Multi-electric vertical take-off and landing high-speed green aircraft

Abstract

The invention provides a multi-electric vertical take-off and landing high-speed green aircraft which comprises an aircraft body of a triangular wing-body integrated structure. The mounting groove plate frame is provided with a plurality of mounting grooves and is connected with the fuselage through a plurality of combination points; the engine comprises a horizontal engine for providing horizontal thrust and a vertical engine for providing vertical thrust, or the engine comprises a rotatable rotary engine, and the rotatable rotary engine can realize horizontal and vertical conversion; and the rotary engine, the horizontal engine and the vertical engine are respectively arranged in the mounting grooves and are connected with the fuselage through a plurality of nodes. The multi-point multi-electric engine is arranged, the vertical and horizontal rotation configuration scheme is achieved, the design flexibility of the aircraft is improved, vertical take-off and landing are achieved through the vertical engine, horizontal thrust is provided through the horizontal engine, the vertical take-off and landing and high-speed flight functions are achieved, meanwhile, a more efficient electric drive and distribution system is adopted, and the system is more efficient. The aircraft weight is reduced, the fuel efficiency is improved, and the maintenance cost is reduced.

Description

Technical Field

[0001] The present application relates to the field of intelligent aviation technology, and in particular to a multi-electric vertical take-off and landing high-speed green aircraft. Background Art

[0002] First, existing airplanes and helicopters have their own shortcomings. Ordinary airplanes cannot take off and land vertically, although they can fly at supersonic speeds; helicopters can take off and land vertically, but they cannot fly fast; drones have a small load capacity and cannot fly fast or far. The new aircraft proposed in this patent is a small and medium-sized passenger and cargo dual-purpose aircraft that can take off and land vertically in a small area without requiring a large take-off space, and can fly horizontally quickly (>600kmh) after take-off.

[0003] Then there is green movement. Green movement refers to green energy drive. Green transportation is to use new energy to provide power energy for the engine. Taking China as an example, the main sources of new energy are wind, solar and water, that is, wind power generation, hydropower generation and photovoltaic power generation. The electricity generated is transmitted from west to east, and then high-energy batteries (such as lithium batteries) are used as the carrier of these new energy electricity to provide green aviation kinetic energy for new energy aircraft. This is the meaning of green movement.

[0004] The next part is about our aircraft design. The green aircraft powered by green energy is a delta-wing aircraft structure, also known as a wing-body aircraft. The concept of wing-body integration has been proposed and applied for a long time. It has many advantages, such as large capacity, high lift-to-drag ratio, etc. Successful cases include the famous B2 aircraft in the United States, but there are few commercial cases, mainly used for large bombers. The main reason affecting its practicality is how to "maintain the balance of this aircraft", especially for commercial economical small and medium-sized delta-wing aircraft, reliability and stability are very important. The delta-wing aircraft needs to have a strong balance force, the number of engines cannot be too small, and the reaction speed between the engines must be fast enough to avoid "turning over". Because the traditional power energy is a jet system, due to factors such as cost, the number of engines equipped on the aircraft is not enough, no more than 4, and the power of flight is not synchronized enough.

[0005] About vertical take-off and landing (VTOL). Vertical take-off and landing technology is to use vertical thrust engines to make the aircraft directly take off without the need for a take-off runway. This technology is similar to helicopters. The difference between vertical take-off and landing aircraft and helicopters is that the vertical take-off and landing engines 1) are not one but multiple (more than 4), 2) are relatively light and small (within 100 kg), and 3) are not that powerful. As far as the current scientific and technological status is concerned, DJI's DJI T40 vertical take-off and landing aircraft is mainly used for low-speed hovering operations, such as spraying pesticides. Because it is not equipped with a horizontal thrust engine, it cannot fly fast and the hovering time is not long. It should be noted that vertical take-off and landing aircraft are often powered by electricity, so eVTOL (electric VTOL) and VTOL are synonymous. The realization of vertical take-off and landing often requires the use of electric aviation engines. The reason is that gas aviation engines are too expensive, inconvenient to assemble, and not easy to rotate. Electric aviation engines can effectively avoid these shortcomings, so vertical take-off and landing VTOL is also called electric vertical take-off and landing eVTOL.

[0006] About distributed electric propulsion technology (DEP), and high-speed aircraft. It ensures that new energy aircraft can achieve both VTOL and high-speed horizontal flight. Distributed electric propulsion technology uses electricity to drive multiple electric aviation engines (3 or more) as the power unit of the aircraft. These electric aviation engines provide various maneuvering power for the aircraft in a linked and distributed manner, such as the vertical take-off and landing mentioned above, as well as various flight actions such as horizontal high-speed flight, rapid turning, rapid lift-off, and sharp deceleration. DEP, that is, the linkage technology of multiple electric engines and aircraft, is currently a hot topic in the aviation field. Distributed electric propulsion technology makes it possible to achieve the advanced aircraft manufacturing concept of standardized design and manufacturing of multiple electric aviation engines and aircraft. DEP distributed electric propulsion technology has great potential in improving aircraft aerodynamic efficiency, carrying capacity and robustness, and is widely regarded as a disruptive technology in the aviation field. Although distributed electric propulsion technology can provide many application scenarios and is currently a hot topic in theoretical research at home and abroad, there are relatively few application cases and designs of distributed electric propulsion technology. For example, distributed electric propulsion technology can start the linkage technology of multiple engines and aircraft, but there are relatively few research works and ideas on how to link, design solutions and practice to produce actual benefits.

