Multi-rotor coaxial helicopter

Abstract

Multi-rotor coaxial helicopter, characterized in that: the coaxial device engine first transmission shaft rod / tube is vertically erected upward and installs the upper rotor, the shaft rod / tube is equipped with the driving gear ring as the sun gear below, drives the three / multiple planetary gears distributed on the periphery, the planetary gears drive the second transmission shaft tube equipped with the strip tooth on the inner wall of corresponding horizontal position, and then drive another transmission shaft tube to rotate in the opposite direction.In the outer shaft tube of the second shaft tube, the lower rotor device is equipped with the upper part, and the bottom of the outer shaft tube is equipped with the center circular hole ring disc, and can rotate in the disc inner ring concave ratchet gear bearing.Engine shaft rod / tube passes through the center from it upward vertically, the disc has support rod and is fixed on the engine above, and the engine is fixed in the bottom plate position in the fuselage.

Description

[0001] Technical Fields: Helicopter Engines, Electromechanical Equipment, Control Systems, Navigation Equipment, Jet Engines

[0002] Background technology: The current development trend of coaxial rotor design for helicopters promotes the diversification and high speed of helicopters to meet people's needs for various types of helicopters.

[0003] SUMMARY OF THE INVENTION: A multi-rotor coaxial helicopter, characterized in that it includes a power plant system of one or more preferred turboshaft engines / fuel engines / gas engines for helicopters, a drive shaft / tube system, a starting device, an internally toothed ring with threads / ridges, an externally toothed ring with ridges, a toothed ring with racks on both the inside and outside, planetary gears, gears, ratchet gears and balls, a rotor device, a swashplate, an electric / pneumatic lever folding system, a pneumatic device, a flight control system, a shift manual control lever, a power take-off, a plurality of electric control keys marked with numbers / words for different functions, a control lever, a landing gear, a universal drive, a differential shaft, 4 rims and tires, a shock-absorbing spring device, a symmetrical tail wing and fixed wing, an electric control string-type propeller blade air duct, a propeller, a "towel" - shaped integrated support propeller with spaced and overlapping upper and lower blades, an outer T-shaped long blade, a fuselage frame, a cockpit, a seat compartment, a variable-frequency motor, a variable-frequency generator / electric start cycle generator, a commutator, a transformer, a rectifier, a capacitor, a resistor, a battery, an instrument, a multi-functional electronic product integrator, a chip component, a circuit board, a communication equipment system, a radio equipment, an avionics and navigation equipment, a plurality of laser wireless cameras, a video equipment, a multi-frame display with a splitter, an instrument, a plurality of data recorders for different items, a memory card black box, a lidar system, a plurality of electric control rotary air ducts / swashplates, a fuel tank / gas cylinder and pipelines, a plurality of small aviation jet engines and combustion chambers, and various parts / components / devices. Among them, the coaxial device includes: the aforementioned engine 1, the engine drive shaft rod / tube 2 vertically erected upward for installing the upper rotor mechanism at position 3, and a toothed ring with ridges 4 is sleeved at the lower position of the upper rotor drive shaft rod / tube as a driving toothed ring rotating with the drive shaft, for driving the planetary gears of three or more passive gears / toothed rings circumferentially distributed around it, that is, the driving toothed ring 4 rotating with the shaft sleeved outside the drive shaft / tube 2 serves as the central sun gear, and a plurality of solid gears of different specifications are circumferentially distributed around it after calculating the torques of the upper and lower rotors as passive rotating planetary gears. The planetary gears act on the toothed ridges on the inner side wall of the corresponding horizontal position of another drive shaft tube 5 outside its shaft, thereby driving the other drive shaft tube 5 outside its shaft to rotate in the opposite direction. Outside the drive shaft tube 2, another set of lower rotor device 6 is sleeved under the top wing of the helicopter. The lengths of the two drive shafts / tubes are different, and the outer rotating tube 5 is shorter than the drive rotating shaft rod / tube 2 at the central position inside it. The bottom of the outer shaft tube 5 is inserted and sleeved into a bottom ring disc 7 with a circular hole of a specified size. There is a ratchet gear 8, balls and bearings in the concave ring of the disc 7, and the outer shaft tube 5 can rotate and be sleeved in the ratchet gear 8 of the concave ring of the disc 7 as the drive shaft / tube 5. The drive shaft tube 2 passes through the center of the disc vertically upward. The disc is sleeved and fixed above the engine, and the engine is fixed at the inner bottom plate position 9 of the casing. The drive shaft 2 rotating vertically upward of the engine is at the center of the outer shaft tube 5 that can rotate in the opposite direction. There are support rods fixed on the outer circumference of the inner shaft tube 2 at the center of each rotatable planetary gear, and the bottom of each support rod is fixed and sleeved on the inner circumferential edge of the outer tube bottom disc 7 near the inside.The lower surface of the disk is fixed to the naval floor by support rods. Alternatively, support rods that support and fix the center of each rotatable planetary gear can extend downward through the disk and be fixed to the naval floor. The entire bottom disk is fixed and does not rotate, while the pawl gear 8, which is installed on its concave inner ring and can be inserted into the outer shaft tube 5, can rotate, forming a coaxial forward and reverse rotation mode for the upper and lower rotors. The engine 1 and drive shaft / tube 2, which are connected to the cockpit control system in automotive mode, operate the two sets of twin rotors on the vertical axis after startup.

