CN113830299A - Main force fixed propeller pitch propeller rotor helicopter - Google Patents
Main force fixed propeller pitch propeller rotor helicopter Download PDFInfo
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- CN113830299A CN113830299A CN202111279169.1A CN202111279169A CN113830299A CN 113830299 A CN113830299 A CN 113830299A CN 202111279169 A CN202111279169 A CN 202111279169A CN 113830299 A CN113830299 A CN 113830299A
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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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Abstract
The invention discloses a main force fixed pitch propeller rotor wing helicopter. A first fixed pitch propeller is arranged at the top of a helicopter body, a second fixed pitch propeller is arranged on the first fixed pitch propeller, a rotor wing is arranged on the second fixed pitch propeller, a tail variable pitch propeller is arranged at the tail end of a tail beam, a total pitch and periodic variable pitch controller is arranged to control the inclination angle of the rotating face of a blade tip of a rotor wing blade, and therefore the size and the direction of lift force of the rotor wing are changed. An undercarriage is arranged at the position, close to the gravity center, below the helicopter body, the second fixed pitch propeller and the first fixed pitch propeller provide most lift force, the rotor wing only provides small lift force and is responsible for controlling pitching and rolling, the tail variable pitch propeller controls the course, the wind resistance is improved, the rotating speed of the rotor wing can be small, the manufacturing difficulty and cost are reduced, the rotating speed of the second fixed pitch propeller and the first fixed pitch propeller is large, the load capacity is increased, and the main force fixed pitch propeller rotor wing helicopter has the beneficial effects of being compact in structure, suitable for long-time flight in narrow space and capable of being applied to the fields of transportation, aerial photography, agricultural operation and the like.
Description
Technical Field
The invention relates to a main force fixed propeller pitch rotor helicopter which does not depend on an airport and can vertically lift, hover, fly forwards, backwards, leftwards and rightwards.
Background
The prior known successful methods for realizing helicopters capable of vertically lifting, flying front, back, left and right and hovering are single-rotor helicopters and four-rotor helicopters, the four-rotor helicopters adopt propellers with fixed pitches and have the advantages of simple structure, high reliability and easiness in manufacturing, but the flight attitude control of the four-rotor helicopters adopts variable speed control of the propellers, the rotational inertia of the propellers is increased along with the increase of the diameters of the propellers, the variable speed reaction speed of the propellers is reduced, so that the diameters of the propellers cannot be too large, the load capacity of the four-rotor helicopters is small, the wind resistance is poor, the single-rotor helicopters adopt the periodic variable pitch of the rotors and the variable pitch of tail propellers to control the flight attitude, the control capability and the wind resistance are strong, but along with the increase of the diameters of the rotors, the rotor hubs of the rotors are difficult to manufacture, and the cost is high.
Disclosure of Invention
In order to improve the advantages of simple structure, high reliability and easy manufacture of a propeller with a fixed propeller pitch of a four-propeller helicopter and the advantage of strong operating capability of a single-rotor helicopter, the invention provides a main force fixed propeller pitch rotary wing helicopter, and the aim is achieved.
The technical scheme adopted by the invention for solving the technical problems is as follows: the top of fuselage, the higher authority of main power fixed pitch propeller helicopter's focus, set up first pitch screw, at the top of fuselage, centrobaric higher authority, the periphery of first pitch screw sets up the vertical support of bikini, set up the horizontal support of middle level Y shape in the vertical support of bikini, set up the second distance screw on the horizontal support of middle level Y shape, in the vertical support of bikini, set up the horizontal support of top layer horizontal Y shape above the horizontal support of middle level Y shape, set up the rotor cabin on the horizontal support of top layer horizontal Y shape, set up the rotor on the rotor cabin, the afterbody in rotor cabin sets up the tail boom, set up the tail displacement screw at the end of tail boom.
The first fixed-pitch propeller and the second fixed-pitch propeller are fixed-pitch propellers with the same size and are driven by respective motors or engines, the motors or engines driving the first fixed-pitch propeller and the second fixed-pitch propeller have the same power, the rotating surfaces of the first fixed-pitch propeller and the second fixed-pitch propeller are horizontally arranged, the rotating directions of the first fixed-pitch propeller and the second fixed-pitch propeller are opposite, and the rotating centers of the first fixed-pitch propeller and the second fixed-pitch propeller and the projection of the gravity center of the main-force fixed-pitch propeller helicopter on the horizontal plane are overlapped.
