CN114524089A

CN114524089A - Two sets of coaxial reverse rotation dual-rotor tandem helicopters

Info

Publication number: CN114524089A
Application number: CN202011319155.3A
Authority: CN
Inventors: 罗灿
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-11-23
Filing date: 2020-11-23
Publication date: 2022-05-24

Abstract

The invention relates to two sets of coaxial reverse rotation dual-rotor wing tandem helicopters, which comprise a helicopter body, a power device, a transmission shaft, two sets of coaxial reverse rotation circumferential propellers, two sets of dual rotor wings, two tilting mechanisms, an operation system and the like. The transmission shaft transmits power from the power device to the coaxial reverse rotation circumferential propeller, and the coaxial reverse rotation circumferential propeller transmits power to the double rotors. Two sets of double rotors are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the double rotor paddle disks are upward. The paddle adopts hard paddle, and the rotation direction of the upper rotor of the double rotors is opposite to that of the lower rotor, and the tension of the rotors is adjusted by adjusting the total pitch of the paddle. Two sets of bispin wings can incline to the left side and incline to the right side separately, incline and receive the mechanism control that verts, and the biggest angle that verts uses bispin wings and fuselage not to collide as the limit. And the control system comprises but is not limited to a total distance adjusting mechanism for controlling two tilting mechanisms and two sets of double rotors.

Description

Two sets of coaxial reverse rotation dual-rotor tandem helicopters

Technical Field

The invention relates to a helicopter, in particular to a helicopter which is provided with two sets of coaxial reverse dual rotors in sequence along the longitudinal direction of a helicopter body, and each set of dual rotors can tilt towards the left side and the right side respectively.

Background

The traditional coaxial reverse rotation dual-rotor helicopter is a helicopter provided with a set of coaxial reverse rotation dual rotors. For example, a set of double rotors of the card 52 helicopter are fixed and do not tilt, each blade of the rotor is controlled by an automatic tilter to periodically change distance to generate periodic flapping motion in flight, the cone of the rotor disc is axially inclined in all directions, and the range of the inclination angle is less than 8 degrees. The device is characterized by small maximum yaw steering moment, small maximum rolling moment and poor maneuverability. The heeling and longitudinal-row double-propeller composite helicopter is reported in 11.6.2020 of the inventor, two sets of longitudinal single rotors are arranged, a transmission device adopts a moving shaft driver to transmit power from a transmission shaft to the single rotors, the two sets of single rotors can tilt to the left side and the right side respectively, and the tilting is controlled by a tilting mechanism. The characteristic is that when tilting, the tilting angle range is far more than 8 degrees, and the maximum horizontal component force of the rotor wing pulling force is large; the helicopter has large maximum rolling moment, large maximum yawing and steering moment and good maneuverability, but the moving shaft driver has a complex structure and great weight. In order to make the helicopter have good maneuverability, simplify the structure of a transmission device and reduce the dead weight, the invention provides the following helicopter structure: two sets of coaxial reverse rotation double rotors are arranged in a longitudinal row, a coaxial reverse rotation circumferential propeller is adopted to transmit power to the double rotors from a transmission shaft, the two sets of double rotors can tilt towards the left side and the right side respectively, the tilting is controlled by a tilting mechanism, and the tilting angle is far larger than 8 degrees; the helicopter has large maximum rolling moment, large maximum yawing steering moment and good maneuverability; the coaxial reverse rotation circumferential propeller has simple structure and small dead weight compared with a moving shaft driver.

Disclosure of Invention

The invention relates to two sets of coaxial reverse rotation dual-rotor wing tandem helicopters, which comprise a helicopter body, a power device, a transmission shaft, two sets of coaxial reverse rotation circumferential propellers, two sets of dual rotor wings, two tilting mechanisms, an operation system and the like.

The helicopter body is a mechanical structure for bearing all devices, mechanisms and equipment of the helicopter and adopts a mature technology. The fuselage is generally a longitudinal, streamlined, long cylinder.

The power device is a device for providing power for double rotors and other mechanism equipment, and adopts one, two or three engines, such as a piston engine or a turboshaft engine, which are mature technologies.

