CN111572763A - Side-tipping longitudinal-row double-propeller composite helicopter - Google Patents
Side-tipping longitudinal-row double-propeller composite helicopter Download PDFInfo
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- CN111572763A CN111572763A CN202010528339.4A CN202010528339A CN111572763A CN 111572763 A CN111572763 A CN 111572763A CN 202010528339 A CN202010528339 A CN 202010528339A CN 111572763 A CN111572763 A CN 111572763A
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- 239000002131 composite material Substances 0.000 title claims abstract description 11
- 230000007246 mechanism Effects 0.000 claims abstract description 85
- 230000005540 biological transmission Effects 0.000 claims abstract description 48
- 238000005516 engineering process Methods 0.000 claims description 23
- 239000003638 chemical reducing agent Substances 0.000 claims description 18
- 150000001875 compounds Chemical class 0.000 claims 2
- 239000011295 pitch Substances 0.000 description 27
- 238000005096 rolling process Methods 0.000 description 21
- 230000009471 action Effects 0.000 description 12
- 238000010586 diagram Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000000737 periodic effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
Abstract
The invention relates to a side-tipping longitudinal double-propeller composite helicopter which comprises a helicopter body, a power device, a transmission device, two pairs of top propeller rotors, two tilting mechanisms, a transmission mechanism, a propelling propeller, an operation system and the like. A moving shaft driver is arranged in the transmission device; the two pairs of top propeller rotors are arranged on the upper part of the fuselage along the longitudinal axis of the fuselage, the propeller blades of the two pairs of top propeller rotors are hard blades, the rotating directions of the two pairs of top propeller rotors are opposite, the distance between two rotor shafts is greater than the radius of the top propeller rotors, the tension of the rotors is adjusted by adjusting the total pitch of the propeller blades, the two pairs of top propeller rotors can tilt towards the left side and the right side respectively, and the tilting is controlled by a tilting mechanism; the propulsion paddle generates forward and backward propulsion force to the machine body; the control system controls five sets of mechanisms, namely a front top propeller rotor total distance adjusting mechanism, a front top propeller rotor tilting mechanism, a rear top propeller rotor total distance adjusting mechanism, a rear top propeller rotor tilting mechanism and a propulsion propeller total distance adjusting mechanism.
Description
Technical Field
The invention relates to a helicopter, in particular to a helicopter which is provided with two pairs of hard blade top propeller rotors arranged in sequence along the longitudinal axis of a helicopter body, wherein each pair of top propeller rotors can tilt towards the left side and the right side and are provided with propelling propellers.
Background
The traditional tandem double-rotor helicopter is a helicopter with two pairs of non-coaxial contrarotating rotors arranged along the longitudinal direction of a fuselage, such as a Canon helicopter. The two pairs of rotors adopt flexible blades or rigid blades. The axis of the rotor shaft is fixed, each blade is controlled by the automatic tilter to periodically change the distance to generate periodic flapping motion when rotating in flight, the inclination of each side of the rotor disc cone in the axial direction is formed, and the inclination angle is smaller than 8 degrees. Therefore, the maximum horizontal component of the pulling force of the rotor wing is small, and the maximum rolling torque and the maximum steering torque of the helicopter are not large enough. And the conventional helicopter is not provided with a propulsion paddle. In order to increase the maximum rolling moment, the maximum steering moment and the lifting mobility of the helicopter and improve the forward and backward flying speed of the helicopter. The invention provides the following helicopter structure: the two pairs of top propeller rotors adopt hard blades. The rear section of the transmission device adopts a moving shaft driver to transmit power to the rotor shaft. Two pairs of top oar rotors can incline to the left side and to the right side respectively around a longitudinal axis, incline to incline and receive the mechanism control that inclines. The tilting angle range is not less than 20 degrees and not more than 70 degrees. Therefore, the maximum horizontal component of the rotor wing pulling force is large, and the maximum rolling moment and the maximum steering moment of the helicopter are large. And the propelling propeller is arranged to push the helicopter to fly forwards and backwards, so that the flying speed is improved.