The engine or the motor is arranged in the rotor cabin, the engine or the motor drives a rotor shaft through a transmission, blades of the rotor are connected with the rotor shaft through a blade housing, the blade housing is provided with a blade waving device consisting of a waving hinge, a shimmy hinge and a variable pitch hinge, a total pitch and periodic variable pitch controller is arranged to control the inclination angle of a rotating surface of a blade tip of the rotor, so that the size and the direction of lift force of the rotor are changed, the rotating surface of the rotor is horizontally arranged, the rotating direction of the rotor is opposite to the rotating direction of a first fixed pitch propeller or a second fixed pitch propeller, and the projections of the rotating centers of the rotor, the first fixed pitch propeller and the second fixed pitch propeller and the gravity center of the rotor helicopter on the horizontal plane are overlapped.
The rotating surface of the tail variable-pitch propeller is vertical or approximately vertical, the normal line of the rotating surface of the tail variable-pitch propeller is parallel to the transverse axis of the main force fixed-pitch propeller-driven rotary-wing helicopter, an engine or a motor in a rotary-wing cabin drives a rotary-wing shaft through a speed changer, and simultaneously a transmission shaft and another speed changer are connected to drive the tail variable-pitch propeller, so that the rotating speed of the tail variable-pitch propeller is greater than that of a rotary wing, and the rotating direction of the tail variable-pitch propeller is that a bottom blade is forward.
The power of a motor or an engine driving the first fixed-pitch propeller and the second fixed-pitch propeller is the same and is larger than that of the motor or the engine driving the rotor wing, so that the lift force generated by the first fixed-pitch propeller and the second fixed-pitch propeller is larger than that generated by the rotor wing, and the lift force of the main-force fixed-pitch propeller-driven helicopter is mainly provided by the first fixed-pitch propeller and the second fixed-pitch propeller.
An undercarriage is arranged under the fuselage near the center of gravity.
The flight principle of the main force fixed pitch propeller rotor helicopter is as follows: from top to bottom, it turns clockwise to establish the rotor, and tail pitch-variable propeller paddle turns to the bottom forward, and during the positive pitch, thrust direction is left, and second distance propeller anticlockwise turns, and first pitch propeller turns clockwise.
When the rotor wing, the tail variable-pitch propeller, the second fixed-pitch propeller and the first fixed-pitch propeller rotate, the rotating speeds of the second fixed-pitch propeller and the first fixed-pitch propeller are equal or approximately equal, the reactive torques of the second fixed-pitch propeller and the first fixed-pitch propeller are offset or approximately offset, the reactive torques of the rotor wing and the residual reactive torques (zero or a small value) of the second fixed-pitch propeller and the first fixed-pitch propeller are offset by the thrust torque of the tail variable-pitch propeller, and the main force fixed-pitch propeller helicopter keeps the course stable.
The motor driving the rotor, the second fixed-pitch propeller and the first fixed-pitch propeller or the accelerator of the engine is increased, so that the rotating speeds of the rotor, the second fixed-pitch propeller, the first fixed-pitch propeller and the tail variable-pitch propeller are increased, the lift force of the second fixed-pitch propeller, the first fixed-pitch propeller and the rotor is increased, and when the total lift force is greater than the weight of the main force fixed-pitch propeller rotorcraft, the main force fixed-pitch propeller rotorcraft vertically ascends.
The motor that reduces drive rotor, second distance screw, first distance screw or the throttle of engine make the rotational speed of rotor, second distance screw, first distance screw and tail displacement screw reduce, and the lift of second distance screw, first distance screw and rotor reduces, and when total lift equals the weight of main power fixed pitch propeller rotorcraft, main power fixed pitch propeller rotorcraft hovers.
And continuously reducing the accelerator of a motor or an engine driving the rotor, the second fixed-pitch propeller and the first fixed-pitch propeller, so that the rotating speeds of the rotor, the second fixed-pitch propeller, the first fixed-pitch propeller and the tail variable-pitch propeller are reduced, the lift force of the second fixed-pitch propeller, the first fixed-pitch propeller and the rotor is reduced, and when the total lift force is smaller than the weight of the main force fixed-pitch propeller rotor helicopter, the main force fixed-pitch propeller rotor helicopter vertically descends.
