CN111498099A - Stepped propeller hub system for rotary wing aircraft - Google Patents
Stepped propeller hub system for rotary wing aircraft Download PDFInfo
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- CN111498099A CN111498099A CN202010370492.9A CN202010370492A CN111498099A CN 111498099 A CN111498099 A CN 111498099A CN 202010370492 A CN202010370492 A CN 202010370492A CN 111498099 A CN111498099 A CN 111498099A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention provides a stepped hub system for a rotary wing aircraft, which is divided into an upper hub system and a lower hub system; the propeller hub system main body structure is fixedly arranged at the upper part of a rotor wing main shaft of a rotary wing aircraft, is used for installing a main propeller blade and realizes the transmission and variable pitch functions of the main propeller blade; the lower propeller hub system is arranged on a rotor wing main shaft of the rotary wing aircraft, is positioned at the lower part of the main body structure of the upper propeller hub system, and is used for installing auxiliary blades and realizing the transmission and variable pitch functions of the auxiliary blades; the lower propeller hub system can control the auxiliary propeller blades to move axially along the main shaft after the main shaft of the rotor wing is locked, and limit the axial in-place positions of the auxiliary propeller blades; when the auxiliary blade moves in place from top to bottom along the axial direction of the main shaft, the auxiliary blade is integrally fused into the fuselage of the rotary wing aircraft. The invention realizes the requirement of the fusion of the auxiliary blade and the aircraft body and can ensure that the auxiliary blade does not interfere the flight in the fixed wing flight stage.
Description
Technical Field
The invention relates to a stepped propeller hub system design of a rotary wing aircraft, which is suitable for a heavy-load rotary wing aircraft.
Background
The rotary wing airplane is a novel manned/unmanned airplane with vertical take-off and landing performance of a helicopter and high-speed cruising performance of a fixed wing airplane, and the Chinese patent with the patent number of Z L201110213680.1 and the name of 'a rotary wing airplane with variable flight modes' is a typical airplane type.
In order to effectively improve the load carrying capacity and the maximum takeoff weight of a rotary wing airplane, a four-blade rotary wing is provided, for example, Chinese patent of Z L201910189236.7, namely a four-blade rotary wing, a rotary wing airplane and a control method.
Disclosure of Invention
Technical problem to be solved
After further theoretical calculation, wind tunnel test and model test flight verification, we find that, in the fixed-wing flight stage of the four-blade rotary wing aircraft, the main blades are perpendicular to the symmetrical plane of the aircraft body, the auxiliary blades are distributed along the longitudinal symmetrical plane of the aircraft body, at the moment, the auxiliary blades along the longitudinal symmetrical plane of the aircraft body generate airflow interference with the upper surface of the aircraft body, the resistance is increased, the inflow of the main blades playing the role of the fixed wing is influenced, in addition, as the auxiliary blades along the longitudinal symmetrical plane of the aircraft body are of a long and thin structure, stronger vibration can be generated in the fixed-wing flight stage, and the flight resistance in the cruise stage can be further increased.
Technical scheme
In order to solve the above problems, the present invention provides a stepped hub system for a rotary wing aircraft, which is divided into an upper hub system and a lower hub system on the premise of meeting the flight control requirements of the rotary wing aircraft at each stage, wherein the upper hub system realizes the transmission and pitch changing functions of a main blade, the lower hub system realizes the transmission and pitch changing functions of an auxiliary blade, and the lower hub system can axially move the auxiliary blade along a main shaft in a locked state of the main shaft to meet the requirement of the integration of the auxiliary blade and a fuselage, so that the fixed wing aircraft can ensure that the auxiliary blade does not interfere with the flight at the stage.