The transmission shaft is a machine for transmitting power from a power device to the coaxial reverse rotation circumferential propeller, comprises an input shaft, gear pairs, a speed reducer, two output shafts and the like, and adopts a mature technology. The input shaft is connected with a power device, and each output shaft is connected with a set of coaxial reverse rotation circumferential propellers.

The coaxial counter-rotating circumferential propeller is a transmission machine which transmits power from a transmission shaft to the double rotors. The invention relates to a coaxial reverse rotation circumferential propeller, which is declared in 2019, 4 and 7 months, and belongs to a mature technology. Each set of coaxial reverse rotation circumferential propeller comprises an input end, a single-way reverser, a double-way deflector, a steering support and two output ends. The input end is connected with the transmission shaft; the two output ends are an inner output end and an outer output end which are respectively connected with the double rotors; two output ends, the double rotors and the like can revolve around the axis of the input end under the control of the tilting mechanism, and the revolution angle range can be 360 degrees.

The two sets of double rotors are divided into a front double rotor and a rear double rotor, and are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the double rotor paddle disk is upward. Referring to fig. 1 and 2, in the two drawings, (2) is a front double-rotor, and (5) is a rear double-rotor. Each set of double rotors comprises a double-rotor shaft, a double-propeller hub, blades, a total distance adjusting mechanism and the like, and mature technology is adopted. The double-rotor shaft is a sleeve shaft, a mature technology is adopted, an inner shaft and an outer shaft of the sleeve shaft are respectively connected with an inner output end and an outer output end of the coaxial reverse rotation circumferential propeller, and the rotation directions of the upper rotor and the lower rotor of each set of double rotors are opposite. The double-propeller hub adopts a mature technology and is respectively connected with an inner shaft and an outer shaft of the double-rotor shaft. The paddle adopts a hard paddle, which is a mature technology. The collective pitch adjusting mechanism adopts a mature technology and adjusts the tension of the double rotors by adjusting the collective pitch of the blades. The distance between the two sets of double-rotor shafts is larger than the sum of the rotor radii of the two sets of double-rotor shafts, so that the two sets of double rotors cannot collide. For the fuselage, two sets of bispin wings can incline to left side and incline to the right side respectively, incline to incline and incline the mechanism control that inclines. Tilting means that two output ends and double rotors revolve around the axis of the input end of the coaxial reverse rotation circumferential propeller. The range of the tilting angle is larger than 8 degrees towards the left side and the right side respectively, and is generally not smaller than 20 degrees, and the maximum tilting angle is limited by the fact that the double rotors do not collide with the airframe.

The two tilting mechanisms are mechanisms for respectively controlling two sets of dual rotors to tilt, and mature technologies such as hydraulic control mechanisms or electric control mechanisms are adopted. Each tilt mechanism includes a base and a moving portion. The base is connected to the body, and the moving portion is connected to a member to be controlled as a tilting object.

The control system controls the action of the helicopter by adopting a mature technology. Including but not limited to, a collective pitch mechanism that controls two tilt mechanisms and controls two sets of dual rotors.

The invention discloses two sets of coaxial reverse rotation dual-rotor wing tandem helicopters, which are the same as the roll tandem dual-rotor wing compound helicopter: two sets of rotors in the longitudinal rows of the two rotors are controlled by the tilting mechanisms, the axes of the two sets of rotors can tilt towards the left side and the right side respectively, and the tilting angle range is limited to the condition that the rotors do not collide with the airframe; the range of the tilting angle is large, the maximum horizontal component force of the rotor wing pulling force is large, and the maximum rolling torque and the maximum yawing steering torque of the helicopter are large. Compared with the prior helicopter, no matter a single rotor wing or a double rotor wing is adopted, the inclination angle range of the cone shaft of the rotor wing is small, the maximum horizontal component of the pulling force of the rotor wing is small, and the maximum rolling moment and the maximum yawing steering moment of the helicopter are small. Referring to fig. 5, the drag of the dual rotors of the present invention is shown as (1) when they tilt, the drag of the dual rotors of the present invention is shown as (4) when the conventional rotor disk tilts, and the tilt angle of the dual rotors is larger than the tilt angle of the conventional rotor disk. When the vertical component (2) of the rotor wing pulling force when the double rotor wings tilt is equal to the vertical component (5) of the rotor wing pulling force when the traditional rotor wing paddle disk tilts, the horizontal component (3) of the tilting rotor wing pulling force is far larger than the horizontal component (6) of the paddle disk tilting rotor wing pulling force.

