CN112591083B - Folding collection rectification structure of paddle - Google Patents
Folding collection rectification structure of paddle Download PDFInfo
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- CN112591083B CN112591083B CN202011573050.0A CN202011573050A CN112591083B CN 112591083 B CN112591083 B CN 112591083B CN 202011573050 A CN202011573050 A CN 202011573050A CN 112591083 B CN112591083 B CN 112591083B
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- blades
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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
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/72—Means acting on blades
Abstract
The invention belongs to the technical field of blades of aviation rotor crafts, and particularly relates to a folding, collecting and rectifying structure of blades. Comprises a nacelle (10), a folding control system (20) and a lift system (30); the rear end of the nacelle (10) is connected with the wings, the surface of the nacelle (10) is provided with a recess which follows the shape of the folded blade in the lift system (30), and the blade can be buried in the recess after being completely folded; the folding control system (20) is arranged inside the nacelle (10); when blade folding is performed, a mechanical connection is generated between the folding control system (20) and the lift system (30) so as to realize blade folding in the lift system (30); when the mechanical connection between the folding control system (20) and the lift system (30) is broken, the blades in the lift system (30) will return to the deployed and rotated state. The invention has the characteristics of simple structure, beautiful appearance, high reliability and good rectifying effect after the blades are folded.
Description
Technical Field
The invention belongs to the technical field of blades of aviation rotor crafts, and particularly relates to a folding, collecting and rectifying structure of blades.
Background
The distributed multi-propeller tilting wing aircraft is a novel configuration aircraft which adopts distributed rotors and tilting wings and is arranged between an airplane and a helicopter, and has airplane and helicopter flight modes. A plurality of distributed electrically-driven rotor wing units are fixed on the wings in a distributed mode, the wings are perpendicular when the helicopter is in helicopter mode flight, all the rotor wings work to provide lift force, the rotor wings tilt by about 90 degrees when the helicopter is in airplane mode flight, and meanwhile, part of the rotor wing units are closed. The aircraft has the capability of vertical take-off and landing, fixed-point hovering and high-speed forward flight, the flight speed and the combat radius are greatly improved compared with those of a conventional helicopter, the aircraft is one of important development directions of a future high-speed new-configuration rotor aircraft, and at present, research institutions such as American NASA (national aeronautical and astronautic administration system), boeing and French airbus and the like carry out a large amount of preliminary research work on the aircraft.
Because the closed rotor wing unit is perpendicular to the airflow in the flight direction when the aircraft flies in a high speed mode, the aerodynamic resistance of the rotor wing is extremely high, if the closed rotor wing unit blades are folded and collected in an engine nacelle, the resistance of the closed rotor wing unit blades can be effectively reduced, and the aircraft can fly in the high speed mode, so that the folding and collection of the blades are also one of important technologies of the aircraft.
However, the existing rotor type aircraft blade folding technology is mainly designed for reducing the occupied space for ground maintenance and facilitating package and transportation, and the folding modes of the blades are different in folding direction and are not suitable for the aircraft with the structure; aiming at the tilt rotor aircraft, the tilt rotor aircraft is characterized in that wings are fixed, the rotors tilt along with an engine nacelle, the folding scheme of the blades is relatively complex due to the difference of structural forms, and meanwhile, the nacelle cannot achieve the collection effect after the blades are folded.
Chinese patent application No. 201080066903.X discloses a foldable rotor system for a rotary-wing aircraft, in which rotor blades are folded in a specific helical trajectory by blade folding actuators, actuated around a clamping pin shaft by tilting disks so that the rotor blades are arranged approximately close to a nacelle, and when the rotor blades are fully folded, air pockets are deployed from the nacelle surface under each rotor blade to act as bumpers for minimizing contact of the rotor blades with the nacelle and for regulating aerodynamic air flow around the rotor blades in the folded position. By adopting the method, the blades are only collected on the surface of the engine compartment, and the blades are still in a Porro state, so that the airflow flowing through the blades and behind the blades is unstable. For the condition that the air flow is only arranged at the outer side of the wing and no other aerodynamic surface (no wing or horizontal tail) is arranged right behind the nacelle, the influence of the unstable air flow on the whole aircraft can be ignored, but for the condition that the aircraft with two tandem wings is arranged at the front and the rear, the number of distributed short bins is large and the number of blades needing to be folded is large, and the unstable air flow flowing through the folded blades above the front stage can generate larger adverse influence on the front wing and the rear wing; meanwhile, the folding process of the blades needs to be realized by driving the folding actuators respectively under the condition that the blades rotate to spirally flow forwards, and if the operation is improper, danger is possibly caused, so that the operation requirement is high, and the process is complex.