Disclosure of Invention
The invention relates to a side-tipping longitudinal double-propeller composite helicopter which comprises a helicopter body, a power device, a transmission device, two pairs of top propeller rotors, a tilting mechanism, a transmission mechanism, a propelling propeller, 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 longitudinally long cylindrical streamline.
The power device is a device for providing power for the top propeller rotor wing, the propulsion propeller and other equipment, and adopts mature technology. Such as a piston engine or a turboshaft engine.
The transmission device is a machine for transmitting power to the top propeller rotor wing, comprises an input shaft, transmission shafts, gear pairs, a speed reducer, a movable shaft driver and the like, and adopts a mature technology. The transmission device takes the approach power device as a front section and takes the approach rotor shaft as a rear section. The input shaft in the front section is connected with a power device. Each transmission shaft, each gear pair and the speed reducer are all machines which transmit the fixed shaft to other fixed shafts. In order to enable the rotor shaft to tilt, a moving shaft driver is arranged in the rear section, and the moving shaft driver is a machine for transmitting the rotating shaft from the fixed shaft. The rotor shaft is a revolution shaft, and the revolution is tilting. The moving shaft drivers are three types, namely a bevel gear pair, a hundred-direction driver and a double-folded circumferential driver. There are three types of structures from the moving shaft driver to the rotor shaft. The first form: the transmission device of the moving shaft adopts a bevel gear pair, the bevel gear pair is arranged, the axis of an input shaft of the bevel gear pair is parallel to the longitudinal axis of the machine body, power is connected to the input shaft of the bevel gear pair through the front section of the transmission device, an output shaft of the bevel gear pair is connected with an input shaft of the speed reducer, and an output shaft of the speed reducer is connected with a rotor shaft; the output shaft of the bevel gear pair, the reducer and the rotor shaft can be controlled to revolve around the input shaft axis of the bevel gear pair. The second form: the moving shaft driver adopts a hundred-direction driver, the hundred-direction driver is arranged, the axis of the inner input end of a clutch in the hundred-direction driver is parallel to the longitudinal axis of the machine body, power is accessed into the input end of the hundred-direction driver through the front section of the driver, and the output end shaft of the hundred-direction driver is connected with the rotor shaft; both the output shaft and the rotor shaft of the hundred-direction driver can be controlled to revolve around the inner input shaft axis of the clutch in the hundred-direction driver. The third form: the driving shaft driver adopts a double-folded circumferential driver, the double-folded circumferential driver is arranged, the axis of a reverse sleeve shaft in the double-folded circumferential driver is parallel to the longitudinal axis of the aircraft body, power is accessed to an input shaft of the double-folded circumferential driver through the front section of the driving device, and an output shaft of the double-folded circumferential driver is connected with the rotor shaft; both the output shaft and the rotor shaft of the bi-fold circumferential transmission can be controlled to revolve around a reversing sleeve shaft axis in the bi-fold circumferential transmission.
The two pairs of top propeller rotors are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the propeller discs of the top propeller rotors face upwards. The top propeller rotor comprises a rotor shaft, a hub, each propeller blade, a total distance adjusting mechanism and the like, and adopts a mature technology. Wherein the propeller blades are hard blades without flapping motion. The rotation directions of the two pairs of top propeller rotors are opposite. The distance between the two rotor shafts is larger than the radius of the top propeller rotor. The top propeller rotor adjusts the propeller blade collective pitch through the collective pitch adjusting mechanism to adjust the rotor tension, and the adjustment adopts a mature technology. The two pairs of top propeller rotors can tilt towards the left side and the right side respectively. The tilting is controlled by a tilting mechanism and adopts a mature technology. Tilting is the rotation of the rotor shaft, hub and propeller blades around the rotor shaft axis while they are also controlled to revolve around a longitudinal axis. The tilting angle ranges are not less than 10 degrees respectively in the left direction and the right direction, and are not less than 20 degrees in total; the left and right are not more than 35 degrees respectively, and the total is not more than 70 degrees.
The two tilting mechanisms are mechanisms for respectively controlling the two pairs of top propeller 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 with the body, and the moving part is connected with the part to be tilted. The control of the tilting adopts a mature technology.
The transmission mechanism is a machine for transmitting power to the propulsion paddle and adopts a mature technology.