The difference between the two is as follows: 1, the invention adopts two sets of double rotors instead of two sets of single rotors. 2, the coaxial reverse rotation circumferential propeller is used for transmitting power from the transmission shaft to the double rotors instead of transmitting power from the transmission shaft to the single rotors through the transmission shaft.

The direct connection of the present invention is a well-established technique of equalizing the rotational speeds of objects to be connected by a connection machine, for example, equalizing the rotational speeds of the objects to be connected by gluing, bolting, riveting, mechanical engagement, coupling, or the like. Indirect coupling is a well-established technique for mechanically correlating the rotational speed determinations of the coupled objects. The connections described herein are generally referred to as direct connections. The transmission shaft, the gear pair and the speed reducer are mature technologies. The revolution is that components such as a shaft and a rotor rotate around other axes, and the rotation is that the components such as the shaft and the rotor rotate around the axes. The hard blade is not provided with a flapping movement device, is an air propeller blade, is not matched with an automatic inclinator, and is a mature technology. The paddle disk refers to a flat cone disk formed by micro-deformation of the paddle due to the pulling force of the rotor when the rotor rotates, and the paddle disk cone shaft of the traditional flexible paddle rotor or the traditional rigid paddle rotor can be controlled by an automatic inclinator to incline.

The invention relates to a technology for arranging two sets of tandem double rotors and coaxial reverse rotation circumferential propellers on a helicopter, which is in parallel relation with the helicopter propulsion technology. That is, the present invention may be combined with various propulsion technologies of helicopters, with tail rotor propulsion, with front rotor propulsion, with side rotor propulsion, with jet propulsion, or with no propulsion.

The action of the helicopter of the invention is as follows: when the two sets of double rotors do not tilt and the tension of the rotors is synchronously adjusted, the helicopter rises, falls or hovers. When the two sets of double rotors do not tilt and the tension of the rotors is asynchronously adjusted, the helicopter tilts or faces upward, the helicopter can horizontally fly forwards on the basis of the tilting action, and the helicopter can horizontally fly backwards on the basis of the facing-upward action. When the two sets of double rotors synchronously adjust and increase the rotor tension and respectively tilt to different sides, the helicopter turns in a yaw mode. When two sets of double rotor wings increase rotor wing pulling force and incline to the same side in step, the helicopter rolls, and the helicopter can be to side horizontal flight on the basis of the action of rolling. These actions can be deduced from public knowledge.

The two sets of coaxial reverse rotation dual-rotor tandem helicopters have the advantages that: the helicopter is provided with two sets of coaxial reverse dual rotors in a longitudinal arrangement, power is transmitted to the dual rotors from a transmission shaft through a coaxial reverse circumferential propeller, the two sets of dual rotors can be controlled by a tilting mechanism to tilt to the left side and the right side respectively, and the maximum tilting angle is limited by the fact that the rotors do not collide with a fuselage. The structures enable the maximum rolling torque and the maximum steering torque of the helicopter to be far greater than those of a traditional helicopter, and the maneuverability is good; the coaxial reverse rotation circumferential propeller has simple structure and small self weight. And the transmission characteristic of the coaxial reverse rotation circumferential propeller enables the tilting mechanism to be stressed very little, and the tilting mechanism can be simplified.

Drawings

Fig. 1 is a schematic side view of embodiment 1 of the present invention. In the figure, 1 is a front double-rotor shaft, 2 is a front double-rotor, 3 is a power device, 4 is a rear double-rotor shaft, 5 is a rear double-rotor, and 6 is a fuselage.

Fig. 2 is a schematic top view of embodiment 1 of the present invention. In the figure, 1 is a front double-rotor shaft, 2 is a front double-rotor, 3 is a power device, 4 is a rear double-rotor shaft, 5 is a rear double-rotor, and 6 is a fuselage.