[0004] Another engine 9, located at the tail of the helicopter fuselage, can rotate at the same speed as the aforementioned engine 1. Its universal joint vertical shaft bevel gear connects to the left and right half-shafts of the differential. Propellers 12 and 13 are fitted onto the outer ends / sides of these left and right half-shafts, with the propellers extending beyond the outer side of the tail fin. Both engines are connected to the cockpit control system in automotive driving mode. They can share the same fuel tank / cylinder or have two separate fuel tanks / cylinders, and can start simultaneously.

[0005] When the auxiliary power is replaced with a small aircraft jet engine, the same fuel tank / gas cylinder can be shared and connected to the combustion chamber of each jet engine.

[0006] A thin, electrically controlled / pneumatic lever is longitudinally mounted at the midpoint of the upper / lower surface of the helicopter's rotor blades. This lever resides in a spring-loaded groove on one side and can be electrically supported, extended, and flattened. It connects to the cockpit control system and is used for folding the rotor before takeoff and after landing. Specifically, the upper rotor folds its blades upwards, and the lower rotor folds its blades downwards. This differs from manually latched folding rotors and electrically controlled folding fixed wings with motors.

[0007] The helicopter has fixed wings mounted on both sides of the front fuselage. An even number of motor / electric starter generator propellers are symmetrically mounted on the front and both ends of the fixed wings, and are electrically connected to the cockpit control system and power battery via wires, enabling assisted forward flight. The propellers at both ends of the fixed wings can be replaced with an even number of small, symmetrically mounted jet engines for lateral flight. An even number of rotatable motor / electric starter generator ducts are symmetrically mounted on the outer side of the fuselage, near the bottom, and on the top / bottom of the fuselage shell. These ducts are electrically connected to the cockpit control system and power battery via wires, and can be controlled via electric buttons to move the helicopter left and right. An even number of motor / electric starter generator ducts 15 and 16, symmetrically mounted on the top / bottom of the fuselage shell, are electrically rotatable to the longitudinal direction via electrically controlled bases, and are electrically connected to the cockpit control system and power battery via wires, and can be controlled via electric buttons for auxiliary power flight. The wind tunnel is a turbofan / fan generator wind tunnel (application number CN116538020A), but it can also be a motor-driven blade wind tunnel. When used as a swashplate, pressing the marked control keys simultaneously controls the rotating wind tunnels on one side of the fuselage top and the other side of the fuselage bottom, causing the fuselage to tilt to one side for flight and turning. Pressing the control key again returns to level flight. Simultaneously pressing another marked control key controls the rotating wind tunnels on the other side of the fuselage top and the other side of the fuselage bottom, corresponding to the positions of the aforementioned wind tunnels, causing the fuselage to tilt to the other side for flight and turning. Pressing the control key again returns to level flight. Replacing the wind tunnels used as top and bottom swashplates with small jet engines, installed in the same position and number as the wind tunnels, and connected to the cockpit control system, allows for tilting and turning controlled by the same control keys as the wind tunnels. In other words, the rotatable jet engines on the top and bottom of the fuselage can serve as assisted forward flight as well as as swashplates for left-right movement and turning.