[0007] In view of this, the present invention is proposed. Summary of the invention

[0008] In view of the defects in the prior art, the purpose of the present application is to provide a multi-electric vertical take-off and landing high-speed green aircraft, that is, a triangular aircraft with electric aviation engines configured at multiple points and a wing-body integration. A triangular physical configuration of the vertical take-off and landing aircraft is proposed, and a vertical and horizontal rotation configuration scheme of the multi-point multi-electric engines is proposed. The aircraft can take off and land vertically and can fly at a relatively high horizontal speed. The aircraft has a large load capacity and load space. At the same time, the engine is small in size, and multiple engines can be placed at different positions of the aircraft. Because it is electrically controlled and has good synchronization, multiple engines cooperate with sensors to dynamically adjust the flight state and maintain the balance state of the aircraft synchronously, making the wing-body integration delta-wing aircraft a commercial possibility.

[0009] In one aspect of the present application, a multi-electric vertical take-off and landing high-speed green aircraft is provided, comprising:

[0010] The fuselage is a triangular wing-body structure;

[0011] The mounting slot plate frame is provided with a plurality of mounting slots and is connected to the fuselage at a plurality of joint points;

[0012] Multi-point multi-electric engines, including horizontal engines that provide horizontal thrust and vertical engines that provide vertical thrust, or, including rotatable rotary engines that can achieve horizontal and vertical conversion;

[0013] The rotary engine, the horizontal engine and the vertical engine are respectively arranged in the installation grooves and are connected to the fuselage via a plurality of nodes.

[0014] Further, the mounting slot plate frame is arranged inside the fuselage;

[0015] Alternatively, the mounting slot frame is arranged at the bottom of the fuselage.

[0016] Furthermore, the mounting slot plate frame is integrally connected to the fuselage or assembled and detachably connected.

[0017] Further, the installation slot includes: a first installation slot having a plurality of slots, which are arranged at intervals on the edge of the installation slot frame, and the vertical engine is arranged in the first installation slot;

[0018] The second mounting groove is arranged at the center of the mounting groove plate frame and is used for mounting the horizontal engine.

[0019] Furthermore, it also includes a fixing pile, one end of which passes through the second installation slot, and the other end is fixed to the installation slot plate frame;

[0020] The fixing pile is provided with a third mounting groove, and the horizontal engine comprises a first horizontal engine, and the first horizontal engine is horizontally arranged in the third mounting groove.

[0021] Furthermore, a fourth mounting slot is provided at the bottom of the mounting slot plate frame, and the horizontal engine also includes a second horizontal engine, which is arranged in the fourth mounting slot and is used to balance the horizontal torque of the aircraft.

[0022] Furthermore, the mounting groove plate frame is also provided with a mounting plate extending from the top of the mounting groove plate frame toward the bottom;

[0023] The fourth mounting groove is arranged on the mounting plate.

[0024] Furthermore, it also includes a gear steering device, which is arranged in the installation groove and is used to control the rotary engine to achieve horizontal and vertical conversion.

[0025] Furthermore, a cavity is provided between the fuselage and the mounting slot frame, and a square structure is provided in the cavity, and a receiving cavity is formed between the square structure and the mounting slot frame, and the receiving cavity is used to bear aviation loads.

[0026] Furthermore, the engine is an electrically driven ducted fan engine.

[0027] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0028] 1. The present application discloses a triangular wing-body aircraft model, which is triangular in shape, equipped with multi-point multi-electric engines, and has a vertical and horizontal rotation configuration scheme, which improves the flexibility of the aircraft. It also has vertical take-off and landing and high-speed flight functions, and is a unique aircraft with multiple vertical and horizontal electric aviation propulsion power systems, which realizes the renewal of flight concepts.

[0029] 2. This application is equipped with a vertical engine, which can perform vertical take-off and landing without a runway, thereby improving the flexibility of the aircraft in limited space or emergency situations. The horizontal engine provides horizontal thrust, so that the aircraft can be converted to horizontal flight after reaching a certain height and speed, achieving the purpose of vertical take-off and landing and high-speed flight. At the same time, a more efficient electric drive and distribution system is adopted to reduce the weight of the aircraft, improve fuel efficiency and reduce maintenance costs.