The propeller is a propeller which can generate forward and backward propelling force to the airframe, the propeller comprises a propeller shaft, a propeller hub, blades, a total distance adjusting mechanism and the like, and the mature technology is adopted. The propulsion paddle adjusts the total pitch of the blades through the total pitch adjusting mechanism to adjust the propulsion force, and the adjustment adopts a mature technology. The number of the propelling paddles is one, two or more, and the propelling paddles are arranged at the head part of the machine body, the tail part of the machine body or the side part of the machine body. The propeller shaft axis is parallel to the longitudinal axis of the fuselage.
The control system adopts a mature technology to control five sets of mechanisms, namely a front top propeller rotor pitch adjusting mechanism, a front top propeller rotor tilting mechanism, a rear top propeller rotor pitch adjusting mechanism, a rear top propeller rotor tilting mechanism and a propulsion propeller pitch adjusting mechanism. The five sets of mechanisms controlled by the control system are simpler than the six sets of mechanisms controlled by the traditional control system of the tandem double-propeller helicopter.
The side-tipping tandem double-propeller composite helicopter of the invention is different from the traditional tandem double-propeller helicopter: 1, the propeller blade of the top propeller rotor adopts a hard blade without flapping motion. The traditional helicopter rotor adopts flexible blades or rigid blades, and the blades are provided with flapping motion. And 2, the tilting of the two pairs of top propeller rotors is controlled by a tilting mechanism and can tilt to the left side and the right side respectively. The rotary axis and the hub rotating axis of the rotor of the traditional helicopter are unchanged, the rotary axis and the hub do not revolve while rotating, and the blades are controlled by the automatic inclinator to periodically change distance to generate periodic flapping motion when rotating in flight, so that the inclination of each direction of the axial direction of the rotor disc cone is formed. The helicopter has the advantages that the tilting angle range of the two pairs of top propeller rotors is large, the maximum horizontal component force of the pulling force of the rotors is large, and the maximum rolling torque and the maximum steering torque are large. The traditional helicopter rotor disc cone shaft has small inclination angle range, small maximum horizontal component force of rotor wing pulling force, small maximum rolling torque and small maximum steering torque. Referring to fig. 2, the top paddle rotor of the present invention tilts compared to conventional rotors with the same vertical component of rotor pull. In the figure, the maximum horizontal component of the rotor pulling force resulting from the tilting of the top-paddle rotor of the present invention is significantly greater than the maximum horizontal component of the rotor pulling force resulting from the tilting of a conventional rotor. 3, the propulsion propellers are firstly provided and arranged in the tandem double-propeller helicopter, when the propulsion propellers work, the advancing blades of the two pairs of top propeller rotors respectively provide lift force for the helicopter to form rolling torque which is mutually offset and balanced, so that the helicopter can fly at high speed with balanced rolling torque.
The connection is a well-established technique in which the rotational speeds of objects to be connected are equalized by a connection machine, for example, by cementing, bolting, riveting, mechanical engagement, coupling, or the like. The transmission shaft, the gear pair, the speed reducer, the bevel gear pair and the double-folded circumferential driver are mature technologies. The hundred-direction driver comprises three types, namely a same-direction transfer hundred-direction driver, a same-direction transfer double-control hundred-direction driver and a double-flow hundred-direction driver, and the three types are similar in structure and function and are mature technologies. The revolution shaft is a shaft which can rotate and revolve, such as a moving shaft driver output shaft, a rotor wing shaft and the like. The paddle provided with the flapping motion comprises a flexible paddle provided with a flapping hinge and a rigid paddle utilizing the elastic flapping motion of a paddle material, and the flexible paddle and the rigid paddle are matched with an automatic tilter and are controlled by the automatic tilter to periodically change distances to generate periodic flapping motion, so that the flapping motion is mature technology. The hard blade without flapping, namely the air propeller blade, is not matched with the automatic inclinator, and is a mature technology. The propulsion propeller comprises a plurality of propellers, ducted propellers and the like, wherein the ducted propellers can adjust the direction of airflow by adjusting the ducted louvers, and the technology is mature. The paddle disc is a cone-shaped disc formed by the rotation of the rotor wing.