[0008] Multiple wired / wireless high-powered laser microphone cameras (19) are mounted at appropriate locations on the front, top, bottom, sides, and tail of the fuselage, and are wired to a junction box and a multi-frame display screen in the cockpit. The electrical signals emitted by the wireless cameras are displayed on the multi-frame display screen in the terminal building, showing the helicopter's flight environment and status. The junction box connects to the black box, which contains multiple radio and camera audio / video data recorder memory cards for flight recording and data storage.

[0009] The helicopter switches from ground-based to car-based driving mode, consisting of a third car engine 10 and a universal joint drive system. Its technical features include: the car engine 10 is located at the front bottom of the helicopter cockpit; the universal joint drive system is located on the bottom of the lower layer of the fuselage's two-layer floor; the car driveshaft connects to and drives the differentials of the left and right half-shafts of the rear axle; and four shock-absorbing wheels on the front and rear axles replace the helicopter's landing gear. The helicopter cockpit's control system is divided into two parts: the car-based control unit, steering wheel, instruments, multi-function electronic product integrator, and display screen are located on the left, controlling the third engine 10 and the universal joint drive system. The control units for the first engine 1 and its vertical driveshaft / tube rotor, the second engine 9 and its tail assembly, instruments, multi-function electronic product integrator, and display screen are located in the middle and on the right. The speed of the fuel / gas engine propeller is controlled by the gear shift lever and the throttle / gas valve. The speed of the electric motor / electric starter generator propeller and blower is electronically controlled by the control buttons. The driver's seat is designed as a sofa, while the passenger seating area is located at the rear of the cockpit.

[0010] In the coaxial design with two sets of dual rotors operating in the same direction, the planetary gears and support rods are removed. The drive gear ring 4, which rotates with the centrally rotating drive shaft / tube 2, drives the longitudinal rack on the inner wall of the second drive shaft tube 5, which is mounted at the same horizontal level, to rotate in the same direction. This, in turn, drives the entire second drive shaft tube 5 connected to its outer sleeve to rotate in the same direction. The lower rotor mounted on the drive shaft tube 5 rotates with the drive shaft tube 5. The disc 7 device mounted at the bottom of this rotating shaft tube 5 is the same as described above. The driving control mode is the same as described above.

[0011] In addition to the previously mentioned design of two sets of coaxial twin rotors rotating simultaneously in opposite directions and in the same direction, the rotary drive shaft tube 5 can also have an external gear ring mounted at its bottom. Beside it, another fuel / gas engine 11, which can be powered by a motor / electric starter generator and can start synchronously at the same speed, can be installed. The gear on the drive shaft of this engine 11 drives the external gear ring 14 mounted on the shaft tube 5 to rotate via a meshing / chain mechanism, thereby driving the shaft tube 2 and the lower rotor mounted above it to rotate. Based on calculated rotational torque data for the upper and lower rotors, when controlling the throttle / gas valves of the two engines 1 and 11, the outer shaft tube 5 and its internal vertical engine drive shaft tube 2 rotate simultaneously and synchronously at the same speed / or simultaneously and synchronously at different speeds in the same direction. Alternatively, the rotation direction of the engine 11 drive shaft can be set so that the drive shaft 2 and the rotary shaft tube 5 rotate in opposite directions respectively, thereby driving the upper and lower rotors on the two inner and outer shaft tubes to rotate and fly.

[0012] The helicopter pilot operates in both helicopter and car driving modes. In helicopter mode, the vertical folding wings are deployed, and the first and second engines (1, 9) or the first, second, and third engines (1, 9, 11) are started. This causes the propellers mounted on each drive shaft / pipe to rotate synchronously at low speeds. The coaxial upper and lower rotors rotate clockwise and counterclockwise. Increasing the engine throttle / air valves accelerates the rotors to high speeds for ascent. Once a controlled altitude is reached, the pilot can control forward, diagonal, left / right, circling, turning, and decelerating while hovering. After decelerating again, the pilot lands on the ground. After the rotors stop rotating, pressing the control button folds up both upper and lower rotors. The car driving mode operates similarly to driving a car.