The technical scheme of the invention is as follows:
the stepped hub system for a rotary wing aircraft is characterized in that: the system comprises an upper propeller hub system and a lower propeller hub system;
the upper propeller hub system main body structure is fixedly arranged at the upper part of a rotor wing main shaft of the rotary wing aircraft, is used for installing two main propeller blades in the rotary wing aircraft and realizes the transmission and variable pitch functions of the main propeller blades; the main blades are a pair of blades which are vertical to the longitudinal symmetrical plane of the rotary wing aircraft when the rotary wing aircraft is in a fixed wing flight mode;
the lower propeller hub system is arranged on a rotor wing main shaft of the rotary wing aircraft, is positioned at the lower part of the main body structure of the upper propeller hub system, and is used for installing two auxiliary blades in the rotary wing aircraft and realizing the transmission and pitch changing functions of the auxiliary blades; the auxiliary blades are a pair of blades which are positioned along the longitudinal symmetrical plane of the airplane body when the rotary wing airplane is in a fixed wing flight mode;
the lower propeller hub system can control the auxiliary propeller blades to move axially along the main shaft after the rotor main shaft of the rotary wing aircraft is locked, and limit the axial in-place positions of the auxiliary propeller blades; when the auxiliary blade moves in place from top to bottom along the axial direction of the main shaft, the auxiliary blade is integrally fused into the fuselage of the rotary wing aircraft.
Furthermore, the lower hub system comprises a sliding actuator, a lower hub, an upper stopper, a lower stopper and a lower hub pitch changer; the lower propeller hub is matched with the rotor main shaft through a spline along the axial direction of the rotor main shaft, and the rotor main shaft can drive the lower propeller hub to rotate through the spline; when the rotor main shaft is locked, the lower propeller hub can move axially along the spline under the driving of the sliding actuator, and the upper in-place and the lower in-place limitation is realized under the constraint of the upper limiting block and the lower limiting block; lower propeller hub displacement ware realizes vice paddle displacement, and can cooperate the slip actuator to realize lower propeller hub along spline axial displacement.
Furthermore, the bottom of the lower propeller hub is provided with a transition structure matched with the sliding actuator, so that the sliding actuator can drive the lower propeller hub to axially move along the spline, and the body of the sliding actuator does not rotate along with the lower propeller hub.
Furthermore, the transition structure at the bottom of the lower propeller hub is a circular sliding groove structure, and the actuating end of the sliding actuator is positioned in the circular sliding groove, so that the lower propeller hub can be driven to move axially along the spline, and can also slide relative to the lower propeller hub when the lower propeller hub rotates.
Further, the lower hub is in the form of a bearingless hub with a flexible beam structure; the variable-pitch outer sleeves are sleeved at the two ends of the flexible beam, and the outer ends of the variable-pitch outer sleeves are connected with the auxiliary blades through blade mounting seats; the lower propeller hub pitch changer is connected to the pitch-changing outer sleeve to realize the pitch changing of the auxiliary propeller blades.
Furthermore, the lower propeller hub distance changer comprises a distance changing actuator, a fixed disc, a movable disc, a distance changing connecting rod and a lower propeller hub distance changing rocker arm; when the lower propeller hub moves from bottom to top, the lower propeller hub and the fixed disc move upwards along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; after the lower propeller hub slides to reach the constraint position of the upper limiting block, the sliding actuator stops acting, the variable-pitch actuator can control the total pitch of the auxiliary propeller blades, and the upper limiting block transmits the lifting force generated by the auxiliary propeller blades to the rotor main shaft.
Furthermore, the lower propeller hub distance changer is provided with at least 3 distance changing actuators, and the fixed disc and the movable disc are matched with the rotating main shaft through spherical hinges, so that the distance changing actuators can operate and control the total distance changing and the periodic distance changing of the auxiliary propeller blades.
Further, the rotor main shaft adopts a hollow shaft; an upper hub automatic inclinator in the upper hub system is positioned at the lower part of the lower hub system and is positioned in the machine body; and the upper propeller hub system adopts a long connecting rod positioned in the rotor spindle to realize the connection between a structure positioned at the upper part of the rotor spindle in the upper propeller hub system and an automatic propeller hub inclinator positioned in the fuselage.
Advantageous effects
Aiming at the requirements of improving the load capacity and the maximum takeoff weight of the rotary wing aircraft, the invention provides a stepped propeller hub system on the basis of the concept of the four-blade rotary wing aircraft, and the lower propeller hub capable of axially moving is designed, so that the auxiliary propeller blades can be fused with the aircraft body in a fixed wing flight mode, and the disturbance and the resistance of the auxiliary propeller blades in the fixed wing flight mode are greatly reduced.
In addition, by designing the stepped hub system, the main blades are arranged upwards, the auxiliary blades are arranged downwards, the auxiliary blades have the effect equivalent to a main blade lifting device, the total pitch of the auxiliary blades can be lifted under the condition of large load to bear more than half of pulling force, and effective support is provided for helicopter mode flight of the rotary wing aircraft.