When the main force fixed propeller pitch rotor wing helicopter is in the air, the total pitch and cyclic pitch controller for operating the rotor wing inclines forwards, the rotating surface of the blade tip of the rotor wing inclines forwards, the lifting force of the rotor wing inclines forwards, and the main force fixed propeller pitch rotor wing helicopter inclines forwards; the total pitch and periodic pitch controller for operating the rotor wing tilts backwards, the rotating surface of the rotor wing tip tilts backwards, the lifting force of the rotor wing tilts backwards, and the main force fixed pitch propeller rotor wing helicopter tilts backwards to realize pitching operation.
When the main force fixed propeller pitch rotor helicopter is in the air, the total pitch and periodic pitch controller of the control rotor wing tilts to the left, the rotating surface of the rotor wing tilts to the left, the lift force of the rotor wing tilts to the left, and the main force fixed propeller pitch rotor helicopter rolls to the left; the total pitch and periodic pitch controller for operating the rotor wing inclines rightwards, the rotating surface of the blade tip of the rotor wing inclines rightwards, the lift force of the rotor wing inclines rightwards, and the main force fixed pitch propeller rotor helicopter rolls rightwards, so that the roll operation is realized.
The forward pitch of the tail variable pitch propeller is increased, the leftward thrust of the tail variable pitch propeller is increased, the leftward torque of the tail variable pitch propeller is increased, the main force fixed pitch propeller rotorcraft turns to the right, the forward pitch of the tail variable pitch propeller is reduced, the leftward thrust of the tail variable pitch propeller is reduced, the leftward torque of the tail variable pitch propeller is reduced, the counter torque of the rotor is larger than the leftward torque of the tail variable pitch propeller, the main force fixed pitch propeller rotorcraft turns to the left, and course control is achieved.
When the main force fixed pitch propeller rotor helicopter is in the air, the helicopter body is controlled to bow forwards, meanwhile, a motor for driving the rotor, the second fixed pitch propeller and the first fixed pitch propeller or an accelerator of an engine is increased, and the main force fixed pitch propeller rotor helicopter flies forwards; the helicopter body is controlled to tilt backwards, and the motor of the rotor wing, the second fixed-pitch propeller and the first fixed-pitch propeller or the accelerator of the engine are driven simultaneously, so that the rotor wing helicopter with the main force fixed-pitch propeller flies backwards; the forward pitch and leftward rotation directions of the helicopter body are controlled, meanwhile, a motor or an accelerator of an engine for driving the rotor wing, the second fixed-pitch propeller and the first fixed-pitch propeller is increased, and the helicopter with the main force fixed-pitch propeller flies leftward and forward; the front pitch and right rotation directions of the helicopter body are controlled, meanwhile, a motor or an accelerator of an engine for driving the rotor wing, the second fixed pitch propeller and the first fixed pitch propeller is increased, and the helicopter with the main force fixed pitch propeller flies right ahead; the helicopter body is controlled to roll leftwards, meanwhile, a motor for driving the rotor wing, the second fixed-pitch propeller and the first fixed-pitch propeller or an accelerator of an engine is increased, and the helicopter with the main force fixed-pitch propeller rotor wing flies leftwards; the helicopter body is controlled to roll rightwards, the motor driving the rotor wing, the second fixed-pitch propeller and the first fixed-pitch propeller or the accelerator of the engine is increased, and the main force fixed-pitch propeller rotor helicopter flies rightwards.
In the whole direction process, the rotating speeds of the second distance propeller and the first distance propeller are kept the same or close to the same, so that the torque generation of the second distance propeller and the torque generation of the first distance propeller are mutually offset or close to offset.
The invention has the advantages that the second fixed-pitch propeller is arranged, the first fixed-pitch propeller provides most of lift force, the rotor only provides smaller lift force, the rotor is responsible for controlling pitching and rolling, the tail variable-pitch propeller controls course, and improves wind resistance, the second fixed-pitch propeller and the first fixed-pitch propeller do not participate in controlling course, pitching and rolling, the size and the rotating speed of the second fixed-pitch propeller and the first fixed-pitch propeller can be improved, the carrying capacity is increased, the rotating speed of the rotor can be smaller, the manufacturing difficulty and the manufacturing cost are reduced, the structure is compact, the occupied space is small, the aircraft is suitable for flying in narrow space for a long time, and the aircraft can be applied to the fields of transportation, aerial photography, agricultural operation and the like.
Drawings
The invention is further illustrated with reference to the following figures and examples.
Fig. 1 is an isometric view of a first embodiment of the invention.
Fig. 2 is an isometric view of a second embodiment of the invention.