Chinese patent application No. 201610933799.9 discloses a folding structure of drawing in, rotor power component and tilt rotor aircraft, the folding structure of drawing in includes: the device comprises a first motor, an installation table, a transfer piece, a driving piece and a plurality of lever pieces; paddle structrual installation is connected with the adaptor on the mount table, paddle structure, and first motor screw output shaft is connected with the driving piece, drives the driving piece through first motor screw output shaft and drives the adaptor up-and-down motion, drives paddle structure and realizes the expansion and receipts of paddle and close. According to the blade folding structure, on one hand, the blades are still folded in a rotating state, if the operation is improper, danger is possibly caused, the operation requirement is high, the integral folding mechanism is also complex, and unreliable factors may exist; on the other hand, after being folded each time, the paddle positions are random and the paddle is exposed, so that the aerodynamic appearance is influenced, and meanwhile, the full natural exposure of the paddle can influence the protection of the paddle for a long time.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects of the prior art, the invention mainly solves the problem of folding the blades at the closed rotor wing unit in the flight of the distributed multi-blade tilting wing aircraft, and meanwhile, the folded blades can be better stored in the short cabin of an engine, thereby reducing the aerodynamic resistance and improving the aerodynamic efficiency of the aircraft in the airplane mode flight.
The technical scheme of the invention is as follows: to achieve the above object, according to a first aspect of the present invention, there is provided a blade folding stowage fairing structure, comprising a nacelle 10, a folding control system 20, a lift system 30;
the rear end of the nacelle 10 is connected with the wing, the surface of the nacelle 10 is provided with a recess which follows the shape of the folded blade in the lift system 30, and the blade can be buried in the recess after being completely folded;
the folding control system 20 is installed inside the nacelle 10; when blade folding is performed, a mechanical connection is generated between the folding control system 20 and the lift system 30 to realize blade folding in the lift system 30; when the mechanical connection between the folding control system 20 and the lift system 30 is broken, the blades in the lift system 30 will return to the deployed and rotated state.
In one possible embodiment, when blade folding is performed, a mechanical positioning connection is created between the folding control system 20 and the lift system 30, first stopping the rotation of the blades in the lift system 30 and fixing the blade position.
In one possible embodiment, the folding control system 20 includes a steering engine 21, a rocker arm 22a, a connecting rod 22b, a first slider joint 23a, a second slider joint 23b, a slide rail 24, a base 25, a compression spring 26, a folding actuator 27, and a positioning cylinder 28;
the steering engine 21 outputs torque according to the control signal requirement and drives the rocker arm 22a to rotate; one end of the rocker arm 22a is actively connected with the steering engine 21, and the other end of the rocker arm is hinged with the connecting rod 22b to drive the connecting rod 22b to move; the connecting rod 22b is hinged to the first sliding block joint 23a and drives the first sliding block joint 23a to move, and the first sliding block joint 23a is connected with the sliding rail 24 in a sliding manner; the slide rail 24 is fixed in the nacelle; the first sliding block joint 23a is further provided with symmetrically arranged lugs, coaxial through holes are formed in the lugs, and the first sliding block joint 23a is fixedly connected with the base 25 through the lugs; the base 25 is circular, a through hole is formed in the center of the base, and a connecting lug piece extends outwards from the edge of the base and is connected with the first slider joint 23a through the connecting lug piece;
the folding actuator cylinder 27 is cylindrical, one end of the folding actuator cylinder is provided with a flange, a plurality of connecting lugs are uniformly distributed on the flange, the connecting lugs on the flange are fixedly connected with the connecting lugs at the corresponding positions of the base 25, and bosses corresponding to the number and the positions of the blades are arranged on the other end surface of the folding actuator cylinder close to the blades and used for pushing the blades to fold in the folding process; a sliding groove is formed in the folding actuating cylinder 27 and used for installing and positioning the positioning cylinder 28; the main body of the positioning cylinder 28 is in a cylindrical shape, a boss is arranged on the outer surface of the circumference of one end of the positioning cylinder 28, which is close to the folding direction of the paddle, and the boss is in sliding fit with a sliding groove in the folding actuating cylinder 27, so that the boss can only move along the sliding groove of the folding actuating cylinder 27 but cannot rotate after being installed, and cannot be separated from the other end of the folding actuating cylinder 27 to play a limiting role, and one end of the positioning cylinder 28, which is far away from the folding direction of the paddle, is provided with a uniformly-distributed meshed structure for positioning the paddle 34 before being folded; the compression spring 26 is arranged in a cavity formed by the base 25, the folding actuating cylinder 27 and the positioning cylinder 28 and is always in a compression state;
the second slider joint 23b is slidably connected to the slide rail 24, the second slider joint 23b also has symmetrically arranged lugs, coaxial through holes are formed in the lugs, and the second slider joint 23b is fixedly connected to one end of the folding actuator cylinder 27 close to the blade through the lugs.