The flight action of the helicopter is as follows: when the propulsion propeller does not rotate or the total pitch of the blades of the propulsion propeller is zero, the effect is equal to that the propulsion propeller is not arranged, and the helicopter can realize various flight actions by controlling the two pairs of top propeller rotors. When the two pairs of top propeller rotors do not tilt and the tension of the rotors is synchronously adjusted, the helicopter is lifted. When the two pairs of top propeller rotors do not tilt and the tension of the rotors is asynchronously adjusted, the helicopter pitches, and the helicopter can horizontally fly forwards and backwards on the basis of pitching action. When the two pairs of top propeller rotors synchronously adjust and increase the rotor tension and respectively incline and rotate towards different directions, the helicopter turns. When the two pairs of top propeller rotors synchronously adjust the tension of the rotors and tilt in the same direction, the helicopter rolls, and the helicopter can horizontally fly leftwards and rightwards on the basis of the rolling action. When the propelling propeller rotates and the total pitch of the blades of the propelling propeller is not zero, the two pairs of top propeller rotors do not tilt, forward blades of the two pairs of top propeller rotors respectively provide lift force for the helicopter to form rolling torque which is mutually offset and balanced, and the helicopter flies forwards and backwards horizontally at high speed under the pushing of the propelling propeller. Various actions may be superimposed.
The side-tipping and longitudinal-row double-propeller composite helicopter has the advantages that: in the tandem double-propeller helicopter, hard blades are firstly provided for top propeller rotors, three types of structures between a movable shaft driver and a rotor shaft are provided, two pairs of top propeller rotors can tilt towards the left side and the right side respectively, and the tilting is controlled by a tilting mechanism. The structural measures enable the maximum rolling moment and the maximum steering moment of the helicopter to be far larger than those of a traditional tandem double-rotor helicopter, and the maneuverability is particularly outstanding. In the tandem double-propeller helicopter, firstly, the propelling propellers are arranged and matched with two pairs of top propeller rotors with opposite rotating directions, so that the helicopter can fly at high speed in a rolling moment balance manner. Only tilt-rotor aircraft have used tilt-rotor technology in proprotor aircraft before, and aircraft and helicopter are two different aircrafts which have different structures and are completely different in operation and control.
Drawings
Fig. 1 is a schematic layout diagram of embodiments 1 and 2 of the present invention. In the figure, 1 is a fuselage, 2 is a rotor shaft of a front top propeller rotor, 3 is a rotor shaft of a rear top propeller rotor, and 4 is a propelling propeller.
Fig. 2 is a schematic diagram comparing top-paddle rotor tilt with conventional rotor-disk cone-axis tilt, where fig. 1 shows the rotor drag resulting from top-paddle rotor tilt of the present invention, with a large horizontal component; 2 is the rotor pulling force that traditional rotor oar dish cone axle slope formed, and its horizontal component is little.
Fig. 3 is a schematic view of a tilt angle range of a top propeller rotor in embodiment 1 of the present invention, where 1 is a longitudinal axis in a fuselage, 2 is a hundred-direction actuator, 3 is a rotor shaft, 4 is a maximum tilt angle of a left side of the rotor shaft, 5 is a maximum tilt angle of a right side of the rotor shaft, and 6 is a tilt angle range of 46 degrees.
Fig. 4 is a schematic diagram of a half-width structure of a equidirectional transfer-case hundred-direction transmission adopted in embodiment 1 of the present invention, in which fig. 1 is an input end of a equidirectional transfer case and is also an input end of a hundred-direction transmission, 2 is an internal output end of the equidirectional transfer case, 3 is an external output end of the equidirectional transfer case, 4 is a commutator, 5 is an external input end of a clutch, 6 is an internal input end of the clutch, 7 is a turnover control end, 8 is an output end of the clutch, and is also an output end of the hundred-direction transmission and is also an output end. In the figure, a transfer case and a clutch in the same direction both adopt bevel gear planet rows, and a commutator adopts a bevel gear planet row commutator; the characteristic parameters of the three bevel gear planet rows are all 1.0.