In the figure, 1, a rotor, 2, a tail beam, 3, a tail variable-pitch propeller, 4, a total pitch and period variable-pitch controller of the rotor, 5, a rotor cabin, 6, a top-layer horizontal Y-shaped transverse support, 7, a middle-layer horizontal Y-shaped transverse support, 8, a three-point type vertical support, 9, a machine body, 10, an undercarriage, 11, a first fixed-pitch propeller, 12, a second fixed-pitch propeller and P, the center of gravity of the propeller-pitch helicopter is fixed by main force.
Detailed Description
In the embodiment shown in fig. 1, a first pitch propeller 11 is arranged on the top of a fuselage 9 and above the center of gravity P of a main-force fixed-pitch propeller-driven rotorcraft, a three-point vertical support 8 is arranged on the top of the fuselage 9 and above the center of gravity P and on the periphery of the first pitch propeller 11, a middle-layer horizontal Y-shaped transverse support 7 is arranged in the three-point vertical support 8, a second pitch propeller 12 is arranged on the middle-layer horizontal Y-shaped transverse support 7, a top-layer horizontal Y-shaped transverse support 6 is arranged in the three-point vertical support 8 and above the middle-layer horizontal Y-shaped transverse support 7, a rotorcraft cabin 5 is arranged on the top-layer horizontal Y-shaped transverse support 6, a rotor 1 is arranged on the rotorcraft cabin 5, a tail beam 2 is arranged at the tail end of the rotorcraft 5, and a tail variable-pitch propeller 3 is arranged at the tail end of the tail beam 2.
The first fixed pitch propeller 11 and the second fixed pitch propeller 12 are fixed pitch propellers having the same size, and are driven by respective motors or engines, the power of the motors or engines driving the first fixed pitch propeller 11 and the second fixed pitch propeller 12 is the same, the rotating surfaces of the first fixed pitch propeller 11 and the second fixed pitch propeller 12 are horizontally arranged, the rotating directions of the first fixed pitch propeller 11 and the second fixed pitch propeller 12 are opposite, and the rotating centers of the first fixed pitch propeller 11 and the second fixed pitch propeller 12 and the projection of the center of gravity P of the main force fixed pitch propeller helicopter on the horizontal plane are overlapped.
An engine or a motor is arranged in a rotor cabin 5, the engine or the motor drives a rotor shaft through a transmission, blades of a rotor 1 are connected with the rotor shaft through a propeller shell, the propeller shell is provided with a blade flapping device consisting of a flapping hinge, a shimmy hinge and a variable pitch hinge, a total pitch and periodic variable pitch controller 4 is arranged to operate the inclination angle of a rotating surface of a rotor blade tip, so that the magnitude and the direction of the lift force of the rotor 1 are changed, the rotating surface of the rotor 1 is horizontally arranged, the rotating direction of the rotor 1 is opposite to the rotating direction of a first fixed pitch propeller 11 or a second fixed pitch propeller 12, the rotating centers of the rotor 1, the first fixed pitch propeller 11 and the second fixed pitch propeller 12, and the projection of the gravity center P of the main force fixed pitch propeller helicopter on the horizontal plane are overlapped.
The rotating surface of the tail variable-pitch propeller 3 is vertical or approximately vertical, the normal line of the rotating surface of the tail variable-pitch propeller 3 is parallel to the transverse axis of the main force fixed-pitch propeller-type rotorcraft, and an engine or a motor in a rotor cabin 5 drives a rotor shaft through a transmission and simultaneously connects a transmission shaft with another transmission to drive the tail variable-pitch propeller 3, so that the rotating speed of the tail variable-pitch propeller 3 is greater than that of the rotor 1, and the rotating direction of the tail variable-pitch propeller 3 is that the bottom blades are forward.
The power of a motor or an engine driving the first fixed-pitch propeller 11 and the second fixed-pitch propeller 12 is the same and is larger than that of a motor or an engine driving the rotor wing 1, so that the lift force generated by the first fixed-pitch propeller 11 or the second fixed-pitch propeller 12 is larger than that generated by the rotor wing 1, and the lift force of the main-force fixed-pitch propeller helicopter is mainly provided by the first fixed-pitch propeller 11 and the second fixed-pitch propeller 12.
An undercarriage 10 is provided below the fuselage 9 near the centre of gravity.
The flight principle of the main force fixed pitch propeller rotor helicopter is as follows: from top to bottom, it turns clockwise to establish rotor 1, and 3 paddles of tail pitch-variable screw turn to the bottom forward, and during the positive pitch, thrust direction is left, and second distance screw 12 anticlockwise turns, and first distance screw 11 clockwise turns.