Preferably, the number of the slide rail 24 and the first slider joint 23a and the second slider joint 23b slidably engaged therewith is two or more.
In one possible embodiment, the lift system 30 comprises an electric motor 31, a hub 32, a blade folding joint 33, a blade 34, a blade bolt 35, elastic means 36, an elastic structure fixing bolt 37;
the motor 31 outputs power, and an output shaft of the motor passes through the folding control system 20 and is used for mounting and driving the hub to rotate; the hub 32 is fixed on the output shaft of the motor 31 in a sleeved mode, and one end, close to the motor, of the hub 32 is provided with a tooth structure matched with the tooth structure uniformly distributed on the positioning cylinder 28 and used for positioning the blade before the blade is folded; each support arm end of the hub 32 is provided with a double-lug-shaped joint for mounting the blade folding joint 33, one end of the blade folding joint 33 is provided with a single lug, a mounting hole is formed in the single lug, the single lug is mounted on the hub 32 through an elastic structure fixing bolt 37 and can rotate around the elastic structure fixing bolt 3790 degrees, meanwhile, a rocker-arm-shaped boss is relatively and rotatably connected to the single lug, and the blade folding joint 33 can rotate around the elastic structure fixing bolt 37 by pushing the rocker-arm-shaped boss; the other end of the blade folding joint 33 is provided with two lugs, and the blade 34 is fixedly installed through a blade bolt 35;
a small boss is arranged on a lug on one side in the double-lug joint at each arm end of the hub 32, and after the center of the elastic device 36 is installed through the elastic structure fixing bolt 37, two ends with opposite rebound tendencies are respectively fixed on the hub 32 and the blade folding joint 33.
In one possible embodiment, the lift system 30 further includes a fairing 38, the fairing 38 being mounted and secured to the forward end of the hub for fairing of the hub.
Preferably, the cooperating teeth on the positioning cylinder 28 and the hub 32 are circular arc shaped teeth for positioning the blades 34 before folding.
Preferably, the cooperating teeth on the positioning sleeve 28 and the hub 32 are triangular teeth for positioning the blades 34 prior to folding.
Preferably, the elastic device 36 may be a torsion spring.
According to a second aspect of the present invention, a tandem multi-blade tiltrotor aircraft is provided, which includes a plurality of blade folding and collecting rectification structures as described above.
The invention has the beneficial effects that:
the folding, storing and rectifying structure for the blades has the characteristics of simple structure, attractive appearance, high reliability, good rectifying effect after the blades are folded and the like. The folding control system and the lifting system are independently designed and installed, and the structure and the control principle are simpler; the folding control system is buried in the nacelle in design, so that the folding control system has a good rectification effect and attractive appearance; the folding control system and the lift system of the paddle are mutually independent, the complexity of a moving part is less increased, the folding control system and the lift system are mutually crosslinked only when the paddle is folded, the paddle is automatically unfolded when the folding control system is disconnected from the lift system, the folding and the unfolding are mainly realized by a mechanism, the mechanism is simple, and the reliability is high; the appearance integrated design after nacelle is sunken and paddle, guarantee that the paddle can be fine after folding collects in the nacelle, the appearance is pleasing to the eye, has good rectification effect to the paddle after folding, has reduced flight resistance. The invention provides a better solution for folding and collecting the blades at the closed rotor wing units and reducing the drag when the tandem distributed multi-blade tilting wing aircraft flies in an airplane mode, and has important significance for improving the maximum forward flying speed of the aircraft.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so that those skilled in the art can understand and read the present invention, and do not limit the conditions for implementing the present invention, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the functions and purposes of the present invention, should still fall within the scope of the present invention.