[0030] 3. The present application combines vertical take-off and landing with horizontal flight to realize a brand new five-step aircraft flight. Specifically, it eliminates the two processes of take-off and landing that require an airport. It can take off and land vertically or use a very small space to take off and land. It does not require an airport to take off and land. It can achieve vertical take-off and landing in a small area (a few meters in size) to achieve aviation rescue missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0032] Figure 1 This is a structural diagram of a multi-electric vertical take-off and landing high-speed green aircraft according to an embodiment of the present application.

[0033] Figure 2 This is a structural diagram of a multi-electric vertical take-off and landing high-speed green aircraft according to an embodiment of the present application.

[0034] Figure 3 This is a schematic diagram of a fuselage and mounting slot frame device according to an embodiment of the present application.

[0035] Figure 4 This is a schematic diagram of the installation structure of the slotted plate frame according to one embodiment of the present application.

[0036] Figure 5 This is a schematic diagram of the assembly of the engine and the mounting slot frame according to an embodiment of the present application.

[0037] Figure 6 This is a schematic diagram of the assembly of a horizontal thrust engine according to an embodiment of the present application.

[0038] Figure 7 This is a schematic diagram of the structure of a gear steering device according to an embodiment of the present application.

[0039] Figure 8 This is a schematic diagram of a test platform according to an embodiment of the present application.

[0040] Fig. 9 This is a schematic diagram of the five flight steps of an embodiment of the present application.

[0041] In the figure: 1. fuselage; 2. mounting slot frame; 21. mounting slot; 210. first mounting slot; 211. second mounting slot; 22. mounting plate; 220. fourth mounting slot; 3. engine; 31. rotary engine; 32. horizontal engine; 320. first horizontal engine; 321. second horizontal engine; 33. vertical engine; 4. fixing pile; 41. third mounting slot; 5. gear steering device; 51. steering rod; 52. steering gear; 53. meshing gear; 6. rudder. DETAILED DESCRIPTION

[0042] The present application is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that, for those of ordinary skill in the art, several variations and improvements can also be made without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0043] The present application proposes a multi-electric vertical take-off and landing high-speed green aircraft (the so-called green aircraft refers to: using green energy to generate electricity, and then using the generated electricity to drive electric aircraft. Green energy is the trend of world energy development, and China's green electricity, wind, solar power and water have natural geographical advantages) aircraft, which is an electric aviation engine multi-point configuration wing-body integrated aircraft. The electric aviation engine is small in size, and multiple aviation engines can be placed at different positions of the aircraft. Because it is electrically controlled and has good synchronization, it cooperates with sensors to dynamically adjust the flight state and simultaneously maintain the balance state of the aircraft, making the wing-body integrated delta-wing aircraft a commercial possibility.

[0044] Reference Figure 1 As shown, a multi-electric vertical take-off and landing high-speed green aircraft according to an embodiment of the present application includes a fuselage 1, a mounting slot frame 2, and an engine 3. Among them, the fuselage 1 is a triangular wing-body integrated structure; the mounting slot frame 2 is provided with a plurality of mounting slots 21, and is connected to the fuselage 1 at a plurality of joint points; the multi-point multi-electric engine 3 includes a horizontal engine 32 providing horizontal thrust and a vertical engine 33 providing vertical thrust, or includes a rotatable rotary engine 31, which can realize horizontal and vertical conversion; the rotary engine 31, the horizontal engine 32, and the vertical engine 33 are respectively arranged in the mounting slot 31, and are connected to the fuselage 1 at a plurality of nodes.

[0045] The present application is equipped with a vertical engine 33, which can perform vertical take-off and landing without a runway, thereby improving the flexibility of the aircraft in space-constrained or emergency situations. The horizontal engine 32 provides horizontal thrust, so that the aircraft can be converted to horizontal flight after reaching a certain height and speed, thereby achieving the purpose of vertical take-off and landing and high-speed flight. At the same time, a more efficient electric drive and distribution system is adopted to reduce the weight of the aircraft, improve fuel efficiency and reduce maintenance costs.

[0046] Specifically, in the above embodiments, one of the specific implementations is: a plurality of mounting slots 21 are provided on the mounting slot frame 2, the multi-point multi-electric engine 3 includes a horizontal engine 32 for providing horizontal thrust and a vertical engine 33 for providing vertical thrust, the horizontal thrust engine and the vertical thrust engine are respectively arranged in the mounting slots 21 of the mounting slot frame 2, and when performing a take-off mission, the aircraft takes off by means of the vertical thrust engine and the horizontal thrust engine.

[0047] In the above embodiment, horizontal and vertical engines are arranged at multiple locations of the delta-wing aircraft to independently realize vertical take-off and landing and horizontal flight, utilizing the characteristics of electric aircraft engines, such as light weight, good electrical synchronization, and economical price. The difference from one solution is that the aircraft engines can be made smaller and more numerous, and vertical thrust and horizontal thrust can be independently generated without rotation: vertical thrust is used for vertical take-off and landing during take-off, and horizontal thrust is used to provide high-speed flight power during navigation, eliminating the transmission device for engine rotation, increasing reliability, and improving simplicity.