Meanwhile, due to the design of the stepped propeller hub system, the rotary wing aircraft can be subjected to redundant control in the takeoff and landing control, the pitching control and the rolling control of a helicopter mode, and the safety margin of the system is improved.
In addition, in the invention, the automatic inclinators for realizing the pitch changing functions of the upper hub and the lower hub are both arranged in the fuselage, thereby reducing the resistance of the rotary wing aircraft in flight.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
figure 1 is a schematic view of a stepped hub;
wherein: 1. an upper hub system, 2 a lower hub system;
FIG. 2 is an example planform of a main blade;
FIG. 3 is an example planform of a secondary blade;
fig. 4 is a schematic view of the upper hub structure;
wherein: 3, a propeller clamp, 4, a variable pitch hinge shell, 5 pull torsion bars, 6 needle roller bearings, 7 upper propeller hubs, 8 long connecting rods, 9 steering plates, 10 variable pitch pull rods, 11 elastic hinges, 12 propeller hub clamping plates, 13 swing hinges, 14 upper propeller hub variable pitch rocker arms and 15 propeller hub supporting arms;
figure 5 is a schematic view of the lower hub construction;
wherein: 16 blade mounting seats, 17 variable-pitch outer sleeves, 18 upper limiting blocks, 19 splines, 20 hub flexible beams, 21 lower hub variable-pitch rocker arms, 22 lower limiting blocks, 23 variable-pitch connecting rods, 24 movable discs, 25 fixed discs, 26 sliding actuators and 27 variable-pitch actuators;
FIG. 6 is a schematic representation of an all-aircraft aerodynamic layout of an aircraft having stepped hub rotor wings, shown without the inclusion of a pilot control surface;
in the figure: 28 fuselages, 29 canard wings, 30 horizontal tails, 31 vertical tails, 32 forward-pulling propellers, 33 four-blade rotary wings, 34 landing gears and 35 tail propellers.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The embodiment provides a stepped hub system applied to a rotary wing aircraft with a four-blade rotary wing. As shown in fig. 1, the stepped hub system is divided into an upper hub system and a lower hub system.
As shown in fig. 1, the upper hub system main body structure is fixedly installed at the top of a rotor main shaft of a rotary wing aircraft, and is used for installing two main blades in the rotary wing aircraft and realizing the transmission and pitch-changing functions of the main blades. The main blades are a pair of blades which are vertical to the longitudinal symmetrical plane of the rotary wing aircraft when the rotary wing aircraft is in a fixed wing flight mode. The blade section of the main blade adopts a symmetrical airfoil design at the front edge and the rear edge, the plane shape of the blade adopts a symmetrical design in the downstream direction, such as an elliptical paddle, a trapezoid, a rectangle and the like, and as shown in figure 2, when the rotary wing aircraft is in a fixed wing flight mode, the main blade serves as an intermediate airfoil surface.
As shown in fig. 4, in this embodiment, the main structure of the upper hub system installed on the top of the rotor shaft includes a paddle clip 3, a pitch-variable hinge housing 4, a pull-torsion bar 5, a needle bearing 6, an upper hub 7, a long link 8, a steering plate 9, a pitch-variable pull bar 10, an elastic hinge 11, a hub clamping plate 12, a flapping hinge 13, an upper hub pitch-variable rocker arm 14, and a hub arm 15.
Wherein, the upper hub 7 adopts a seesaw type hub with elastic constraint; hub clamp 12 connects hub arms 15 on opposite sides of the hub to enable up and down flapping about flapping hinge 13, and elastic hinge 11 provides elastic restraint to the flapping motion to increase rotor handling torque. The paddle clamp 3 adopts a pull-torsion rod type paddle clamp, the pull-torsion rod 5 is arranged in a paddle hub support arm 15, one end of the pull-torsion rod is connected with the variable-pitch hinge shell 4, and the other end of the pull-torsion rod is connected with the upper paddle hub 7 to bear centrifugal force and variable-pitch torsion, so that the structure reduces the using number of bearings, and reduces the number of parts, the maintenance complexity and the lubrication problem; the pitch hinge housing 4 is mounted on the hub arm 15 by means of needle bearings 6 for transmitting torque in the plane of rotation of the upper hub.