[0013] Based on the design requirements for helicopter use, the heavier automotive driving components can be removed: engine 10, steering wheel, universal joint, shock absorber springs, wheel rims, instruments, and related parts and devices, as well as the control system, while retaining the devices and systems used in helicopter flight mode. Further removal of the fixed wings and front propeller, along with related parts and devices, is also possible, retaining the remaining devices, instruments, and control system. Various instruments, electronic product integrators (application number CN104820658A), terminals, and additional functions can be designed and installed according to the required functions.

[0014] This technical solution is applicable to helicopter cars and Chinook helicopters. The two drive shafts 2 and 5 of the engine / motor / electric starter cycle engine, along with the technical solution, can be designed and installed on the left and right sides / stern of a ship or boat, with the drive shafts extending outside the hull and a propeller mounted on them for navigation on water.

[0015] It is distinct from helicopters with a single vertical top wing and a propeller in the middle / on one side of the tail wing, coaxial helicopters, Chinook helicopters, vertical wing helicopter cars, and vertical wing Chinook helicopter cars. Attached image description:

[0016] Figure 1 It is a coaxial / two-drive-shaft tube device, the technical feature of which is as described in the invention description.

[0017] Figure 2 It is a coaxial top and bottom rotor helicopter, the technical feature of which is: including the various parts, components and avionics used mentioned above, according to the invention content of the technical solution, the preferred engine, coaxial device and the design of the helicopter coaxial / two vertical shaft tubes of the top and bottom rotors.

[0018] The other engine 9, located at the tail of the helicopter fuselage, can rotate at the same speed as the first engine 1. Its universal joint vertical shaft bevel gear connects to the left and right half-shafts of the differential. The outer ends / sides of the left and right half-shafts are fitted with propellers, which extend outwards from the tail fin. Both engines are connected to the cockpit control system in a car-like manner. They can share the same fuel tank / cylinder or have two separate fuel tanks / cylinders. The engines can start simultaneously to run their respective propellers synchronously.

[0019] The helicopter has fixed wings mounted on both sides of the forward fuselage. Motor / electric starter generator propellers are mounted on the front and at both ends of the fixed wings, and are electrically connected to the cockpit control system and power battery via electrical cables, enabling assisted forward flight. One or more motor / electric starter generator fan ducts are symmetrically mounted laterally on the inner sides of the fuselage (near the bottom) and on the top / bottom of the fuselage outer shell. These are electrically connected to the cockpit control system and power battery via electrical buttons, controlling the left and right propeller fan ducts respectively, serving as a mechanism for left and right movement of the fuselage. One or more motor / electric starter generator fan ducts are symmetrically mounted longitudinally on the top / bottom of the fuselage outer shell, electrically connected to the cockpit control system and power battery via electrical cables, and controlled via electrical buttons, providing auxiliary powered flight.

[0020] Multiple wired / wireless high-magnification laser microphone cameras are installed at any suitable location on the front, top, bottom, sides, and tail of the fuselage, and are wired to a junction box and a multi-frame display screen in the cockpit. The electrical signals emitted by the wireless cameras are displayed on the multi-frame display screen in the terminal building, showing the helicopter's flight environment and status. The junction box connects to the black box, which contains multiple radio and camera audio / video data recorder memory cards for flight recording and data storage.

[0021] In the coaxial design with two sets of dual rotors operating in the same direction, the planetary gears and support rods are removed. The driving gear ring, fitted onto the centrally rotating drive shaft / tube, drives the longitudinal rack inside the second drive shaft tube, which is mounted at the same horizontal level, to rotate in the same direction. This, in turn, drives the entire outer casing of the second drive shaft tube to rotate in the same direction. The lower rotor mounted on it rotates with the drive shaft tube. The disc device fitted at the bottom of this rotating shaft tube is the same as described above. The driving control mode is the same as described above.