When the rotor wing 1, the tail variable-pitch propeller 3, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 rotate, the rotating speeds of the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 are equal or approximately equal, the reactive torques of the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 are offset or approximately offset, the reactive torque of the rotor wing 1 and the residual reactive torque (zero or a small value) of the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 are offset by the thrust torque of the tail variable-pitch propeller 3, and the main force fixed-pitch propeller helicopter keeps the course stable.
The accelerator of a motor or an engine for driving the rotor wing 1, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 is increased, so that the rotating speeds of the rotor wing 1, the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the tail variable-pitch propeller 3 are increased, the lift force of the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the rotor wing 1 is increased, and when the total lift force is greater than the weight of the main force fixed-pitch propeller rotor helicopter, the main force fixed-pitch propeller rotor helicopter vertically rises.
The throttle of the motor or the engine driving the rotor wing 1, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 is reduced, so that the rotating speeds of the rotor wing 1, the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the tail variable-pitch propeller 3 are reduced, the lift force of the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the rotor wing 1 is reduced, and when the total lift force is equal to the weight of the main-force fixed-pitch propeller rotor helicopter, the main-force fixed-pitch propeller rotor helicopter hovers.
And continuously reducing the accelerator of a motor or an engine for driving the rotor wing 1, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11, so that the rotating speeds of the rotor wing 1, the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the tail variable-pitch propeller 3 are reduced, the lift force of the second fixed-pitch propeller 12, the first fixed-pitch propeller 11 and the rotor wing 1 is reduced, and when the total lift force is smaller than the weight of the main force fixed-pitch propeller-based helicopter, the main force fixed-pitch propeller-based helicopter vertically descends.
When the main force fixed propeller pitch rotor helicopter is in the air, the total pitch and cyclic pitch controller 4 for operating the rotor wing inclines forwards, the rotating surface of the blade tip of the rotor wing 1 inclines forwards, the lifting force of the rotor wing 1 inclines forwards, and the main force fixed propeller pitch rotor helicopter inclines forwards; the total pitch and cyclic pitch controller 4 for operating the rotor wing tilts backwards, the rotating surface of the blade tip of the rotor wing 1 tilts backwards, the lifting force of the rotor wing 1 tilts backwards, and the main force fixed pitch propeller-driven rotor helicopter tilts backwards to realize pitching operation.
When the main force fixed propeller pitch proprotor helicopter is in the air, the total pitch and periodic pitch controller 4 of the control rotor wing tilts to the left, the rotating surface of the blade tip of the rotor wing 1 tilts to the left, the lift force of the rotor wing 1 tilts to the left, and the main force fixed propeller pitch proprotor helicopter rolls to the left; the total pitch and cyclic pitch controller 4 for operating the rotor wing inclines rightwards, the rotating surface of the blade tip of the rotor wing 1 inclines rightwards, the lift force of the rotor wing 1 inclines rightwards, and the main force fixed pitch propeller rotor helicopter rolls rightwards, so that the roll operation is realized.
The forward pitch of the tail variable pitch propeller 3 is increased, the leftward thrust of the tail variable pitch propeller 3 is increased, the leftward torque of the tail variable pitch propeller 3 is increased, the main force fixed pitch propeller helicopter is enabled to turn rightward, the forward pitch of the tail variable pitch propeller 3 is reduced, the leftward thrust of the tail variable pitch propeller 3 is reduced, the leftward torque of the tail variable pitch propeller 3 is reduced, the reaction torque of the rotor 1 is larger than the leftward torque of the tail variable pitch propeller 3, the main force fixed pitch propeller helicopter is enabled to turn leftward, and course control is achieved.
When the main force fixed pitch propeller rotor helicopter is in the air, the fuselage 9 is controlled to bow forwards, meanwhile, the motor or the accelerator of the engine for driving the rotor 1, the second fixed pitch propeller 12 and the first fixed pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies forwards; the helicopter body 9 is controlled to tilt backwards, simultaneously the accelerator of a motor or an engine driving the rotor wing 1, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 is increased, and the main force fixed-pitch propeller helicopter flies backwards; the front pitch and left rotation directions of the helicopter body 9 are controlled, meanwhile, the motor or the accelerator of the engine for driving the rotor wing 1, the second fixed pitch propeller 12 and the first fixed pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies towards the left front; the front pitch and right rotation directions of the helicopter body 9 are controlled, meanwhile, the motor or the accelerator of the engine for driving the rotor wing 1, the second fixed pitch propeller 12 and the first fixed pitch propeller 11 is increased, and the main force fixed pitch propeller helicopter flies right ahead; the helicopter body 9 is controlled to roll leftwards, meanwhile, the motor or the accelerator of the engine for driving the rotor wing 1, the second fixed-pitch propeller 12 and the first fixed-pitch propeller 11 is increased, and the main force fixed-pitch propeller rotor helicopter flies leftwards; the fuselage 9 is steered to roll right while the motor or engine throttle driving the rotor 1, the second pitch propeller 12 and the first pitch propeller 11 is increased, and the main force fixed pitch propeller helicopter flies to the right.