[0048] For example: Figure 1 As shown, the vertical engine 33 is vertically mounted in the four mounting slots 21 of the mounting frame, and the horizontal thrust engine is mounted on the fixing pile 4, and then the fixing pile 4 is mounted at the center of the upper mounting slot 41. It can be fixed by bolting.

[0049] Among them, the vertical engine 33 and the horizontal engine 32 in this application can exert force at the same time to achieve the best flight state, such as the lowest fuel consumption rate and power consumption. For example, while the horizontal engine is flying at high speed, the thrust generated by the vertical engine is used synchronously to reduce the weight of the aircraft. The flight effect brought about is that the lift-to-drag ratio of the aircraft is improved due to the reduction of the flight weight, or the drag is reduced under the condition of the same aircraft lift-to-drag ratio, so that the aircraft can obtain a relatively high horizontal speed with a smaller lateral thrust. This design is suitable for medium-sized new energy aircraft, which require multiple engines to provide thrust. The aircraft is relatively large in size, 1 ton to 10 tons, and there is enough plane space to place multiple engines.

[0050] Another specific implementation is: a plurality of mounting slots 21 are provided on the mounting slot frame 2, and a plurality of rotatable engines 31 are installed in the mounting slots 21, so that when performing a flight mission, the vertical and horizontal states can be switched as needed, providing vertical power and horizontal thrust at the same time.

[0051] as follows Figure 2 As shown in the figure, the two rear engines are in a horizontal propulsion state, and the front engine is in a vertical propulsion state. By adjusting the power of the engine, the aircraft can be in a climbing state, that is, the nose is raised and the tail is lowered. The following example is an example of an aircraft climbing. During the flight of the aircraft, the three engines can independently perform vertical and horizontal conversions to adapt to the current situation. The conversion device is as follows Figure 7 As shown, the horizontal to vertical conversion is achieved by rotating the rotating rod 51 and the steering gear 52.

[0052] In some possible embodiments, the present application also provides a design solution, referring to Figure 2As shown, the design scheme takes advantage of the characteristics of the electric aircraft engine being light and agile, and uses a rotatable wing to complete the rotation of the engine 3, so as to realize the flexible rotation and steering of the aircraft engine 3. At the bottom of the aircraft, at the three corners and the center of the triangle, a multi-point freely rotatable lateral and vertical thrust engine 3 is arranged, and the direction of the engine 3 is adjusted according to the flight state. This multi-point electric aircraft engine 3 design method requires a gear rotor device to realize the flexible conversion of the engine between vertical and horizontal. In addition, there is a rotating rudder 6 on the top of the aircraft to quickly adjust the flight direction. The vertical and horizontal thrust engines 3 need to adopt a gear steering device 5 (such as Figure 7 The conversion can be achieved by using a relatively small number of engines to achieve vertical and horizontal flight functions, which physically reduces the weight of the aircraft.

[0053] Reference Fig. 9 As shown, the gear steering device 5 includes a rotating rod 51, a steering gear 52, and a meshing gear 53. The rotating rod 51 is sleeved with a steering gear 52, and the output of the steering gear 52 is vertically meshed with another meshing gear 53, and the output of the other gear is connected to the engine 3. The rotating rod 51 is driven by the rudder 6 and the driving device to rotate, thereby driving the steering gear 52 connected to the rotating rod 51 to rotate, and the steering gear 52 drives another gear meshing with it 53 to rotate, thereby realizing the flexible conversion of the engine between vertical and horizontal.

[0054] In some possible embodiments, the mounting slot plate frame 2 is arranged inside the fuselage 1. Of course, in other embodiments, the mounting slot plate frame 2 can also be arranged at the bottom of the fuselage 1.

[0055] Specifically, one specific implementation is: when the mounting slot plate frame 2 is arranged inside the fuselage 1, the bottom of the fuselage 1 is provided with openings corresponding to the multiple mounting slots 21 on the mounting slot plate frame 2, so as to facilitate the passing of the motor when installing. Another specific implementation is: the mounting slot plate frame 2 is arranged at the bottom of the fuselage 1, and is fixedly connected to the fuselage 1, and there is no need to set an opening at the bottom of the fuselage 1, and the engine 3 is directly installed through the multiple mounting slots 21 on the mounting slot plate frame 2.

[0056] In some possible embodiments, the mounting slot plate frame 2 is integrally connected to the fuselage 1 or assembled and detachably connected.

[0057] When assembling, this application includes two methods: one is integrated and the other is assembled. The former is suitable for small aircraft with a scale of less than 3 meters. The engine 3 is an electric aviation engine with no more than 7 engines. The latter is suitable for medium-sized aircraft with a scale of 3 meters to 10 meters. The integrated aircraft molding method can be formed in one step by 3D printing. The assembled method can be made into several components by 3D or other film-forming methods such as casting, and then assembled into shape. There are also two ways to match the aircraft engine 3 with the aircraft. One is to place the engine 3 on an independent mounting slot plate frame 2, and then integrate the mounting slot plate frame 2 with the aircraft fuselage 1. The second method is that the aircraft fuselage 1 itself has a predetermined position and a fixing device for assembling the engine 3, and the aircraft engine 3 is organically installed in various parts of the aircraft. Both have their own advantages and characteristics, and need to be selected according to specific scenarios, manufacturing processes and. The following is a detailed introduction.