[0022] In addition to the previous design of two sets of coaxial twin rotors rotating simultaneously in opposite directions or in the same direction, an external gear ring can be fitted at the bottom of the outermost rotating shaft tube. Next to it, another fuel / gas engine 11, which can be powered by a motor / electric starter generator and can start synchronously at the same speed, can be installed. The gear / chain on the engine's drive shaft drives the external gear ring 14 fitted on the outermost shaft tube to rotate, thereby driving the shaft tube 5 and the lower rotor mounted above it to rotate. Calculations show that when controlling the throttle / gas valves of the two engines, the outer shaft tube 5 and its internal vertical engine drive shaft tube 2 can rotate simultaneously at the same speed, simultaneously at different speeds in the same direction, or rotate in opposite directions, thus each driving the upper and lower rotors on the two inner and outer shaft tubes to rotate and fly.

[0023] The invention relates to an external gear ring device designed to be mounted on the lower part of an external rotating shaft, driven by a gear meshing / chain on an engine drive shaft. Its technical features are described in the invention description.

[0024] The front and rear transverse axles and wheel rims of a helicopter are fixedly mounted under the bottom protective plate, which is the same as the installation method of the front and rear transverse axles and wheel rims of a car body.

[0025] Figure 3 This is a coaxial rotor helicopter-car, characterized by the addition of a car-driving mode power unit based on the aforementioned coaxial rotor helicopter design. When switching from ground driving to car driving mode, the helicopter-car consists of a third car engine 10 located within the fuselage and a universal joint drive system. The car engine 10 is positioned at the bottom forward of the helicopter cockpit, the universal joint drive system is located at the bottom of the fuselage, the car driveshaft is connected to and driven by the differentials of the left and right half-axles of the rear axle, and the four shock-absorbing wheels on the front and rear axles replace the helicopter landing wheels. Driving is controlled by a steering wheel. The helicopter cockpit driving control system is divided into two parts: the car driving device, steering wheel and instruments, multi-function electronic product integrator, and display screen are located on the left. The driving control devices for the first engine 1, vertical rotor, second engine 9, and tail fin, as well as the instruments, multi-function electronic product integrator, and display screen, are located in the middle and on the right. The speed of the fuel / gas engine propeller is controlled by the gear shift lever and the throttle / gas valve, while the speed of the electric motor / electric starter generator propeller and blower is electronically controlled by the driving control keys. The driver's seat is designed as a sofa, while the passenger seating area is located at the rear of the cockpit.

[0026] Detailed implementation: The invention is carried out according to the technical solution described in the invention and the embodiments described in the accompanying drawings, and is tested, flown, and piloted.