In the embodiment shown in fig. 2, a first pitch propeller 11 is arranged on the top of a fuselage 9 and above the center of gravity P of a main-force fixed-pitch proprotor helicopter, a three-point vertical bracket 8 is arranged on the top of the fuselage 9 and above the center of gravity P and on the periphery of the first pitch propeller 11, a top-layer horizontal Y-shaped transverse support 6 is arranged in the three-point vertical bracket 8 and above the first pitch propeller 11, a rotor nacelle 5 is arranged on the top-layer horizontal Y-shaped transverse support 6, a rotor 1 is arranged on the rotor nacelle 5, a tail boom 2 is arranged at the tail part of the rotor nacelle 5, and a tail pitch propeller 3 is arranged at the tail end of the tail boom 2.
The first fixed-pitch propeller 11 is a fixed-pitch propeller and is driven by a motor or an engine, the rotating surface of the first fixed-pitch propeller 11 is horizontally arranged, and the projection of the rotating center of the first fixed-pitch propeller 11 and the projection of the gravity center P of the main force fixed-pitch propeller helicopter on the horizontal plane are overlapped.
The rotor wing helicopter is characterized in that an engine or a motor is arranged in a rotor wing cabin 5, the engine or the motor drives a rotor wing shaft through a speed changer, blades of a rotor wing 1 are connected with the rotor wing shaft through a blade shell, the blade shell is provided with a blade waving device consisting of a waving hinge, a shimmy hinge and a variable pitch hinge, a total pitch and periodic pitch controller 4 is arranged to operate the inclination angle of a rotating surface of a blade tip of the rotor wing, so that the lift force and the lift force of the rotor wing are changed, the rotating surface of the rotor wing 1 is horizontally arranged, the rotating direction of the rotor wing 1 is opposite to the rotating direction of a first pitch propeller 11, and the projections of the rotating center of the rotor wing 1, the first pitch propeller 11 and the gravity center P of a main force fixed pitch propeller helicopter on the horizontal plane are overlapped.
The rotating surface of the tail variable-pitch propeller 3 is vertical or approximately vertical, the normal line of the rotating surface of the tail variable-pitch propeller 3 is parallel to the transverse axis of the main force fixed-pitch propeller-type rotorcraft, and an engine or a motor in a rotor cabin 5 drives a rotor shaft through a transmission and simultaneously connects a transmission shaft with another transmission to drive the tail variable-pitch propeller 3, so that the rotating speed of the tail variable-pitch propeller 3 is greater than that of the rotor 1, and the rotating direction of the tail variable-pitch propeller 3 is that the bottom blades are forward.
The power of a motor or an engine driving the first pitch propeller 11 is set to be larger than that of a motor or an engine driving the rotor wing 1, so that the lift force generated by the first pitch propeller 11 is larger than that generated by the rotor wing 1, and most of the lift force of the main force fixed pitch propeller-driven rotorcraft is provided by the first pitch propeller 11.
An undercarriage 10 is provided below the fuselage 9 near the centre of gravity.
The flight principle of the main force fixed pitch propeller rotor helicopter is as follows: from top to bottom, it turns anticlockwise to establish rotor 1, and 3 paddles of tail pitch-variable screw turn to the bottom forward, when positive pitch, thrust direction is left, and first pitch screw 11 turns clockwise.
When rotor 1, tail variable-pitch propeller 3, first pitch propeller 11 rotate, first pitch propeller 11's rotational speed is greater than the rotational speed at rotor 1, first pitch propeller 11's reaction torque is greater than rotor 1's reaction torque, first pitch propeller 11's reaction torque and rotor 1's reaction torque part offset, remaining reaction torque is clockwise first pitch propeller 11's partial reaction torque, offset each other by tail variable-pitch propeller 3's thrust moment, main force fixed pitch propeller helicopter keeps the course stable.