FIG. 1 is an overall schematic view of a blade folding and storing rectification structure in the preferred embodiment of the invention
Wherein:
10 nacelle 20 folding control system 30 lift system
FIG. 2 is a schematic view of the unfolding effect of the blades of the preferred embodiment of the present invention
FIG. 3 is a schematic view of the folding, storage and rectification effects of the blades of the preferred embodiment of the invention
FIG. 4 is a schematic diagram of the folding control system 20 according to the preferred embodiment of the present invention
Wherein:
21 steering engine 22a rocker arm 22b connecting rod 23a sliding block joint 23b sliding block joint
24 slide rail 25, base 26, compression spring 27, folding actuator 28 and positioning cylinder
Figure 5 shows a schematic of the folding actuator 27 of the preferred embodiment of the invention
FIG. 6 is a schematic view of the positioning barrel 28 of the preferred embodiment of the present invention
FIG. 7 is a schematic illustration of the structure of a lift system 30 according to a preferred embodiment of the invention
Wherein:
31 motor 32 blade hub 33 blade folding joint 34 blade 35 blade bolt 36 elastic device 37 elastic structure fixing bolt 38 fairing
FIG. 8 is a schematic view of the construction of hub 32 in a preferred embodiment of the invention
FIG. 9 is a schematic view of the structure of a blade folding joint 33 in the preferred embodiment of the present invention
FIG. 10 is a schematic view showing the effect of the unfolded state of the blade in the preferred embodiment of the present invention
FIG. 11 is a schematic diagram illustrating the effect of the positioning state of the blades before folding in the preferred embodiment of the present invention
FIG. 12 is a schematic view showing the effect of the intermediate state of blade folding in the preferred embodiment of the present invention
FIG. 13 is a schematic diagram illustrating the effect of the preferred embodiment of the present invention when the paddles are folded in place
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be construed as limiting the present invention, and the terms "first", "second", "third" are used for descriptive purposes only and are not intended to indicate or imply relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; there may be communication between the interiors of the two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The blade folding, storing and rectifying structure is characterized by comprising a nacelle 10, a folding control system 20 and a lift system 30;
the rear end of the nacelle 10 is connected with the wing, the surface of the nacelle 10 has a recess following the shape of the folded blade in the lift system 30, and the blade can be buried in the recess after being completely folded, as shown in fig. 3;
the folding control system 20 is installed inside the nacelle 10; when blade folding is performed, a mechanical connection is generated between the folding control system 20 and the lift system 30 to realize blade folding in the lift system 30;
when blade folding is performed, a mechanical positioning connection is generated between the folding control system 20 and the lift system 30, and the blades in the lift system 30 are firstly stopped from rotating and are fixed in position.