[0058] Specifically, one manufacturing solution is an integrated one. When the mounting slot frame 2 is arranged inside the fuselage 1, the mounting slot frame 2 and the fuselage 1 can be formed in one piece. By integrating the fuselage 1 and the engine 3 mounting device into one body, the engine 3 is directly mounted on the aircraft. The mounting slot frame 2, the aircraft and other accessories are printed out by 3D printing, and then the electric engine 3 is fixed with screws by punching holes to realize the suspended flight of the aircraft. Figure 5 As shown, the engine 3 is mounted in the mounting hole or the fixing pile, and these mounting brackets and structures are integrated on the aircraft. The above embodiment can print the mounting bracket and the aircraft as a whole by 3D printing, and the engine is inside the aircraft. The above method is suitable for drone express delivery.

[0059] When the mounting slot frame 2 is arranged at the bottom of the fuselage 1, another manufacturing scheme is to combine the fuselage 1 and the engine 3 mounting device into an assembly type, such as Figure 3 and Figure 6 As shown, the fuselage 1 of the aircraft is on the top, and the base with the engine 3 is in the middle. The fuselage 1 is placed on the base to form an assembly type, thereby realizing the assembly of the aircraft.

[0060] In some possible embodiments, the mounting slot 21 includes: a first mounting slot 210, which has multiple slots spaced apart at the edge of the mounting slot frame 2, and the vertical engine 33 is arranged in the first mounting slot 210; a second mounting slot 211, which is arranged at the center of the mounting slot frame 2 and is used to install the horizontal engine 32.

[0061] Specifically, the engine 3, the mounting slot frame 2 and the fuselage 1 are assembled, with the fuselage 1 of the aircraft on top and the mounting slot frame 2 with the engine 3 in the middle. The aircraft is placed on the mounting slot frame 2. There are four engine 3 placement slots on the mounting slot frame 2 of the engine 3. The engine 3 is installed in the corresponding mounting slots 21, among which the four first mounting slots 210 on the edge of the mounting slot frame 2 are the vertical engine 33 installation positions that provide vertical lift.

[0062] In the above embodiment, it also includes a fixing pile 4, one end of which passes through the second mounting groove 211, and the other end is fixed on the mounting groove plate frame 2; a third mounting groove 41 is provided on the fixing pile 4, and the horizontal engine 32 includes a first horizontal engine 320, and the first horizontal engine 320 is horizontally arranged in the third mounting groove 41.

[0063] The third mounting slot 41 in the middle is used as the mounting position of the engine 3 for providing horizontal thrust. A fixing pile 4 is extended from the second mounting slot 211 toward the bottom of the fuselage 1, and a third mounting slot 41 is provided on the fixing pile 4. The first horizontal engine 320 is installed in the third mounting slot 41 to provide horizontal thrust for the aircraft. As an option, the wheels of the aircraft can be installed on the mounting slot frame 2 of the aircraft to facilitate horizontal gliding during landing. A rudder 3 can be installed on the top of the aircraft for fine-tuning of the direction.

[0064] Reference Figures 4 to 5 As shown, it is an embodiment of the present application, the inner wall of the second installation groove 211 is provided with a symmetrical positioning groove, and the outer wall of the fixing pile is provided with a positioning protrusion matching the positioning groove; the positioning protrusion can pass through the positioning groove during installation.

[0065] The present application sets a positioning groove, and when installing the fixing pile 4, the positioning protrusion on the fixing pile 4 is aligned with the positioning groove on the inner wall of the second installation groove 211, and the fixing pile 4 can be installed on the installation groove plate frame 2. At the same time, a fixing hole is provided on the outer side of the second installation groove 211, and a flange is provided at one end of the fixing pile 4 adjacent to the positioning groove, and an opening corresponding to the fixing hole is provided on the flange, and the fixing pile 4 is fixedly connected to the installation groove plate frame 2 by screws.

[0066] Reference Figure 6 As shown, in some possible embodiments, a fourth mounting slot 220 is further provided at the bottom of the mounting slot frame 2, and the horizontal engine 32 further includes a second horizontal engine 321, which is arranged in the fourth mounting slot 220, for balancing the horizontal torque of the aircraft.

[0067] In the above embodiment, specifically, the mounting slot frame 2 is further provided with a mounting plate 22 extending from the top to the bottom of the mounting slot frame 2 ; the fourth mounting slot 220 is provided on the mounting plate 22 .