In order to reduce resistance and match with the installation space of the lower propeller hub, an operating system of the upper propeller hub system adopts in-shaft operation, namely, a pitch-variable hinge shell is connected with a pitch-variable pull rod through a pitch-variable rocker arm, the pitch-variable pull rod is connected with a long connecting rod in a hollow rotating main shaft through a steering plate, the long connecting rod is connected with an upper propeller hub automatic inclinator which is positioned at the lower part of the lower propeller hub system and in the machine body, and the pitch-variable control of the main propeller blades is realized through the upper propeller hub automatic inclinator.
As shown in fig. 1, the lower hub system is installed on a rotor main shaft of a rotary wing aircraft, is located at the lower part of a main body structure of the upper hub system, and is used for installing two auxiliary blades in the rotary wing aircraft and realizing the transmission and pitch changing functions of the auxiliary blades. The auxiliary blades are a pair of blades which are positioned along the longitudinal symmetrical plane of the airplane body when the rotary wing airplane is in a fixed wing flight mode. The profile of the auxiliary blade adopts a rotor wing profile meeting the performance requirements of the helicopter rotor, and the auxiliary blade has higher rotor aerodynamic efficiency and lighter structural weight than the main blade, as shown in fig. 3.
The lower propeller hub system can control the auxiliary propeller blades to move axially along the main shaft after the rotor main shaft of the rotary wing aircraft is locked, and limit the axial in-place positions of the auxiliary propeller blades; when the auxiliary blades move in place from top to bottom along the axial direction of the main shaft, the auxiliary blades are integrally fused into the fuselage of the rotary wing aircraft, so that disturbance of the auxiliary blades in a fixed wing flight mode is avoided, and resistance is reduced.
As shown in fig. 5, in the present embodiment, the lower hub system includes a sliding actuator, a lower hub, an upper stopper, a lower stopper, and a lower hub torque converter.
The lower propeller hub is matched with the rotor main shaft through a spline along the axial direction of the rotor main shaft, and the rotor main shaft can drive the lower propeller hub to rotate through the spline; when the rotor main shaft is locked, the lower propeller hub can move axially along the spline under the driving of the sliding actuator, and the upper in-place and the lower in-place limitation is realized under the constraint of the upper limiting block and the lower limiting block; lower propeller hub displacement ware realizes vice paddle displacement, and can cooperate the slip actuator to realize lower propeller hub along spline axial displacement.
In this embodiment, the lower hub is in the form of a bearingless hub with a flexible beam structure; the variable-pitch outer sleeves are sleeved at the two ends of the flexible beam, and the outer ends of the variable-pitch outer sleeves are connected with the auxiliary blades through blade mounting seats; the lower propeller hub pitch changer is connected to the pitch-changing outer sleeve to realize the pitch changing of the auxiliary propeller blades.
The lower propeller hub distance changer comprises a distance changing actuator, a fixed disc, a movable disc, a distance changing connecting rod and a lower propeller hub distance changing rocker arm.
When the lower propeller hub moves from bottom to top, the lower propeller hub and the fixed disc move upwards along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; after the lower propeller hub slides to reach the constraint position of the upper limiting block, the sliding actuator stops acting, the variable-pitch actuator can control the auxiliary propeller blades to change the total pitch by driving the fixed disc and the movable disc to move, and the upper limiting block transmits the lifting force generated by the auxiliary propeller blades to the rotor main shaft. In other words, as shown in fig. 5, in this case, the lower hub pitch changer has only two pitch actuators, and can realize total pitch change of the secondary blades, but cannot realize periodic pitch change, and the relative structure is simple, and at this time, the rotary wing controls the main blades through the upper hub automatic tilter to realize periodic pitch change operation.
Of course, the lower hub pitch changer may also have at least 3 pitch actuators, and the fixed disk and the movable disk are coupled to the rotating main shaft through ball joints, so that the pitch actuators can control the collective pitch and the cyclic pitch of the auxiliary blades.
When the lower propeller hub moves from top to bottom, the lower propeller hub and the fixed disc move downwards along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; after the lower propeller hub slides to reach the lower limiting block restraining position, the sliding actuator and the variable-pitch actuator stop acting, and the auxiliary propeller blades are integrally blended into the fuselage of the rotary wing aircraft.