Example 1
As shown in fig. 4, the folding control system 20 includes a steering engine 21, a rocker arm 22a, a connecting rod 22b, a first slider joint 23a, a second slider joint 23b, a slide rail 24, a base 25, a compression spring 26, a folding actuator cylinder 27, and a positioning cylinder 28;
the steering engine 21 outputs torque according to the control signal requirement and drives the rocker arm 22a to rotate; one end of the rocker arm 22a is actively connected with the steering engine 21, and the other end of the rocker arm is hinged with the connecting rod 22b to drive the connecting rod 22b to move; the connecting rod 22b is hinged to the first sliding block joint 23a and drives the first sliding block joint 23a to move, and the first sliding block joint 23a is connected with the sliding rail 24 in a sliding manner; the slide rail 24 is fixed in the nacelle; the first sliding block joint 23a is further provided with symmetrically arranged lugs, coaxial through holes are formed in the lugs, and the first sliding block joint 23a is fixedly connected with the base 25 through the lugs; the base 25 is circular, a through hole is formed in the center of the base, and a connecting lug piece extends outwards from the edge of the base and is connected with the first slider joint 23a through the connecting lug piece;
the folding actuator cylinder 27 is cylindrical, one end of the folding actuator cylinder is provided with a flange, a plurality of connecting lugs are uniformly distributed on the flange, the connecting lugs on the flange are fixedly connected with the connecting lugs at the corresponding positions of the base 25, and bosses corresponding to the number and the positions of the blades are arranged on the other end surface of the folding actuator cylinder close to the blades and used for pushing the blades to fold in the folding process; a sliding groove is formed in the folding actuating cylinder 27 and used for installing and positioning the positioning cylinder 28; the main body of the positioning cylinder 28 is in a cylindrical shape, a boss is arranged on the outer surface of the circumference of one end of the positioning cylinder 28, which is close to the folding direction of the paddle, and the boss is in sliding fit with a sliding groove in the folding actuating cylinder 27, so that the boss can only move along the sliding groove of the folding actuating cylinder 27 but cannot rotate after being installed, and cannot be separated from the other end of the folding actuating cylinder 27 to play a limiting role, and one end of the positioning cylinder 28, which is far away from the folding direction of the paddle, is provided with a uniformly-distributed meshed structure for positioning the paddle 34 before being folded; the compression spring 26 is arranged in a cavity formed by the base 25, the folding actuating cylinder 27 and the positioning cylinder 28 and is always in a compression state;
the second slider joint 23b is slidably connected to the slide rail 24, the second slider joint 23b also has symmetrically arranged lugs, coaxial through holes are formed in the lugs, and the second slider joint 23b is fixedly connected to one end of the folding actuator cylinder 27 close to the blade through the lugs;
the lift system 30 comprises a motor 31, a hub 32, a blade folding joint 33, a blade 34, a blade bolt 35, an elastic device 36 and an elastic structure fixing bolt 37;
the sliding rails 24 and the first sliding block joints 23a and the second sliding block joints 23b which are in sliding fit with the sliding rails are two groups;
the motor 31 outputs power, and an output shaft of the motor passes through the folding control system 20, so that a hub is installed and is driven to rotate; the hub 32 is fixed on the output shaft of the motor 31 in a sleeved mode, and one end, away from the blades, of the hub 32 is provided with a tooth structure matched with the tooth structure uniformly distributed on the positioning cylinder 28 and used for positioning the hub before the blades are folded; each support arm end of the hub 32 is provided with a double-lug-shaped joint for mounting the blade folding joint 33, one end of the blade folding joint 33 is provided with a single lug, a mounting hole is formed in the single lug, the single lug is mounted on the hub 32 through an elastic structure fixing bolt 37 and can rotate around the elastic structure fixing bolt 3790 degrees, meanwhile, a rocker-arm-shaped boss is relatively and rotatably connected to the single lug, and the blade folding joint 33 can rotate around the elastic structure fixing bolt 37 by pushing the rocker-arm-shaped boss; the other end of the blade folding joint 33 is provided with two lugs, and the blade 34 is fixedly installed through a blade bolt 35;
a small boss is arranged on a lug plate on one side in the double-lug-shaped joint at each arm end of the propeller hub 32, the center of the elastic device 36 is arranged on an elastic structure fixing bolt 37, and the two ends of the elastic device are respectively fixed on the propeller hub 32 and the blade folding joint 33;
the lift system 30 further comprises a fairing 38 mounted at the hub end, the fairing 38 being used for fairing of the hub;
one end of the positioning cylinder 28, which is close to the paddle, is provided with uniformly distributed arc-shaped teeth for positioning the paddle 34 before folding;
the elastic device 36 is a torsion spring.
Example 2
Embodiment 2 differs from embodiment 1 in that the end of the hub 32 remote from the blades has circular arc shaped teeth that mate with equispaced triangular teeth on the positioning cylinder 28;
the elastic device 36 is a torsion spring.
Example 3
A tandem multi-paddle aircraft with tilting wings is provided with a plurality of distributed blades, and each blade comprises the blade folding, storing and rectifying structure.