Fig. 5 is a schematic view of a tilt angle range of a top propeller rotor wing according to embodiment 2 of the present invention, in which fig. 1 is a longitudinal axis in a fuselage, 2 is a bevel gear pair, 3 is a speed reducer, 4 is a rotor shaft, 5 is a maximum angle at which the rotor shaft tilts to the left, 6 is a maximum angle at which the rotor shaft tilts to the right, and 7 is a tilt angle range of 60 degrees.
The components in the drawings are only schematic in relation to each other, and do not reflect actual shapes and dimensions.
Detailed Description
Example 1: the invention embodiment 1 discloses a side-tipping and longitudinal-column double-propeller composite helicopter which comprises a helicopter body, a power device, a transmission device, two pairs of top propeller rotors, two tilting mechanisms, a transmission mechanism, a propelling propeller, an operation system and the like. The moving shaft driver adopts a unidirectional transmission with equidirectional transfer. The layout of the embodiment is shown in fig. 1.
The fuselage is a longitudinal long cylindrical streamline.
The power device adopts a turboshaft engine.
The transmission device comprises an input shaft, transmission shafts, gear pairs, a speed reducer, a movable shaft driver and the like, and transmits power to the top propeller rotor wing. The transmission device takes the approach power device as a front section and takes the approach rotor shaft as a rear section. The input shaft in the front section is connected with a power device. Each transmission shaft, each gear pair and the speed reducer are all machines which transmit the fixed shaft to other fixed shafts. A moving shaft driver is arranged in the rear section, and the moving shaft driver is a machine for driving the fixed shaft to the revolution shaft. The moving shaft driver adopts a equidirectional transfer hundreds-directional driver which is shown in figure 4 and is a half-frame structural diagram commonly used in the industry. The structure between the moving shaft driver and the rotor shaft is in a second form: the method comprises the following steps that a equidirectional transfer and hundred-direction driver is arranged, the axis of the inner input end of a clutch in the equidirectional transfer and hundred-direction driver is parallel to the longitudinal axis of a machine body, power is accessed into the input end of the equidirectional transfer and hundred-direction driver through the front section of a transmission device, and the output end shaft of the equidirectional transfer and hundred-direction driver and a rotor wing shaft are connected; both the output shaft and the rotor shaft can be controlled to revolve around the inner input axis of the clutch in the hundred-direction transmission.
The two pairs of top propeller rotors are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the propeller discs of the top propeller rotors face upwards. The top propeller rotor comprises a rotor shaft, a hub, each propeller blade, a total distance adjusting mechanism and the like. Wherein the propeller blades are hard blades without flapping motion. The rotation directions of the two pairs of top propeller rotors are opposite and are linked. The distance between the two rotor shafts is equal to 1.4 times of the radius of the top propeller rotor. The front top propeller rotor hub is low, and the rear top propeller rotor hub is high. The top propeller rotor adjusts the propeller blade collective pitch through the collective pitch adjusting mechanism to adjust the rotor tension. The two pairs of top propeller rotors can tilt towards the left side and the right side respectively. The tilting is controlled by a tilting mechanism. The tilting angle ranges from 23 degrees to the left and the right respectively, and is 46 degrees in total. See fig. 3.
And the two tilting mechanisms adopt electric control mechanisms and respectively control the two pairs of top propeller rotors to tilt. Each tilt mechanism includes a base and a moving portion. The base is connected with the body, and the moving part is connected with the part to be tilted. The control adopts mature technology.
The transmission mechanism transmits power to the propulsion paddle.
The propulsion oar comprises a propulsion oar shaft, an oar hub, an oar blade, a total distance adjusting mechanism and the like, and generates forward and backward propulsion force on the airplane body. The propulsion oar adjusts the total pitch of the blades through the total pitch adjusting mechanism to adjust the propulsion. The propulsion paddle adopts one, and the arrangement position is at the tail of the machine body. The propeller shaft axis is parallel to the longitudinal axis of the fuselage.
The control system adopts a mature technology to control five sets of mechanisms, namely a front top propeller rotor pitch adjusting mechanism, a front top propeller rotor tilting mechanism, a rear top propeller rotor pitch adjusting mechanism, a rear top propeller rotor tilting mechanism and a propulsion propeller pitch adjusting mechanism.