[0068] Reference Figure 6 As shown, this is an embodiment of the present application, the horizontal engine 32 also includes a second horizontal engine 321, which is used to balance the horizontal torque of the aircraft; the mounting slot frame 2 is also provided with a mounting plate 22 extending from the top to the bottom of the mounting slot frame 2, which is used to install the second horizontal engine 321.

[0069] The present application sets a plurality of second horizontal engines 321 on the mounting slot frame 2. Their function is to avoid the problem that the aircraft rotates horizontally, loses balance, and falls into a spinning state due to the inertia of the rotation of the vertical engine 33 during vertical takeoff. Since the thrust of the first horizontal engine 320 and the second horizontal engine 321 deviates from the center of the aircraft, the horizontal rotation caused by inertia can be balanced by adjusting the thrust of the first horizontal engine 320 and the second horizontal engine 321. By installing one or more engines (below) to balance the horizontal torque inside the aircraft, Figure 5 , 6 As shown in FIG. 1 , the thrust of the horizontally placed first horizontal engine 320 and the second horizontal engine 321 (ducted fan) is used to balance the torque generated by the four vertically placed ducted fans when they rotate, so as to achieve efficient operation of the aircraft. In addition to balancing the torque, the two horizontal engines 32 can also provide additional horizontal thrust for the aircraft.

[0070] As an example of a design solution, 1 to 4 horizontal engines 32 are placed on the mounting slot frame 2 to provide horizontal thrust, and 4 vertical engines 33 at the four corners provide vertical thrust so that the aircraft can take off and land vertically. The power system is composed of a trinity of an electric motor, a ducted fan, and a battery.

[0071] The principle of existing single-rotor helicopters to cope with torque is to add a small propeller at the tail of the helicopter to balance the torque with reverse thrust, so the small propeller is also called a torsion propeller. If the helicopter is not equipped with such a tail rotor, it may cause the helicopter to lose balance easily during flight. The main function of the tail rotor is to balance the torque generated by the main rotor when it rotates. For traditional single-rotor helicopters, the tail rotor is a key part. The tail rotor is crucial to the stability of the helicopter. If the tail rotor fails, it is a very dangerous situation that may cause a crash.

[0072] The situation is different for existing twin-rotor helicopters. Coaxial twin-rotor helicopters do not have a small propeller at the tail. Whether it is a coaxial or non-coaxial twin-rotor helicopter, their two blades rotate in opposite directions. The advantage of this design is that the torque generated by the two blades will offset each other, so there is no need for a tail rotor to balance. Most helicopters are still single-rotor helicopters. For traditional single-rotor helicopters, the tail rotor is a key part.

[0073] The drones commonly used now use four propellers to balance the torque of the propeller rotation. Among the four propellers of the existing rotor drones, the two opposite propellers rotate in opposite directions, so that the aircraft will not rotate horizontally.

[0074] The new energy multi-electric vertical take-off and landing aircraft proposed in the present application adopts an electric ducted fan jet (i.e., engine) as aviation power, and the ducted fans on the market all rotate in the same direction. When the four vertically-powered ducted fan jets rotate at the same time to generate vertical thrust, the aircraft will also produce horizontal rotation due to the action of torque. In order to balance the effect of this torque, it is necessary to add a horizontal thrust engine off-center when designing the aircraft. The off-center thrust is used to balance the torque of the four engines and make the aircraft reach a stable state. The present application uses the above-mentioned torque balancing method to overcome the torque problem generated when starting the flight.

[0075] In some possible embodiments, a gear steering device 5 is further included, which is arranged in the installation slot 21 and is used to control the rotary engine 31 to achieve horizontal and vertical conversion.

[0076] In the above embodiment, the rotary engine 31 is used to achieve the dual technical purposes of vertical take-off and landing and horizontal flight. Figure 2 and Figure 7 As shown, this design scheme takes advantage of the characteristics of the electric aviation engine being light and agile, and uses the rotatable wing to complete the rotation of the engine 3, realizing the flexible rotation and steering of the aviation engine. At the bottom of the aircraft, at the three corners of the triangle and the center position, multiple freely rotatable lateral and vertical thrust engines are arranged, and the direction of the engine is adjusted according to the flight state. This multi-point electric aviation engine design method requires a gear steering device 5 to realize the flexible conversion of the engine between vertical and horizontal. In addition, there is a rotating rudder 6 on the top of the aircraft to quickly adjust the flight direction. The vertical and horizontal thrust engines 3 require a special gear transmission method to achieve the conversion. The advantage of this design is that a relatively small number of engines can be used to achieve vertical and horizontal flight functions, which physically reduces the weight of the aircraft.

[0077] In some possible embodiments, there is a cavity between the fuselage 1 and the mounting slot frame 2, and a square structure is provided in the cavity to form a receiving cavity between the mounting slot frame 2, and the receiving cavity is used to bear aviation loads.

[0078] In the above embodiment, the engine 3 is an electrically driven ducted fan engine, which includes a horizontal engine 32 , a vertical engine 33 and a rotary engine 31 .