Claims

1. The technical features of a multi-rotor coaxial helicopter are: It includes preferably more than one number of turboshaft engine / fuel engine / gas engine power plant systems for helicopters, drive shaft / tube systems, starting devices, internal toothed rings with threads / stripes, external toothed rings with stripes, toothed rings with racks inside and outside, planetary gears, gears, ratchet gears and balls, rotor devices, electric control / pneumatic lever folding systems, pneumatic devices, flight control systems, shift control levers, power take-offs, multiple electric control keys with digital / word markings for different functions, landing gear, universal drive devices, differential shafts, 4 rims and tires, shock absorber spring devices, symmetrical tail fins and fixed wings, electric control string-shaped helical blade air ducts, propellers, "towel" shaped integrated support propellers with spaced and overlapping blades up and down, outer end T-shaped long blades, fuselage frames, cockpits, seat cabins, variable frequency motors, variable frequency generators / electric start cycle generators, commutators, transformers, rectifiers, capacitors, resistors, batteries, instruments, multi-functional electronic product integrators, chip components, circuit boards, communication equipment systems, radio devices, avionics equipment, navigation equipment, multiple laser wireless cameras, video devices, multi-frame displays with split screens, instruments, data recorders for multiple different items, memory card black boxes, lidar systems, electric control tilters, fuel tanks / gas cylinders and pipelines, multiple small aviation jet engines and combustion chambers, various parts / components / devices. Among them, the coaxial device includes: the aforementioned engine 1 used, the engine drive shaft rod / tube 2 stands vertically upward for installing the position 3 of the uppermost rotor mechanism, and a striped toothed ring 4 is sleeved at the position below the upper rotor drive shaft rod / tube as the driving toothed ring that rotates synchronously with the drive shaft, for synchronously driving the planetary gears of three / more passive gears / toothed rings distributed circumferentially around it. That is, the driving toothed ring 4 sleeved outside the drive shaft / tube 2 and rotating synchronously with the shaft serves as the central sun gear, and multiple solid gears of various specifications are distributed circumferentially around it after calculating the torques of the upper and lower rotors. These solid gears serve as the passive synchronously rotating planetary gears, and these planetary gears act on the stripes on the inner side wall of the corresponding horizontal position of another drive shaft tube 5 outside its shaft, thereby driving the other drive shaft tube 5 outside its shaft to rotate synchronously in the opposite direction. Outside the drive shaft tube 2, another set of lower rotor devices 6 is sleeved under the top wing of the helicopter. The lengths of the two drive shafts / tubes are different, and the outer rotating tube 5 is shorter than the drive rotating shaft rod / tube 2 at its internal central position. The upper part of the outer shaft tube 5 is installed with a rotor device, and its bottom is inserted and sleeved into a bottom ring disc 7 with a circular hole of a specified size. There are ratchet gears 8, balls and bearings in the concave ring of the disc 7, and the outer shaft tube 5 can rotate and sleeve on the drive shaft / tube 5 in the concave ring ratchet gear 8 of the disc 7. The drive shaft tube 2 passes through the center of the disc and stands vertically upward. The disc is sleeved and fixed above the engine, and the engine is fixed at the position of the inner bottom plate of the casing 9. The drive shaft 2 that rotates vertically upward from the engine is at the center of the outer shaft tube 5 that can rotate in the opposite direction. There are support rods fixed on the circumferential outer side of the inner shaft tube 2 at the center of each rotatable planetary gear, and the bottom of each support rod is fixed and sleeved on the inner circumferential edge of the outer tube bottom disc 7. The lower surface of the disc has support rods fixed on the cabin floor.Alternatively, a support rod supporting and fixing the center of each rotatable planetary gear can be extended downwards through the disk and fixed to the nacelle floor. The entire bottom disk is fixed and does not rotate, while the pawl gear 8, which is installed on its concave inner ring and can be inserted into the outer shaft tube 5, can rotate, forming a coaxial forward and reverse rotation mode for the upper and lower rotors. The engine 1 and drive shaft / tube 2, which are connected to the cockpit control system in automotive mode, operate the two sets of twin rotors on the vertical axis after startup. Another engine 9, located at the tail of the helicopter fuselage, can rotate at the same speed as the aforementioned engine 1. Its universal joint vertical shaft bevel gear connects to the left and right half-shafts of the differential. Propellers 12 and 13 are fitted onto the outer ends / sides of these half-shafts, with the propellers extending beyond the outer sides of the tail fin. Both engines are connected to the cockpit control system in automotive driving mode. They can share the same fuel tank / cylinder or have two separate fuel tanks / cylinders, and can start simultaneously. When the auxiliary power is replaced with a small aircraft jet engine, the same fuel tank / gas cylinder can be shared and connected to the combustion chamber of each jet engine. A thin, electrically controlled / pneumatic lever is longitudinally mounted at the midpoint between the upper surface of the upper rotor blade and the lower surface of the lower rotor. This lever is located within a spring-loaded groove on one side and can be supported and extended horizontally via electronic control. It connects to the cockpit control system and is used for folding the rotor before takeoff and after landing. Specifically, the upper rotor folds its blades upwards, and the lower rotor folds its blades downwards. The helicopter has fixed wings mounted on both sides of the front fuselage. An even number of motor / electric starter generator propellers are symmetrically mounted on the front and ends of each fixed wing, and are electrically connected to the cockpit control system and power battery via wires, enabling