The lateral-inclination longitudinal-row double-propeller composite helicopter of the embodiment is different from the traditional longitudinal-row double-propeller helicopter: 1, the propeller blade of the top propeller rotor adopts a hard blade without flapping motion. The traditional helicopter rotor adopts flexible blades or rigid blades, and the blades are provided with flapping motion. 2, the two pairs of top propeller rotors of the helicopter of the embodiment have large tilting angle range, the maximum horizontal component of the rotor tension is large, and the maximum rolling torque and the maximum steering torque are large. The traditional helicopter rotor disc cone shaft has small inclination angle range, small maximum horizontal component force of rotor wing pulling force, small maximum rolling torque and small maximum steering torque. And 3, the arrangement of the propelling propellers in the tandem double-propeller helicopter is firstly proposed, and when the propelling propellers work, advancing blades of the two pairs of top propeller rotors respectively provide lift force for the helicopter to form rolling torque to counteract balance with each other, so that the helicopter can fly at high speed in a rolling torque balance manner.
The flight action of the helicopter of the embodiment is as follows: when the propulsion propeller does not rotate or the total pitch of the blades of the propulsion propeller is zero, the effect is equal to that the propulsion propeller is not arranged, and the helicopter can realize various flight actions by controlling the two pairs of top propeller rotors. When the two pairs of top propeller rotors do not tilt and the tension of the rotors is synchronously adjusted, the helicopter is lifted. When the two pairs of top propeller rotors do not tilt and the tension of the rotors is asynchronously adjusted, the helicopter pitches, and the helicopter can horizontally fly forwards and backwards on the basis of pitching action. When the two pairs of top propeller rotors synchronously adjust and increase the rotor tension and respectively incline to different directions, the helicopter turns. When the two pairs of top propeller rotors synchronously adjust the tension of the rotors and tilt in the same direction, the helicopter rolls, and the helicopter can horizontally fly leftwards and rightwards on the basis of the rolling action. When the propelling propeller rotates and the total pitch of the blades of the propelling propeller is not zero, the two pairs of top propeller rotors do not tilt, forward blades of the two pairs of top propeller rotors respectively provide lift force for the helicopter to form rolling torque which is mutually offset and balanced, and the helicopter flies forwards and backwards horizontally at high speed under the pushing of the propelling propeller. Various actions may be superimposed.
Example 2: the invention embodiment 2 discloses a lateral-tilting and longitudinal-column double-propeller composite helicopter, which comprises a helicopter body, a power device, a transmission device, two pairs of top propeller rotors, two tilting mechanisms, a transmission mechanism, a propelling propeller, an operation system and the like. A moving shaft driver adopts a bevel gear pair. The layout of the embodiment is shown in fig. 1.
The fuselage is a longitudinal long cylindrical streamline.
The power device adopts a turboshaft engine.
The transmission device comprises an input shaft, transmission shafts, gear pairs, a speed reducer, a movable shaft driver and the like, and transmits power to the top propeller rotor wing. The transmission device takes the approach power device as a front section and takes the approach rotor shaft as a rear section. The input shaft in the front section is connected with a power device. Each transmission shaft, each gear pair and the speed reducer are all machines which transmit the fixed shaft to other fixed shafts. A moving shaft driver is arranged in the rear section, and the moving shaft driver is a machine for driving the fixed shaft to the revolution shaft. The moving shaft driver adopts a bevel gear pair. The structure between the moving shaft driver and the rotor shaft is in a form I: the bevel gear pair is arranged, the axis of an input shaft of the bevel gear pair is parallel to the longitudinal axis of the machine body, power is connected to the input shaft of the bevel gear pair through the front section of the transmission device, an output shaft of the bevel gear pair is connected with an input shaft of the speed reducer, and an output shaft of the speed reducer is connected with the rotor shaft; the output shaft of the bevel gear pair, the reducer and the rotor shaft can be controlled to revolve around the input shaft axis of the bevel gear pair.