Fig. 3 is a schematic front view of embodiment 1 of the present invention. In the figure, 1 is a front double-rotor shaft, 2 is a front double-rotor, 3 is a power device, 4 is an angle range of the front double-rotor tilting to the left side and the right side, and 5 is a fuselage.

Fig. 4 is a schematic view of a coaxial counter-rotating circumferential thruster. In the figure, 1 is an input end, 2 is a coaxial bearing, 3 is a coaxial shaft, 4 is a coaxial reversing sleeve shaft, 5 is a first driving bevel gear, 6 is a second driving bevel gear, 7 is a first driven bevel gear, 8 is a second driven bevel gear, 9 is a fixed shaft bearing, 10 is a moving shaft bearing, 11 is a steering support, 12 is an output sleeve shaft, 13 is an inner output end, 14 is an outer output end, 15 is a front bevel gear, 16 is a reversing bevel gear, 17 is a rear bevel gear, 18 is a worm gear, and 19 is a worm.

In the above drawings, the respective components are only schematic in relation to each other, and do not reflect actual shapes and dimensions.

Fig. 5 is a schematic diagram showing the comparison between the rotor tension when the dual rotors tilt and the rotor tension when the conventional rotor disc tilts according to the present invention, in which 1 is the rotor tension when the dual rotors tilt according to the present invention, 2 is the vertical component of the tilt rotor tension, 3 is the horizontal component of the tilt rotor tension, 4 is the rotor tension when the conventional rotor disc tilts, 5 is the vertical component of the rotor tension when the rotor disc tilts, and 6 is the horizontal component of the rotor tension when the rotor disc tilts.

Detailed Description

Example 1: the embodiment 1 of the invention provides two sets of coaxial reverse rotation dual-rotor tandem helicopters, which comprise a helicopter body, a power device, a transmission shaft, two sets of coaxial reverse rotation circumferential propellers, two sets of dual rotors, two tilting mechanisms, an operation system and the like. See fig. 1, 2, 3.

The fuselage is a longitudinal streamline long cylinder.

The power plant adopts a mature technology. This embodiment employs two turboshaft engines.

The transmission shaft comprises an input shaft, gear pairs, a speed reducer, two output shafts and the like, and adopts a mature technology. The input shaft is connected with a power device, and each output shaft is connected with the input end of a set of coaxial reverse rotation circumferential propellers.