The accelerator of the motor or the engine driving the rotor wing 1 and the first pitch propeller 11 is increased, so that the rotating speeds of the rotor wing 1, the first pitch propeller 11 and the tail variable pitch propeller 3 are increased, the lift force of the first pitch propeller 11 and the rotor wing 1 is increased, and when the total lift force is greater than the weight of the main force fixed pitch propeller rotor helicopter, the main force fixed pitch propeller rotor helicopter vertically rises.
The throttle of the motor or the engine driving the rotor 1 and the first pitch propeller 11 is reduced, so that the rotating speeds of the rotor 1, the first pitch propeller 11 and the tail variable pitch propeller 3 are reduced, the lift force of the first pitch propeller 11 and the rotor 1 is reduced, and when the total lift force is equal to the weight of the main force fixed pitch propeller helicopter, the main force fixed pitch propeller helicopter hovers.
The number of the throttles driving the motor or engine of the rotor 1 and the first pitch propeller 11 is continuously reduced, so that the number of the revolutions of the rotor 1, the first pitch propeller 11 and the tail variable pitch propeller 3 is reduced, the lift force of the first pitch propeller 11 and the rotor 1 is reduced, and when the total lift force is smaller than the weight of the main force fixed pitch propeller helicopter, the main force fixed pitch propeller helicopter vertically descends.
When the main force fixed propeller pitch rotor helicopter is in the air, the total pitch and cyclic pitch controller 4 for operating the rotor wing inclines forwards, the rotating surface of the blade tip of the rotor wing 1 inclines forwards, the lifting force of the rotor wing 1 inclines forwards, and the main force fixed propeller pitch rotor helicopter inclines forwards; the total pitch and cyclic pitch controller 4 for operating the rotor wing tilts backwards, the rotating surface of the blade tip of the rotor wing 1 tilts backwards, the lifting force of the rotor wing 1 tilts backwards, and the main force fixed pitch propeller-driven rotor helicopter tilts backwards to realize pitching operation.
When the main force fixed propeller pitch proprotor helicopter is in the air, the total pitch and periodic pitch controller 4 of the control rotor wing tilts to the left, the rotating surface of the blade tip of the rotor wing 1 tilts to the left, the lift force of the rotor wing 1 tilts to the left, and the main force fixed propeller pitch proprotor helicopter rolls to the left; the total pitch and cyclic pitch controller 4 for operating the rotor wing inclines rightwards, the rotating surface of the blade tip of the rotor wing 1 inclines rightwards, the lift force of the rotor wing 1 inclines rightwards, and the main force fixed pitch propeller rotor helicopter rolls rightwards, so that the roll operation is realized.
Increase the positive pitch of tail variable pitch propeller 3, the left thrust of tail variable pitch propeller 3 increases, the left moment of tail variable pitch propeller 3 increases, make main power fixed pitch propeller helicopter turn to the right, reduce the positive pitch of tail variable pitch propeller 3, the left thrust of tail variable pitch propeller 3 reduces, the left moment of tail variable pitch propeller 3 reduces, the reaction torque of the first pitch propeller 11 of clockwise turning and the reaction torque part of the rotor 1 of anticlockwise turning offset, remaining reaction torque is the partial reaction torque of the first pitch propeller 11 of clockwise turning, be greater than the left moment of tail variable pitch propeller 3, make main power fixed pitch propeller helicopter turn to the left, realize course control.
When the main force fixed pitch propeller rotor helicopter is in the air, the fuselage 9 is controlled to bow forwards, meanwhile, the motor driving the rotor 1 and the first pitch propeller 11 or the accelerator of the engine is increased, and the main force fixed pitch propeller rotor helicopter flies forwards; the helicopter body 9 is controlled to tilt backwards, simultaneously the accelerator of a motor or an engine for driving the rotor wing 1 and the first fixed pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies backwards; the front pitch and left rotation directions of the helicopter body 9 are controlled, simultaneously, the accelerator of a motor or an engine for driving the rotor wing 1 and the first pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies left forward; the front pitch and right rotation directions of the helicopter body 9 are controlled, simultaneously, the accelerator of a motor or an engine for driving the rotor wing 1 and the first pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies right ahead; the helicopter body 9 is controlled to roll leftwards, simultaneously the accelerator of a motor or an engine for driving the rotor wing 1 and the first fixed pitch propeller 11 is increased, and the main force fixed pitch propeller rotor helicopter flies leftwards; the fuselage 9 is steered to roll right while the motor or engine throttle driving the rotor 1 and the first pitch propeller 11 is increased, the main force fixed pitch propeller helicopter flies to the right.