As shown in fig. 10-13, when the blade is folded, the steering engine 21 in the folding control system 20 drives the rocker arm 22a and the connecting rod 22b to make the first slider joint 23a, the second slider joint 23b drive the folding actuator 27 and the positioning cylinder 28 to slide along the slide rail 24, and first, the meshing structure that is mutually matched with the positioning cylinder 28 and the hub 32 is engaged, so that the blade stops rotating and is positioned; when the folding actuating cylinder 27 is further driven to push the rocker-shaped boss of the blade folding joint 33, the blade folding joint 33 and the blade 34 rotate for 90 degrees around the elastic structure fixing bolt 37 to realize folding;
when the blade is unfolded, the steering engine 21 in the folding control system 20 drives the folding actuating cylinder 27 and the positioning cylinder 28 to move in the direction opposite to the folding direction of the blade, and when the mechanical connection between the folding control system 20 and the lift system 30 is disconnected, the elastic device 36 utilizes the self elastic force to enable the folding joint 33 of the blade and the blade 34 to be in an unfolded state.
The folding, storing and rectifying structure for the blades has the characteristics of simple structure, attractive appearance, high reliability, good rectifying effect after the blades are folded and the like. The folding control system and the lifting system are independently designed and installed, and the structure and the control principle are simpler; the folding control system is buried in the nacelle in design, has good rectification effect and attractive appearance; the folding control system and the lift system of the paddle are mutually independent, the complexity of a moving part is less increased, the folding control system and the lift system are mutually crosslinked only when the paddle is folded, the paddle is automatically unfolded when the folding control system is disconnected from the lift system, the folding and the unfolding are mainly realized by a mechanism, the mechanism is simple, and the reliability is high; the appearance integrated design after nacelle is sunken and paddle, guarantee that the paddle can be fine after folding collects in the nacelle, the appearance is pleasing to the eye, has good rectification effect to the paddle after folding, has reduced flight resistance.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. The blade folding, storing and rectifying structure is characterized by comprising a nacelle (10), a folding control system (20) and a lift system (30);
the rear end of the nacelle (10) is connected with the wings, the surface of the nacelle (10) is provided with a recess which follows the shape of the folded blade in the lift system (30), and the blade can be buried in the recess after being completely folded; the folding control system (20) is arranged inside the nacelle (10); when blade folding is performed, a mechanical connection is generated between the folding control system (20) and the lift system (30) so as to realize blade folding in the lift system (30); when the mechanical connection between the folding control system (20) and the lift system (30) is disconnected, the blades in the lift system (30) will return to the unfolded and rotated state;
the folding control system (20) comprises a steering engine (21), a rocker arm (22 a), a connecting rod (22 b), a first sliding block joint (23 a), a second sliding block joint (23 b), a sliding rail (24), a base (25), a compression spring (26), a folding actuating cylinder (27) and a positioning cylinder (28); the steering engine (21) outputs torque according to the control signal requirement and drives the rocker arm (22 a) to rotate;
one end of the rocker arm (22 a) is actively connected with the steering engine (21), and the other end of the rocker arm is hinged with the connecting rod (22 b) to drive the connecting rod (22 b) to move; the connecting rod (22 b) is hinged with the first sliding block joint (23 a) and drives the first sliding block joint (23 a) to move, and the first sliding block joint (23 a) is connected with the sliding rail (24) in a sliding mode; the sliding rail (24) is fixed in the nacelle; the first sliding block joint (23 a) is also provided with symmetrically arranged lugs, coaxial through holes are formed in the lugs, and the first sliding block joint (23 a) is fixedly connected with the base (25) through the lugs; the base (25) is annular, a through hole is formed in the center of the base, a connecting lug piece extends outwards from the edge of the base, and the base is connected with the first sliding block joint (23 a) through the connecting lug piece;