In addition, in order to isolate the rotary motion of the lower propeller hub from the sliding actuator body, a transition structure matched with the sliding actuator is arranged at the bottom of the lower propeller hub, specifically, a circular sliding groove structure can be adopted, and the actuating end of the sliding actuator is positioned in the circular sliding groove, so that the lower propeller hub can be driven to move axially along the spline, and can also slide relative to the lower propeller hub when the lower propeller hub rotates. In addition, a fixed disk structure similar to that of an automatic tilter can be adopted to realize that the rotating motion of the lower propeller hub is isolated from the sliding actuator body.
Fig. 6 shows a high-load and high-takeoff-weight rotary wing aircraft with four blades and adopting the stepped hub proposed by the embodiment, which comprises a fuselage, a canard wing arranged at the front part in the longitudinal direction of the fuselage, a four-blade rotary wing arranged at the middle part in the longitudinal direction of the fuselage, an empennage arranged at the tail part in the longitudinal direction of the fuselage, a propeller arranged on the fuselage and used for providing forward flight power of the rotary wing aircraft, a counter-torque device arranged on the fuselage, a power system and a flight control system arranged in the fuselage, and a landing gear arranged at the lower.
The canard provides partial lift during the fixed wing mode flight phase and the transition flight phase of the rotary wing aircraft, and provides the pitching and/or rolling maneuvering and/or balancing moment in some way, such as full-motion canard, canard control surface and the like; the horizontal tail in the empennage provides partial lift during the fixed wing flight phase as well as the transition flight phase of the rotary wing aircraft and provides, in some way, a steering and/or balancing moment for pitch and/or roll, such as a full-motion horizontal tail, a horizontal tail rudder, etc. And at least one vertical tail fin should be present in the tail fin in order to ensure the heading steering capability of the aircraft. The form of the tail may take many forms, such as a T-shaped tail, an H-shaped tail, etc.
The rotor wing with stepped hub provides all pulling force in helicopter mode flight, the main blades are locked in fixed wing mode flight, the locked main blades are perpendicular to the longitudinal symmetrical plane of the rotor wing airplane and provide partial lift force in fixed wing mode flight. The auxiliary blades descend to the lowest point in the fixed wing mode flight phase and are integrated with the airplane body, so that the resistance is reduced.
The propeller for providing the forward flying power of the rotary wing aircraft can be a forward-pulling variable pitch propeller arranged at the head of the aircraft body, but considering that the forward-pulling propeller does not work in the helicopter mode flying stage and the tail rotor does not work in the fixed wing mode flying stage, the forward-pulling propeller and the tail rotor can be combined into a tail rotor with variable thrust direction, the thrust tail rotor moves according to a specific rule to change the thrust direction, and the reverse torque in the helicopter mode and the thrust required by the flight in the fixed wing mode can be provided.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (8)
1. A stepped hub system for a rotary wing aircraft, comprising: the system comprises an upper propeller hub system and a lower propeller hub system;
the upper propeller hub system main body structure is fixedly arranged at the upper part of a rotor wing main shaft of the rotary wing aircraft, is used for installing two main propeller blades in the rotary wing aircraft and realizes the transmission and variable pitch functions of the main propeller blades; the main blades are a pair of blades which are vertical to the longitudinal symmetrical plane of the rotary wing aircraft when the rotary wing aircraft is in a fixed wing flight mode;
the lower propeller hub system is arranged on a rotor wing main shaft of the rotary wing aircraft, is positioned at the lower part of the main body structure of the upper propeller hub system, and is used for installing two auxiliary blades in the rotary wing aircraft and realizing the transmission and pitch changing functions of the auxiliary blades; the auxiliary blades are a pair of blades which are positioned along the longitudinal symmetrical plane of the airplane body when the rotary wing airplane is in a fixed wing flight mode;
the lower propeller hub system can control the auxiliary propeller blades to move axially along the main shaft after the rotor main shaft of the rotary wing aircraft is locked, and limit the axial in-place positions of the auxiliary propeller blades; when the auxiliary blade moves in place from top to bottom along the axial direction of the main shaft, the auxiliary blade is integrally fused into the fuselage of the rotary wing aircraft.