The coaxial reverse rotation circumferential propeller transmits power from a transmission shaft to the double rotors, and belongs to the mature technology. Each set of coaxial reverse rotation circumferential thrusters comprises an input end, a one-way reverser, a two-way deflector, a steering support and two output ends, see fig. 4. The input end (1) inputs power from the transmission shaft, and the rear part of the input end is connected with a homodromous shaft (3). The one-way reverser comprises a coaxial shaft (3), a front bevel gear (15), a reversing bevel gear (16), a reversing bevel gear support, a rear bevel gear (17) and a coaxial reversing sleeve shaft (4). Fixing a same-direction shaft bearing, and arranging a front bevel gear (15) on the same-direction shaft (3); a reversing bevel gear (16) fixed on a support thereof is meshed with the front bevel gear (15), and the axis of the reversing bevel gear is vertical to the axis of the coaxial shaft. The coaxial reversing shaft is fixed through a bearing, the coaxial reversing sleeve shaft (4) and the coaxial shaft (3) are positioned on the same axis, and a rear bevel gear (17) is arranged on the outer shaft of the coaxial reversing sleeve shaft and meshed with a reversing bevel gear (16). The coaxial shaft (3) is directly connected with the inner shaft of the coaxial reverse sleeve shaft, and the front bevel gear (15) and the rear bevel gear (17) form indirect connection through a reversing bevel gear (16). Making the transmission ratio of this indirect connection equal to-1.0, take: the tooth number of the front bevel gear is equal to that of the reversing bevel gear and is equal to that of the rear bevel gear, which is equal to 17. The inner and outer shafts of the coaxial reversing quill rotate at equal speeds in opposite directions. The two-way deflector comprises a first driving bevel gear (5), a second driving bevel gear (6), a first driven bevel gear (7), a second driven bevel gear (8) and an output sleeve shaft (12). The first drive bevel gear (5) is directly connected with the inner shaft of the coaxial reversing sleeve shaft, and the second drive bevel gear (6) is directly connected with the outer shaft of the coaxial reversing sleeve shaft; a first driven bevel gear (7) is arranged on the inner shaft of the output sleeve shaft, and a second driven bevel gear (8) is arranged on the outer shaft of the output sleeve shaft; the first driven bevel gear (7) and the inner shaft of the output sleeve shaft are directly connected with the inner output end (13), and the second driven bevel gear (8) and the outer shaft of the output sleeve shaft are directly connected with the outer output end (14). The axial line of the output sleeve shaft and the axial line of the coaxial reverse sleeve shaft form an included angle in the same plane, the included angle is a folding angle, and the folding angle is 90 degrees in the embodiment; keeping the first driving bevel gear (5) meshed with the first driven bevel gear (7), and keeping the second driving bevel gear (6) meshed with the second driven bevel gear (8). The transmission ratio from the inner shaft of the coaxial reverse sleeve shaft to the inner shaft of the output sleeve shaft is equal to the transmission ratio from the outer shaft of the coaxial reverse sleeve shaft to the outer shaft of the output sleeve shaft, and the following steps are carried out: the first driving bevel gear tooth number is 17, the first driven bevel gear tooth number is 19, and the second driving bevel gear tooth number is 19. The steering support comprises a dead axle bearing (9), a steering support (11), a moving axle bearing (10), a worm wheel (18) and a worm (19). Coaxial reversal quill is also called the dead axle, sets up dead axle bearing (9) bearing coaxial reversal quill outside coaxial reversal quill (4), sets up axis bearing (10) bearing output quill outside output quill (12), with steering bracket (11) lug connection dead axle bearing (9) and moving axis bearing (10), makes whole steering support can have enough to meet the need around the dead axle axis. A worm wheel (18) is arranged on the dead axle bearing (9), the worm wheel (18) and the dead axle bearing (9) keep synchronous, and a matched worm (19) is arranged to be meshed with the worm wheel (18) to form a worm and gear mechanism; the number of the worm heads is 2, the number of the worm gear teeth is 30, and the transmission ratio of the worm gear mechanism is 15. The worm (19) is connected with the tilting mechanism. The two output ends are an inner output end (13) and an outer output end (14), and the two output ends are respectively connected with the double rotors. Two output ends, double rotors and the like controlled by the tilting mechanism can revolve around the axis of the input end, and the revolution angle range can be 360 degrees.

The two sets of double rotors comprise a front double rotor and a rear double rotor, and are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the double rotor paddle disk is upward. Each set of double rotors comprises a double rotor shaft, a double propeller hub, blades, a total distance adjusting mechanism and the like. The double-rotor shaft is a sleeve shaft, and an inner shaft and an outer shaft of the sleeve shaft are respectively connected with an inner output end and an outer output end of the coaxial reverse rotation circumferential propeller by adopting a mature technology. The rotation direction of the upper rotor wing and the lower rotor wing of each set of double rotor wings is opposite. The double-propeller hub adopts a mature technology and is respectively connected with an inner shaft and an outer shaft of the double-rotor shaft. The paddle adopts a hard paddle, which is a mature technology. The collective pitch adjusting mechanism adopts a mature technology and adjusts the tension of the double rotors by adjusting the collective pitch of the blades. The distance between the two sets of double-rotor shafts is larger than the sum of the rotor radii of the two sets of double-rotor shafts, so that the two sets of double rotors cannot collide. For the fuselage, two sets of bispin wings can incline to left side and incline to the right side respectively, incline to incline and incline the mechanism control that inclines. The tilt angle ranges in the present embodiment are 23 degrees to the left and to the right. For avoiding the dual rotor wing to incline when inclining and the fuselage collision, can set up the angle scope stopper that inclines, this is mature technique.