The two pairs of top propeller rotors are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, and the propeller discs of the top propeller rotors face upwards. The top propeller rotor comprises a rotor shaft, a hub, each propeller blade, a total distance adjusting mechanism and the like. Wherein the propeller blades are hard blades without flapping motion. The rotation directions of the two pairs of top propeller rotors are opposite and are linked. The distance between the two rotor shafts is equal to 1.4 times of the radius of the top propeller rotor. The front top propeller rotor hub is low, and the rear top propeller rotor hub is high. The top propeller rotor adjusts the propeller blade collective pitch through the collective pitch adjusting mechanism to adjust the rotor tension. The two pairs of top propeller rotors can tilt towards the left side and the right side respectively. The tilting is controlled by a tilting mechanism. The tilting angle ranges from 30 degrees to the left and the right respectively, and the tilting angle ranges from 60 degrees in total. See fig. 5.
And the two tilting mechanisms adopt hydraulic control mechanisms and respectively control the two pairs of top propeller rotors to tilt. Each tilt mechanism includes a base and a moving portion. The base is connected with the body, and the moving part is connected with the part to be tilted. The control adopts mature technology.
The transmission mechanism transmits power to the propulsion paddle.
The propulsion oar comprises a propulsion oar shaft, an oar hub, an oar blade, a total distance adjusting mechanism and the like, and generates forward and backward propulsion force on the airplane body. The propulsion oar adjusts the total pitch of the blades through the total pitch adjusting mechanism to adjust the propulsion. The propulsion paddle adopts one, and the arrangement position is at the tail of the machine body. The propeller shaft axis is parallel to the longitudinal axis of the fuselage.
The control system adopts a mature technology to control five sets of mechanisms, namely a front top propeller rotor pitch adjusting mechanism, a front top propeller rotor tilting mechanism, a rear top propeller rotor pitch adjusting mechanism, a rear top propeller rotor tilting mechanism and a propulsion propeller pitch adjusting mechanism.
The lateral-inclination longitudinal-row double-propeller composite helicopter of the embodiment is different from the traditional longitudinal-row double-propeller helicopter: 1, the propeller blade of the top propeller rotor adopts a hard blade without flapping motion. The traditional helicopter rotor adopts flexible blades or rigid blades, and the blades are provided with flapping motion. 2, the two pairs of top propeller rotors of the helicopter of the embodiment have large tilting angle range, the maximum horizontal component of the rotor tension is large, and the maximum rolling torque and the maximum steering torque are large. The traditional helicopter rotor disc cone shaft has small inclination angle range, small maximum horizontal component force of rotor wing pulling force, small maximum rolling torque and small maximum steering torque. And 3, the arrangement of the propelling propellers in the tandem double-propeller helicopter is firstly proposed, and when the propelling propellers work, advancing blades of the two pairs of top propeller rotors respectively provide lift force for the helicopter to form rolling torque to counteract balance with each other, so that the helicopter can fly at high speed in a rolling torque balance manner.
The flight action of the helicopter of the embodiment 2 is the same as the flight action of the helicopter of the embodiment 1.