2. The stepped hub system of claim 1, wherein: the lower propeller hub system comprises a sliding actuator, a lower propeller hub, an upper limiting block, a lower limiting block and a lower propeller hub distance changer; the lower propeller hub is matched with the rotor main shaft through a spline along the axial direction of the rotor main shaft, and the rotor main shaft can drive the lower propeller hub to rotate through the spline; when the rotor main shaft is locked, the lower propeller hub can move axially along the spline under the driving of the sliding actuator, and the upper in-place and the lower in-place limitation is realized under the constraint of the upper limiting block and the lower limiting block; lower propeller hub displacement ware realizes vice paddle displacement, and can cooperate the slip actuator to realize lower propeller hub along spline axial displacement.
3. The stepped hub system of claim 2, wherein: the bottom of the lower propeller hub is provided with a transition structure matched with the sliding actuator, so that the sliding actuator can drive the lower propeller hub to axially move along the spline, and the sliding actuator body does not rotate along with the lower propeller hub.
4. The stepped hub system of claim 3, wherein: the transition structure of lower propeller hub bottom is circular spout structure, and the sliding actuator actuates the end and is located circular spout, can drive lower propeller hub along spline axial displacement, also can slide relative lower propeller hub when lower propeller hub rotates.
5. The stepped hub system for a rotary wing aircraft of claim 2 or 3, wherein: the lower propeller hub is in a bearing-free propeller hub form with a flexible beam structure; the variable-pitch outer sleeves are sleeved at the two ends of the flexible beam, and the outer ends of the variable-pitch outer sleeves are connected with the auxiliary blades through blade mounting seats; the lower propeller hub pitch changer is connected to the pitch-changing outer sleeve to realize the pitch changing of the auxiliary propeller blades.
6. The stepped hub system of claim 2, wherein: the lower propeller hub distance changer comprises a distance changing actuator, a fixed disc, a movable disc, a distance changing connecting rod and a lower propeller hub distance changing rocker arm; when the lower propeller hub moves from bottom to top, the lower propeller hub and the fixed disc move upwards along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; after the lower propeller hub slides to reach the constraint position of the upper limiting block, the sliding actuator stops acting, the variable-pitch actuator can control the total pitch of the auxiliary propeller blades, and the upper limiting block transmits the lifting force generated by the auxiliary propeller blades to the rotor main shaft.
7. The stepped hub system of claim 6, wherein: the lower propeller hub pitch changer is provided with at least 3 pitch actuators, and the fixed disc and the movable disc are matched with the rotating main shaft through the spherical hinge, so that the pitch actuators can control the total pitch and the periodic pitch of the auxiliary propeller blades.
8. The stepped hub system for a rotary wing aircraft of claim 1 or 6, wherein: the rotor main shaft adopts a hollow shaft; an upper hub automatic inclinator in the upper hub system is positioned at the lower part of the lower hub system and is positioned in the machine body; and the upper propeller hub system adopts a long connecting rod positioned in the rotor spindle to realize the connection between a structure positioned at the upper part of the rotor spindle in the upper propeller hub system and an automatic propeller hub inclinator positioned in the fuselage.
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| CN202010370492.9A CN111498099B (en) | 2020-05-04 | 2020-05-04 | Stepped propeller hub system for rotary wing aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN113942639A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade droop limiter, upper swing limiter and swing limiting system |
| CN115783243A (en) * | 2021-09-09 | 2023-03-14 | 中国科学院沈阳自动化研究所 | Rotor unmanned aerial vehicle hub system verts |
| CN116280188B (en) * | 2023-04-18 | 2024-05-28 | 安阳市豪克航空科技有限公司 | Bearingless variable-pitch propeller |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113460299B (en) * | 2021-09-02 | 2021-11-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN115783243A (en) * | 2021-09-09 | 2023-03-14 | 中国科学院沈阳自动化研究所 | Rotor unmanned aerial vehicle hub system verts |
| CN113942639A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Helicopter blade droop limiter, upper swing limiter and swing limiting system |
| CN113942639B (en) * | 2021-10-09 | 2023-05-05 | 中国直升机设计研究所 | Centrifugal blade swing limiting system of helicopter |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN113753261B (en) * | 2021-11-09 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN116280188B (en) * | 2023-04-18 | 2024-05-28 | 安阳市豪克航空科技有限公司 | Bearingless variable-pitch propeller |
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