Claims (2)
1. A rotor helicopter with main fixed-pitch propeller is composed of a main body, a first fixed-pitch propeller above the center of gravity of said main fixed-pitch propeller, a three-point vertical supporter above the top and center of said main body and around said first fixed-pitch propeller, a middle horizontal Y-shaped transverse supporter in said three-point vertical supporter, a second fixed-pitch propeller on said middle horizontal Y-shaped transverse supporter, a top horizontal Y-shaped transverse supporter in said three-point vertical supporter and above said middle horizontal Y-shaped transverse supporter, a rotor cabin on said top horizontal Y-shaped transverse supporter, a rotor wing in said rotor cabin, a tail beam at the tail of said rotor cabin, a tail variable-pitch propeller at the tail end of said tail beam, and two fixed-pitch propellers, the power of a motor or an engine for driving the first fixed-pitch propeller and the second fixed-pitch propeller is the same, the rotating surfaces of the first fixed-pitch propeller and the second fixed-pitch propeller are horizontally arranged, the engine or the motor is arranged in a rotor cabin, the engine or the motor drives a rotor shaft through a speed changer, blades of the rotor are connected with the rotor shaft through a blade shell, the blade shell is provided with a blade flapping device consisting of a flapping hinge, a shimmy hinge and a variable pitch hinge, a total pitch and periodic variable pitch controller is arranged for controlling the inclination angle of the rotating surface of the tip of the rotor blade so as to change the magnitude and the direction of the lift force of the rotor, the rotating surface of the rotor is horizontally arranged, the rotating surface of the tail variable pitch propeller is vertical or approximately vertical, the normal line of the rotating surface of the tail variable pitch propeller is parallel to the transverse axis of the main force fixed-pitch propeller helicopter, and the engine or the motor in the rotor cabin drives the rotor shaft through the speed changer, connect transmission shaft and another derailleur drive tail displacement screw, make the rotational speed of tail displacement screw be greater than the rotational speed of rotor, the direction of rotation of tail displacement screw is that the bottom paddle is forward, and the power that sets up the motor or the engine of first distance screw of drive and second distance screw is the same and is greater than the power of the motor or the engine of drive rotor, and near the focus sets up undercarriage, characterized by under the fuselage: the rotor, the rotation center of first fixed pitch propeller and second fixed pitch propeller, the projection at the horizontal plane of focus of main force fixed pitch propeller rotor helicopter overlaps, the rotational speed of second fixed pitch propeller and first fixed pitch propeller equals or approximately equals, the direction of rotation of first fixed pitch propeller and second fixed pitch propeller is opposite, the reaction torque of second fixed pitch propeller and first fixed pitch propeller offsets or approximately offsets each other, the lift that first fixed pitch propeller and second fixed pitch propeller produced is greater than the lift that the rotor produced, the lift of main force fixed pitch propeller rotor helicopter is mainly provided by first fixed pitch propeller and second fixed pitch propeller, first fixed pitch propeller and second fixed pitch propeller do not participate in the every single move, roll and the course of manipulating main force fixed pitch propeller rotor helicopter.
2. The main force fixed pitch proprotor helicopter of claim 1, wherein: the middle-layer horizontal Y-shaped transverse support and the second fixed-pitch propeller are not arranged, the lift force of the main force fixed-pitch propeller rotorcraft is mainly provided by the first fixed-pitch propeller, the rotating directions of the rotor and the first fixed-pitch propeller are opposite, the reactive torque of the first fixed-pitch propeller is larger than the reactive torque of the rotor, the reactive torque of the rotor and the first fixed-pitch propeller are partially offset, and the rest reactive torque is the partial reactive torque of the first fixed-pitch propeller and is offset by the thrust torque of the tail variable-pitch propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111279169.1A CN113830299A (en) | 2021-10-31 | 2021-10-31 | Main force fixed propeller pitch propeller rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111279169.1A CN113830299A (en) | 2021-10-31 | 2021-10-31 | Main force fixed propeller pitch propeller rotor helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113830299A true CN113830299A (en) | 2021-12-24 |
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ID=78966542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111279169.1A Withdrawn CN113830299A (en) | 2021-10-31 | 2021-10-31 | Main force fixed propeller pitch propeller rotor helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113830299A (en) |
-
2021
- 2021-10-31 CN CN202111279169.1A patent/CN113830299A/en not_active Withdrawn
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Application publication date: 20211224 |