assisted forward flight. The propellers at both ends of the fixed wings can be replaced with an even number of small, symmetrically mounted jet engines for lateral flight. An even number of rotatable motor / electric starter generator ducts are symmetrically mounted on the outer side of the fuselage, near the bottom, and on the top / bottom of the fuselage shell. These ducts are electrically connected to the cockpit control system and power battery via wires, and can be controlled via electric buttons to move the helicopter left and right. An even number of motor / electric starter generator ducts 15 and 16, symmetrically mounted on the top / bottom of the fuselage shell, have electrically controlled bases that can rotate longitudinally. These ducts are electrically connected to the cockpit control system and power battery via wires, and are controlled via electric buttons, providing auxiliary power for flight. The wind tunnel is a turbofan / fan generator wind tunnel (application number CN116538020A), or it can be a wind tunnel with a series of blades driven by an electric motor. When used as a swashplate, pressing the marked control keys simultaneously in the cockpit controls the rotating wind tunnel on one side of the top of the fuselage and the rotating wind tunnel on the other side of the bottom of the fuselage, causing the fuselage to tilt to one side for flight and turning. Pressing the control key again returns to level flight. Simultaneously pressing another marked control key controls the rotating wind tunnel on the other side of the top of the fuselage and the rotating wind tunnel on the other side of the bottom of the fuselage, corresponding to the positions of the aforementioned wind tunnels, causing the fuselage to tilt to the other side for flight and turning. Pressing the control key again returns to level flight. Replacing the wind tunnel used as a top and bottom swashplate with a small jet engine, its installation position and number are the same as the wind tunnel, and it is connected to the cockpit control system by wiring. The tilting and turning are controlled by the control keys in the same way as the wind tunnel. It can be used as an auxiliary for forward flight or as a swashplate for left and right movement and turning. Multiple wired / wireless high-magnification laser microphone cameras 19 are installed at any location on the front, top, bottom, sides, or tail of the fuselage, and are connected by wires to the junction box and multi-frame display screen in the cockpit. The electrical signals emitted by the wireless cameras are displayed on the multi-frame display screen in the terminal building to show the helicopter's flight environment and status. The junction box is connected to the black box, which contains multiple radio and camera audio / video data recorder memory cards for recording flight data. The helicopter switches from ground-based to car-based driving mode, consisting of a third car engine 10 and a universal joint drive system. Its technical features include: the car engine 10 is located at the front bottom of the helicopter cockpit; the universal joint drive system is located at the bottom of the lower layer of the fuselage's two-layer floor; the car driveshaft connects to and drives the differentials of the left and right half-shafts of the rear axle; and four shock-absorbing wheels on the front and rear axles replace the helicopter's landing gear. The helicopter cockpit's control system is divided into two parts: the car-based control unit, steering wheel, instruments, multi-function electronic product integrator, and display screen are located on the left, controlling the third engine 10 and the universal joint drive system. The control of the first engine 1 and its vertical driveshaft / tube rotor, the second engine 9 and its tail assembly, instruments, multi-function electronic product integrator, and display screen are located in the middle and on the right. The speed of the fuel / gas engine propeller is controlled by the gear shift lever and the throttle / gas valve. The speed of the electric motor / electric starter generator propeller and blower is electronically controlled by the control buttons. The driver's seat is designed as a sofa, while the passenger seating area is located at the rear of the cockpit. The helicopter pilot operates in both helicopter and car driving modes. In helicopter mode, the vertical folding wings are opened, and then the first and second engines (1, 9) or the first, second, and third engines (1, 9, 11) are started. This causes the propellers mounted on each drive shaft / pipe to rotate synchronously at low speed. The upper and lower rotors on the same axis rotate clockwise and counterclockwise. By increasing the engine throttle / air valve, each propeller is accelerated to high speed and synchronous rotation for ascent. Once a controlled altitude is reached, the pilot can control forward, circling, turning, and hovering flight. After deceleration and landing, the upper and lower rotors are folded up by pressing the control button after the rotors stop rotating. In car driving mode, the operation is the same as driving a car. Based on the design requirements for helicopter use, the heavier automotive driving components can be removed: engine 10, steering wheel, universal joint, shock absorber springs, wheel rims, instruments, and related parts and devices, as well as the control system, while retaining the devices and systems used in helicopter flight mode. Further removal of the fixed wings and front propeller, along with related parts and devices, is also possible, retaining the remaining devices, instruments, and control system. Various instruments, electronic product integrators (application number CN104820658A), terminals, and additional functions can be designed and installed according to the required functions. This technical solution is applicable to helicopter cars and Chinook helicopters. The two drive shafts 2 and 5 of the engine / motor / electric starter cycle engine, along with the technical solution, can be designed and installed on the left and right sides / stern of a ship or boat, with the drive shafts extending outside the hull and a propeller mounted on them for navigation on water. It is distinct from helicopters with a single vertical top wing and a propeller in the middle / on one side of the tail wing, coaxial helicopters, Chinook helicopters, vertical wing helicopter cars, and vertical wing Chinook helicopter cars.

