet the use requirements of low speed / high speed and short range / long range, and through multi-body combination, the advantages of single machines can be complementary to form overall gain, and stronger use convenience and deployment flexibility than existing unmanned aerial vehicle equipment can be obtained. In addition, the modular design of the combined aircraft can greatly reduce production costs and realize rapid iterative development of equipment families.

Claims

1. A high-speed monomeric aircraft characterized by, The aircraft is composed of a front fuselage (1), a support (2), a duct body (3), a wing (4), an aileron (5), a tail (6), a rudder (7), a propeller (8), an electric motor (9), a guide vane (10), a rear fuselage (11); The front fuselage (1) is connected to the duct body (3) through the support (2), the wing (4) is installed on both sides of the duct body (3), the wing (4) is provided with the aileron (5), the electric motor (9) is fixedly installed at the tail of the front fuselage (1), the propeller (8) is installed on the electric motor (9), the duct body (3) is provided with the guide vane (10) at the tail, the rear fuselage (11) is connected to the duct body (3) through the guide vane (10), the tail (6) is connected to the tail of the rear fuselage (11), and four groups of rudders (7) are installed on the tail (6); The interiors of the front fuselage (1) and the rear fuselage (11) are used for arranging flight control, avionics, power supply and mission load equipment; The duct body (3) has a ring structure, and the unfolded cross section is similar to an airfoil, and has a lip and a diffusion section; The guide vane (10) has an airfoil cross section; The distance between the blade tip of the propeller (8) and the inner wall of the duct body (3) is within 3% of the propeller radius; The high-speed single-body aircraft has five flight modes, i.e. vertical take-off, vertical-horizontal conversion flight, horizontal flight, horizontal-vertical conversion flight and vertical landing; In the vertical take-off and vertical landing mode, the high-speed single-body aircraft balances the gravity by the propeller thrust, the propeller is driven by the electric motor, the propeller thrust can be changed by adjusting the rotating speed of the electric motor, the vertical movement of the aircraft is adjusted, the four groups of independently deflectable rudders (7) located on the tail (6) are in the wake of the propeller (8), the deflected rudders (7) generate a control force and a moment relative to the center of gravity of the aircraft to realize the yaw, roll and pitch control of the aircraft; In the vertical take-off and landing mode, the four groups of rudders are deflected downward to generate an upward resultant force, and a pitch moment relative to the center of gravity is generated to lower the head; similarly, the four groups of rudders are deflected upward to generate a downward resultant force, and a pitch moment relative to the center of gravity is generated to raise the head; In the vertical take-off and landing mode, the four groups of rudders are deflected to the left to generate a rightward resultant force, and a roll moment relative to the center of gravity is generated to roll to the left; similarly, the four groups of rudders are deflected to the right to generate a leftward resultant force, and a roll moment relative to the center of gravity is generated to roll to the right; In the vertical take-off and landing mode, the four groups of rudders are deflected clockwise, the tail generates a counterclockwise lift, and a right yaw moment relative to the center of gravity axis is generated; similarly, the four groups of rudders are deflected counterclockwise to generate a left yaw moment; In the vertical take-off and landing mode, the four groups of rudders participate in the pitch, roll and yaw control simultaneously. In the vertical take-off and landing mode, the tail (6) is used as the landing gear of the aircraft.

2. The high-speed single-body aircraft according to claim 1, characterized in that In horizontal flight, the high-speed monomer aircraft is balanced by the wing (4) lift to balance the gravity, the propeller (8) thrust to balance the forward resistance, the propeller is driven by the motor, adjusting the motor speed can change the propeller thrust, realize the aircraft acceleration and deceleration, the aileron (5) on the wing (4) provides the roll control moment, the four groups of rudders (7) on the tail (6) provide the pitch and yaw control moment.