[0079] Reference Figure 8As described above, for one embodiment of the present application, a method for testing aircraft performance is provided, starting from a small-sized model aircraft and transitioning to an actual-sized aircraft, starting from a preliminary verification experiment and gradually transitioning to future reliability commercial practice, starting from an unmanned express delivery aircraft and transitioning to manned operation. Different from the traditional aircraft flight method, a unique, concise and feasible test solution is designed.

[0080] A fixed cylinder is erected vertically, and the aircraft is connected to the cylinder with a lifting rod using bearings. The vertical engine is started to lift the aircraft vertically and hover, and then the horizontal thrust engine is started to rotate along the central axis, and the aircraft delta wing is used to achieve lift-off and flight, and technical parameters such as lift-to-drag ratio are measured.

[0081] Specifically including control, connection and flight.

[0082] In this embodiment, control is performed by remote control to control the vertical and horizontal flight of the aircraft and their related combinations. The aircraft is allowed to glide and fly vertically along a fixed cylinder to measure its flight speed and vertical take-off and landing capability.

[0083] In this embodiment, the connection is: one end of a straight rod is connected to the aircraft, and the other end is connected to the cylinder, so that the aircraft can rise and fall synchronously and rotate horizontally around the cylinder along the circumference. One end of the aircraft is fixed on a vertical column, and the connection can slide up and down with a bearing, and relevant flight data can be collected during this process.

[0084] During flight in this embodiment: a. the vertical engine generates power to achieve vertical lift and suspension, b. after suspension, the horizontal engine is started to generate horizontal speed along the circumference, c. when the horizontal acceleration reaches a certain level, the Bernoulli streamline design of the aircraft can enable the aircraft to generate lift and rise in a circular rotation.

[0085] The specific experimental process is as follows: after installing the electric engine, the engine is controlled by remote control of the drone to make the aircraft take off and hover, and the lift test is carried out at the same time. 1) Detect the movement speed of the aircraft. The method of detecting the speed of the aircraft is to measure the number of circles per unit time. The radius of the circle is a known number, so the circumference of the circle can be calculated. The circumference divided by the unit time value is the orbital speed. 2) Detect the actual thrust of the vertical engine of the aircraft, which can be achieved using a thrust meter.

[0086] After taking off, the aircraft can be controlled wirelessly to perform circular accelerated flight around a cylinder. When the speed reaches the take-off speed, the aircraft will take off from the ground, and then the aircraft will perform a spiral accelerated ascent process along the circumference. During the circular ascent flight, the aircraft's rotation speed can be detected to estimate the horizontal movement speed of the aircraft. The actual thrust of the aircraft's horizontal engine can be calculated using the formula for the flight lift-to-drag ratio, and experimental data can be collected to optimize the aircraft design. For example, different aircraft design shapes can be used for experiments, and their lift-to-drag ratios can be compared to obtain the best design. The aircraft's rotation experiment is controlled by a drone, and the periphery of the rotating space is surrounded by wire mesh to ensure the safety of the experimenters. Through flight experiments, new energy aircraft are developed and their stability, safety, and operability during flight are studied in a controllable and monitorable operability environment in the laboratory.

[0087] Through the above process, the flight mode is realized as an organic combination of vertical take-off and landing and horizontal propulsion. At the same time, the flight process is vertical take-off and landing at the head and tail, and navigation relies on horizontal thrust.

[0088] Reference Fig. 9 As shown, it is an embodiment of the present application, which provides a new flight process.

[0089] First, a possible specific embodiment of the present application takes a delta-wing multi-point multi-electric VTOL aircraft as an example:

[0090] The delta-wing aircraft has a larger internal volume, a higher headwind ratio, and better flight dynamics; the multi-point vertical injection engine can realize vertical take-off and landing of the aircraft, has no airport restrictions, and is suitable for a variety of maneuvering purposes (such as emergency helicopter rescue); the multi-point horizontal propulsion electric engine can increase the flight speed, instead of the ordinary drone or helicopter, the maximum speed can only reach 200 kilometers per hour. There are two major categories of this type of aircraft: pure electric drive and hybrid electric drive. The former is suitable for small models less than 1 ton, with a flight radius of less than 200km and a flight time of less than 2 hours. The latter is a medium-sized aircraft less than 10 tons, with a flight radius of up to 1000km and a flight time of not less than 7 hours. New energy aircraft are air cars and Taobao express delivery machines. The prototype is planned to weigh less than 10 kilograms and less than 600 mm. The future goal is a 300kg-10-ton sedan aircraft and a van aircraft. The engines for vertical take-off and horizontal flight operate independently to achieve an update of the flight concept.

[0091] First of all, the traditional flight concept is: the old five steps of flight are: the first step is horizontal takeoff which requires a runway; the second step is horizontal climb which requires distance; the third step is parallel flight; the fourth step is horizontal gradual descent which requires distance; and the fifth step is horizontal landing which requires a runway.