Two tilting mechanisms respectively control two sets of dual rotors to tilt, and an electric control mechanism is adopted, so that the dual-rotor type wind turbine is a mature technology. Each tilt mechanism includes a base and a moving portion. The base is connected to the body, and the moving portion is connected to a member to be controlled as a tilting object. Referring to fig. 4, the tilting mechanism moving part of the present embodiment is connected with a worm (19) of a coaxial counter-rotating circumferential thruster. Other mature forms of connection between the tilt mechanism of the present invention and the part to be controlled as to tilt are also contemplated.

The control system controls the action of the helicopter and adopts a mature technology. Including but not limited to, a collective pitch mechanism that controls two tilt mechanisms and controls two sets of dual rotors.

The action of the helicopter of the embodiment is as follows: when the two sets of double rotors do not tilt and the tension of the rotors is synchronously adjusted, the helicopter rises, falls or hovers. When the two sets of double rotors do not tilt and the tension of the rotors is asynchronously adjusted, the helicopter tilts or faces upward, the helicopter can horizontally fly forwards on the basis of the tilting action, and the helicopter can horizontally fly backwards on the basis of the facing-upward action. When the two sets of double rotors synchronously adjust and increase the rotor tension and respectively tilt to different sides, the helicopter turns in a yaw mode. When the two sets of double rotors synchronously adjust and increase the rotor tension and incline to the same side, the helicopter rolls, and the helicopter can horizontally fly to the side on the basis of the rolling action.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents.

Claims

1. The invention relates to two sets of coaxial reverse rotation dual-rotor wing tandem helicopters, which comprise a helicopter body, a power device, a transmission shaft, two sets of coaxial reverse rotation circumferential propellers, two sets of dual rotor wings, two tilting mechanisms, an operation system and the like:

the helicopter body is a mechanical structure for bearing all devices, mechanisms and equipment of the helicopter;

the power device is a device for providing power for the double rotors and other mechanism equipment;

the transmission shaft is a machine for transmitting power from the power device to the coaxial reverse circumferential propellers, and comprises an input shaft, gear pairs, a speed reducer, two output shafts and the like, wherein the input shaft is connected with the power device, and each output shaft is connected with one set of coaxial reverse circumferential propellers;

the coaxial reverse rotation circumferential propellers are transmission machinery for transmitting power from a transmission shaft to the double rotors, each set of coaxial reverse rotation circumferential propeller comprises an input end, a one-way commutator, a two-way deflector, a steering support and two output ends, the input end is connected with the transmission shaft, the two output ends are an inner output end and an outer output end which are respectively connected with the double rotors, and the two output ends, the double rotors and the like can revolve around the axis of the input end under the control of a tilting mechanism;

two sets of double-rotor include preceding double-rotor and back double-rotor, set up in fuselage upper portion behind one in the front of the fuselage longitudinal axis, the double-rotor oar dish is upwards, and every set of double-rotor includes double-rotor axle, two propeller hubs, paddle and total distance adjusting mechanism etc. the double-rotor axle is the quill, and the interior output end and the outer output end of this quill and coaxial reversal circumference propeller are connected respectively, and the rotation direction of the upper rotor of every set of double-rotor is opposite with lower floor's rotor. The double-rotor hub is respectively connected with an inner shaft and an outer shaft of the double-rotor shaft, the blades are hard blades, the total distance adjusting mechanism adjusts the tension of the double rotors by adjusting the total distance of the blades, the distance between the two sets of double-rotor shafts is greater than the sum of the radii of the rotors, the two sets of double rotors can tilt towards the left side and the right side respectively, the tilting is controlled by the tilting mechanism, the tilting angle range is greater than 8 degrees towards the left side and the right side respectively, and the maximum tilting angle is limited by the fact that the double rotors do not collide with the fuselage;

the two tilting mechanisms are mechanisms for respectively controlling two sets of dual rotors to tilt, each tilting mechanism comprises a base and a moving part, the base is connected with the aircraft body, and the moving part is connected with a part of a controlled tilting object;

the control system controls the actions of the helicopter, including but not limited to controlling two tilting mechanisms and controlling a total distance adjusting mechanism of two sets of double rotors.