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 (3)
1. The heeling longitudinal double-propeller composite helicopter comprises a helicopter body, a power device, a transmission device, two pairs of top propeller rotors, two tilting mechanisms, a transmission mechanism, a propulsion propeller, an operation system and the like, and is characterized in that:
the helicopter body bears all devices, mechanisms and equipment of the helicopter;
the power device provides power for the top propeller rotor, the propulsion propeller and other equipment;
the transmission device transmits power to the propeller rotor, the transmission device comprises an input shaft, transmission shafts, gear pairs, a speed reducer, a movable shaft driver and the like, the transmission device takes an approach power device as a front section, the approach rotor shaft is taken as a rear section, the input shaft is connected with the power device in the front section, the movable shaft driver is arranged in the rear section, the movable shaft driver enables the rotor shaft to revolve around a longitudinal axis, the revolution is tilting, the movable shaft driver is of three types, the bevel gear pairs, the transmission in hundreds directions and the transmission in two directions are respectively adopted, and the structure between the movable shaft driver and the rotor shaft is of three types, wherein the form is one: the transmission device of the moving shaft adopts a bevel gear pair, the bevel gear pair is arranged, the axis of an input shaft of the bevel gear pair is parallel to the longitudinal axis of the machine body, power is connected to the input shaft of the bevel gear pair through the front section of the transmission device, an output shaft of the bevel gear pair is connected with an input shaft of the speed reducer, an output shaft of the speed reducer is connected with a rotor shaft, and the output shaft of the bevel gear pair, the speed reducer and the rotor shaft can be controlled to revolve around the axis of the input shaft of the bevel gear pair;
two pairs of top propeller rotors are arranged on the upper part of the fuselage in tandem along the longitudinal axis of the fuselage, the propeller discs of the top propeller rotors face upwards, each top propeller rotor comprises a rotor shaft, a propeller hub, each propeller blade, a total distance adjusting mechanism and the like, and the propeller blades are hard blades which do not set flapping motion. The two pairs of top propeller rotors rotate in opposite directions, the distance between two rotor shafts is greater than the radius of the top propeller rotors, the top propeller rotors adjust the propeller blade collective pitch through a collective pitch adjusting mechanism to adjust the tension of the rotors, the two pairs of top propeller rotors can tilt towards the left side and the right side respectively, the tilting is controlled by a tilting mechanism, and the tilting angle ranges from left to right not less than 10 degrees and not more than 35 degrees;
the two tilting mechanisms respectively control the two pairs of top propeller 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 to be controlled to tilt;
the transmission mechanism transmits power to the propelling paddle;
the propelling propellers generate forward and backward propelling force to the fuselage, the propelling propellers comprise propelling propeller shafts, propeller hubs, blades, a total pitch adjusting mechanism and the like, the propelling propellers adjust the total pitch of the blades through the total pitch adjusting mechanism to adjust the propelling force, the number of the propelling propellers is one, two or more, the propelling propellers are arranged at the head part of the fuselage, the tail part of the fuselage or the side part of the fuselage, and the axes of the propelling propeller shafts are parallel to the longitudinal axis of the fuselage;
the control system adopts a mature technology to control five sets of mechanisms, namely a front top propeller rotor pitch adjusting mechanism, a front top propeller rotor tilting mechanism, a rear top propeller rotor pitch adjusting mechanism, a rear top propeller rotor tilting mechanism and a propulsion propeller pitch adjusting mechanism.
2. The compound helicopter of claim 1 wherein the structure from the moving axis driver to the rotor axis takes the form two: the moving shaft driver adopts a hundred-direction driver, the hundred-direction driver is arranged, the inner input end axis of a clutch in the hundred-direction driver is parallel to the longitudinal axis of the machine body, power is connected to the input end of the hundred-direction driver through the front section of the driver, the output end shaft of the hundred-direction driver and the rotor shaft are connected, and the output end shaft of the hundred-direction driver and the rotor shaft can be controlled to revolve around the inner input end axis of the clutch in the hundred-direction driver.
3. The compound helicopter of claim 1 wherein the structure from the moving axis driver to the rotor axis takes the form three: the driving shaft driver adopts a double-folded circumferential driver, the double-folded circumferential driver is arranged, the axis of a reversing sleeve shaft in the double-folded circumferential driver is parallel to the longitudinal axis of the machine body, power is connected to an input shaft of the double-folded circumferential driver through the front section of the driving device and is connected with an output shaft of the double-folded circumferential driver and a rotor shaft, and the output shaft of the double-folded circumferential driver and the rotor shaft can be controlled to revolve around the axis of the reversing sleeve shaft in the double-folded circumferential driver.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010528339.4A CN111572763A (en) | 2020-06-11 | 2020-06-11 | Side-tipping longitudinal-row double-propeller composite helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010528339.4A CN111572763A (en) | 2020-06-11 | 2020-06-11 | Side-tipping longitudinal-row double-propeller composite helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN111572763A true CN111572763A (en) | 2020-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010528339.4A Pending CN111572763A (en) | 2020-06-11 | 2020-06-11 | Side-tipping longitudinal-row double-propeller composite helicopter |
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| CN (1) | CN111572763A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
-
2020
- 2020-06-11 CN CN202010528339.4A patent/CN111572763A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
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