the folding actuator cylinder (27) main body is cylindrical, one end of the folding actuator cylinder is provided with a flanging, a plurality of connecting lugs are uniformly distributed on the flanging, the connecting lugs on the flanging are fixedly connected with the connecting lugs at the corresponding positions of the base (25), and bosses corresponding to the number and the positions of the blades are arranged on the other end surface of the folding actuator cylinder close to the blades and used for pushing the blades to fold in the folding process; a sliding groove is formed in the folding actuating cylinder (27) and used for installing and positioning the positioning cylinder (28); the main body of the positioning cylinder (28) is in a cylindrical shape, a boss is arranged on the outer surface of the circumference of one end, close to the folding direction of the paddle, of the positioning cylinder, the boss is in sliding fit with a sliding groove in the folding actuating cylinder (27), so that the positioning cylinder can only move along the sliding groove of the folding actuating cylinder (27) but cannot rotate after being installed, and cannot be separated from the other end of the folding actuating cylinder (27) to play a limiting role, and one end, far away from the folding direction of the paddle, of the positioning cylinder (28) is provided with a uniformly distributed meshed structure for positioning the paddle (34) before being folded; the compression spring (26) is arranged in a cavity formed by the base (25), the folding actuating cylinder (27) and the positioning cylinder (28) and is always in a compression state;
the second sliding block joint (23 b) is connected with the sliding rail (24) in a sliding mode, the second sliding block joint (23 b) is also provided with symmetrically-arranged lugs, coaxial through holes are formed in the lugs, and the second sliding block joint (23 b) is fixedly connected with one end, close to the blade, of the folding actuating cylinder (27) through the lugs;
the lift system (30) comprises a motor (31), a hub (32), a blade folding joint (33), a blade (34), a blade bolt (35), an elastic device (36) and an elastic structure fixing bolt (37);
the motor (31) outputs power, and an output shaft of the motor penetrates through the folding control system (20) and is used for mounting a hub and driving the hub to rotate; the propeller hub (32) is fixedly sleeved on an output shaft of the motor (31), and one end, close to the motor, of the propeller hub (32) is provided with a tooth structure matched with the uniformly distributed tooth structure on the positioning cylinder (28) and used for positioning the blade before the blade is folded; each support arm end of the hub (32) is provided with a double-lug-shaped joint for mounting the blade folding joint (33), one end of the blade folding joint (33) is provided with a single lug, a mounting hole is formed in the single lug, the blade folding joint is mounted on the hub (32) through an elastic structure fixing bolt (37) and can rotate around the elastic structure fixing bolt (37) for 90 degrees, meanwhile, a rocker-shaped boss is connected to the single lug in a relatively rotating mode, and the blade folding joint (33) can rotate around the elastic structure fixing bolt (37) by pushing the rocker-shaped boss; the other end of the blade folding joint (33) is provided with two lugs, and the blade (34) is installed and fixed through a blade bolt (35); and a small boss is arranged on a lug at one side in the double-lug joint at each arm end of the hub (32), and after the center of the elastic device (36) is installed through the elastic structure fixing bolt (37), two ends with opposite rebound tendency are respectively fixed on the hub (32) and the blade folding joint (33).
2. A blade folding stowage fairing according to claim 1, wherein when blade folding is performed, a mechanical positioning connection is created between the folding control system (20) and the lift system (30), the blades in the lift system (30) are first stopped from rotating and fixed in position.
3. The blade folding and stowing fairing structure as recited in claim 1, wherein the number of the sliding rails (24) and the first slider joints (23 a) and the second slider joints (23 b) slidably engaged therewith is two or more than three.
4. The blade folding stowage fairing structure of claim 1 wherein said lift system (30) further comprises a fairing (38), said fairing (38) being fixedly mounted to said hub forward end for fairing drag reduction of the hub.
5. A blade folding stowage fairing according to claim 1, wherein the cooperating teeth on the positioning cylinder (28) and the hub (32) are rounded teeth for positioning the blade (34) before folding.
6. A blade folding stowage fairing according to claim 1, wherein the cooperating teeth on the positioning cylinder (28) and the hub (32) are triangular teeth for positioning the blade (34) before folding.
7. A blade-folding stowage fairing as recited in claim 1, wherein said resilient means (36) is selected from a torsion spring.
8. A tandem multi-paddle tiltrotor wing aircraft comprising a plurality of blade folding stowage fairing arrangements as claimed in any one of claims 1 to 7.
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| CN112918671B (en) * | 2021-04-07 | 2022-04-26 | 北京航空航天大学 | Automatic rotor wing folding system for tandem double-rotor helicopter |
| CN113443132B (en) * | 2021-07-29 | 2023-01-31 | 上海交通大学 | Miniature longitudinal reverse dual-rotor aircraft |
| IL286211B1 (en) * | 2021-09-09 | 2024-04-01 | Israel Aerospace Ind Ltd | Propulsion system |
| CN113942636A (en) * | 2021-11-16 | 2022-01-18 | 深圳市龙云创新航空科技有限公司 | Composite rotor craft |
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