3. The high-speed monomer aircraft according to claim 2, wherein, In horizontal flight, the four groups of rudders are deflected downward simultaneously to generate upward combined force, which generates the pitch moment of lowering head relative to the center of gravity; Similarly, the four groups of rudders are deflected upward simultaneously to generate downward combined force, which generates the pitch moment of lifting head relative to the center of gravity. In horizontal flight, the four groups of rudders are deflected leftward simultaneously to generate rightward combined force, which generates the yaw moment of leftward yaw relative to the center of gravity; Similarly, the four groups of rudders are deflected rightward simultaneously to generate leftward combined force, which generates the yaw moment of rightward yaw relative to the center of gravity.

4. The high-speed monomer aircraft according to claim 1, wherein, In vertical-horizontal conversion flight and horizontal-vertical conversion flight, the propeller (8) thrust and the wing (4) lift balance the gravity, the rudders (7) on the tail and the aileron (5) on the wing (4) provide the control moment together.

5. The high-speed monomer aircraft according to claim 4, wherein, In vertical-horizontal conversion flight, the aircraft first performs vertical acceleration climbing, and then controls the rudders (7) on the tail (6) to gradually change the aircraft attitude angle from vertical to horizontal, gradually transitions from the gravity balance by the propeller (8) thrust to the gravity balance by the wing (4) lift, gradually uses the propeller (8) thrust to balance the forward resistance of the aircraft, and gradually increases the roll moment effect generated by the aileron (5) on the wing (4) as the forward flight speed increases. In horizontal-vertical conversion flight, the aircraft first accelerates, and then controls the rudders (7) on the tail (6) to gradually change the aircraft attitude angle from horizontal to vertical, gradually transitions from the gravity balance by the wing (4) lift to the gravity balance by the propeller (8) thrust, gradually reduces the roll moment effect generated by the aileron (5) on the wing (4) as the forward flight speed decreases, and gradually provides the pitch, roll and yaw control moment by the rudders on the tail (6).

6. A low speed monoplane aircraft characterized by, The high-speed monomer aircraft according to any one of claims 1-5 is converted into a low-speed monomer aircraft by removing the wings (4) on both sides; The low-speed monomer aircraft balances the gravity by the propeller (8) in the duct (3), the propeller (8) generates the wake acting on the rudders (7) on the tail (6), and the deflected rudders (7) generate the control force and moment relative to the center of gravity of the aircraft, realizing the pitch, roll and yaw control of the low-speed monomer aircraft, and realizing the forward and backward directions, left and right directions and turning of the aircraft.

7. The low-speed monomer aircraft according to claim 6, wherein, Four groups of rudders deflect downward simultaneously to generate upward resultant force, which generates low head pitch moment relative to the center of gravity, to realize forward movement of the low-speed single-body aircraft; similarly, four groups of rudders deflect upward simultaneously to generate downward resultant force, which generates high head pitch moment relative to the center of gravity, to realize backward movement of the low-speed single-body aircraft. Four groups of rudders deflect clockwise to generate counterclockwise lift on the tail, which generates right yaw moment relative to the center of gravity axis, to realize right turning of the low-speed single-body aircraft; similarly, four groups of rudders deflect counterclockwise to generate left yaw moment, to realize left turning of the low-speed single-body aircraft.

8. A combined unmanned aerial vehicle, characterized by, The high-speed single-body aircraft is realized by using any one of claims 1-5, and a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, and the combined unmanned aircraft is: The wing tips of multiple high-speed single-body aircrafts are connected to be converted into a parallel multi-body combined unmanned aircraft with a large aspect ratio wing.

9. A combined unmanned aerial vehicle, characterized by, The high-speed single-body aircraft is realized by using any one of claims 1-5, and a quick connecting device is arranged on the wing tip of each high-speed single-body aircraft, and the combined unmanned aircraft is: Four high-speed single-body aircrafts are combined into a rectangular structure of a hybrid multi-body combined aircraft, which are clockwise denoted as aircraft one, aircraft two, aircraft three, and aircraft four, the wing tips of the aircraft one and the aircraft two are connected to each other, the wing tips of the aircraft three and the aircraft four are connected to each other, the joints of the aircraft two and the aircraft three are connected to each other, the joints of the aircraft one and the aircraft four are connected to each other, and a load cabin is installed in the middle space between the four high-speed single-body aircrafts.

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