2. According to claim 1, in the coaxial design of two sets of dual rotors operating in the same direction, the planetary gears and support rods are removed. The drive gear ring 4, which rotates with the shaft and is fitted onto the centrally rotating drive shaft / tube 2, drives the longitudinal rack on the inner wall of the second drive shaft tube 5, which is fitted at the same horizontal position, to rotate in the same direction. This, in turn, drives the entire second drive shaft tube 5 connected to its outer sleeve to rotate in the same direction. The lower rotor mounted on the drive shaft tube 5 rotates with the drive shaft tube 5. The device with the disc 7 fitted at the bottom of the rotating shaft tube 5 is the same as described above. The driving control mode is the same as described above.

3. According to claim 1, in addition to the previously described design of two sets of coaxial twin rotors rotating simultaneously in opposite directions and in the same direction, the rotary transmission shaft tube 5 can also have an external gear ring fitted at its bottom, and another fuel / gas engine 11, which can be used as a power device superior to a motor / electric starter cycle generator and can be started synchronously at the same speed, can be installed on its side. The gear on the transmission shaft of the engine 11 drives the external gear ring 14 fitted on the shaft tube 5 to rotate through a meshing / chain type, thereby driving the shaft tube 2 and the lower rotor mounted on it to rotate with the shaft tube. According to the calculated rotational torque data of the upper and lower rotors, when controlling the throttle / gas valves of the two engines 1 and 11, the outer shaft tube 5 and its internal vertical engine transmission shaft tube 2 rotate simultaneously and synchronously at the same speed / and simultaneously and synchronously at different speeds in the same direction. Alternatively, the rotation direction of the engine 11 transmission shaft can be set, with the transmission shaft 2 and the rotary shaft tube 5 rotating in the forward and reverse directions respectively, thereby driving the upper rotor and lower rotor on the two inner and outer shaft tubes to rotate and fly.

4. According to claim 1, the coaxial dual-rotor helicopter is characterized by the following: including all the various parts, components, and avionics used, the preferred engine, coaxial device, and coaxial / vertical dual rotors of the helicopter are designed according to the invention content of the technical solution. Based on the design requirements of the helicopter, the heavier automotive driving components can be removed: engine 10, steering wheel, universal joint, shock absorber spring device, wheel rims, instruments, and related components and devices, and control system, while retaining the devices and systems used in the helicopter's flight mode. Further, the fixed wing and front propeller, as well as related components and devices, are removed, retaining the remaining devices, instruments, and control system. Various instruments and electronic product integrators are designed and installed according to the required functions.

5. The coaxial top-and-bottom rotor helicopter-car according to claim 1, characterized in that: a power unit for a car driving mode is designed and installed based on the content of the coaxial top-and-bottom rotor helicopter. When the helicopter-car switches from ground driving to car driving mode, it consists of a third car engine and a universal joint transmission device installed in the fuselage.

6. According to claim 1, this technical solution is applicable to helicopter cars and Chinook helicopters. The two drive shafts 2 and 5 of the engine / motor / electric starter cycle engine, and the technical solution described herein, can be designed and installed on the left and right sides / stern of a boat or vessel, with the drive shafts extending outside the hull and a propeller mounted on the drive shafts for water navigation.

7. According to claim 1, the engines with drive shafts can be either turboshaft engines or automotive fuel / gas engines, and the engine categories should be as consistent as possible. The variable frequency motor and variable frequency electric starter generator used as power units have a rotor shaft as their electric drive shaft, on which a propeller can be mounted.

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