[0092] Reference Fig. 9As shown, the vertical take-off and landing function of this application has achieved a new flight concept, that is, the new five-step flight:

[0093] The first step is vertical take-off without the need for an airport; the second step is to combine vertical and horizontal flight to achieve rapid climb; the third is to combine vertical and horizontal flight to achieve optimal lift-to-drag ratio flight; the fourth is to combine vertical and horizontal flight to quickly decelerate and descend; and the fifth is vertical landing.

[0094] Specifically, it includes take-off, climb, navigation, descent and landing.

[0095] The takeoff is as follows: During a vertical takeoff, the aircraft faces the ground (the front is at the top and the rear is at the bottom) to provide vertical jet thrust.

[0096] Then climb: After takeoff, the engine angle gradually rotates from 90 degrees to 60 degrees, and then to 45 degrees to tilt. The aircraft gradually climbs at a steady cruising speed.

[0097] Then fly: Once the aircraft reaches its flying altitude, all electric engines should be oriented to the appropriate angles to achieve the best horizontal / vertical propulsion efficiency. This stable attitude is achieved through the vertical jets of the electric engines and the lift-to-weight ratio of the entire aircraft during flight. The aircraft streamline should be carefully designed with the help of CFD and test flights to achieve the best L / D ratio.

[0098] Then comes the landing: As the aircraft approaches its destination, the deceleration mode begins, with the horizontal engines slowing down and the vertical thrust engines turning on, which together allow the aircraft to decelerate within a much shorter range than with traditional landing methods.

[0099] Final touchdown: When the triangular aircraft reaches zero horizontal speed, all vertical engines provide moderate thrust to cushion the aircraft gradually descending to the ground. Appropriate sensors are needed to detect the distance from the ground so that the foldable landing gear can be deployed and the aircraft can be landed stably on the ground.

[0100] Compared with the old five-step flight that requires huge airport resources, the new five-step flight greatly increases the flexibility, maneuverability and economy of flight, and can complete air rescue tasks in a small area, such as vertical take-off and landing and picking up the wounded within a range of three meters. This 3×3 aircraft can carry three people, has a side length of only three meters, and is equipped with three electric engines, so it is called a 3×3 electric rescue aircraft. There are many similar mobile scenarios, and the uses of new energy electric helicopters are unlimited.

[0101] The above describes the specific embodiments of the present application. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various modifications or variations within the scope of the claims, which does not affect the substantive content of the present application. The above preferred features can be used in any combination without conflicting with each other.

Claims

1. A multi-electric vertical take-off and landing high-speed green aircraft, characterized in that: include: The fuselage is a triangular wing-body structure; The mounting slot plate frame is provided with a plurality of mounting slots and is connected to the fuselage at a plurality of joint points; The engine includes a horizontal engine that provides horizontal thrust and a vertical engine that provides vertical thrust, or includes a rotatable rotary engine that can achieve horizontal and vertical conversion; The rotary engine, horizontal engine and vertical engine are respectively arranged in the installation grooves and connected to the fuselage through multiple nodes to form a multi-point multi-electric engine.

2. A multi-electric vertical take-off and landing high-speed green aircraft according to claim 1, characterized in that: The mounting slot frame is arranged inside the fuselage; Alternatively, the mounting slot frame is arranged at the bottom of the fuselage.

3. A multi-electric vertical take-off and landing high-speed green aircraft according to claim 2, characterized in that: The mounting slot plate frame is integrally connected with the fuselage or assembled and detachably connected.

4. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 1, characterized in that: The mounting slot comprises: a first mounting slot having a plurality of slots disposed at intervals on the edge of the mounting slot plate frame, wherein the vertical engine is disposed in the first mounting slot; The second mounting groove is arranged at the center of the mounting groove plate frame and is used for mounting the horizontal engine.

5. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 4, characterized in that: It also includes a fixing pile, one end of which passes through the second mounting slot and the other end is fixed to the mounting slot plate frame; The fixing pile is provided with a third mounting groove, and the horizontal engine comprises a first horizontal engine, and the first horizontal engine is horizontally arranged in the third mounting groove.

6. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 5, characterized in that: A fourth mounting slot is also provided at the bottom of the mounting slot plate frame, and the horizontal engine also includes a second horizontal engine, which is arranged in the fourth mounting slot and is used to balance the horizontal torque of the aircraft.

7. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 6, characterized in that: The mounting groove plate frame is also provided with a mounting plate extending from the top of the mounting groove plate frame toward the bottom; The fourth mounting groove is arranged on the mounting plate.

8. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 2, characterized in that: It also includes a gear steering device, which is arranged in the installation groove and is used to control the rotary engine to achieve horizontal and vertical conversion.

9. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 2, characterized in that: A cavity is provided between the fuselage and the mounting slot frame, and a square structure is provided in the cavity. A receiving cavity is formed between the square structure and the mounting slot frame, and the receiving cavity is used to bear aviation loads.

10. The multi-electric vertical take-off and landing high-speed green aircraft according to claim 1, characterized in that: The engine is an electrically driven ducted fan engine.

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