CN110435877A - A kind of adaptive pneumatic variable-pitch propeller - Google Patents
A kind of adaptive pneumatic variable-pitch propeller Download PDFInfo
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- CN110435877A CN110435877A CN201910818204.9A CN201910818204A CN110435877A CN 110435877 A CN110435877 A CN 110435877A CN 201910818204 A CN201910818204 A CN 201910818204A CN 110435877 A CN110435877 A CN 110435877A
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- 230000003044 adaptive effect Effects 0.000 title claims abstract description 17
- 239000011295 pitch Substances 0.000 description 20
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
- B64C11/34—Blade pitch-changing mechanisms mechanical automatic
- B64C11/343—Blade pitch-changing mechanisms mechanical automatic actuated by the centrifugal force or the aerodynamic drag acting on the blades
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- Engineering & Computer Science (AREA)
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- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The embodiment of the present invention is about a kind of adaptive pneumatic variable-pitch propeller.The propeller includes: propeller hub；At least two blades, the blade include main part and taper, which is rotatably dispose on the propeller hub；Wherein, the taper of the blade is negative twisted tip；The taper has the deflection of a predetermined angle relative to main part in the horizontal direction；And/or the taper has the offset of a pre-determined distance relative to main part in the horizontal direction.The embodiment of the present invention is by the way that the main part of blade to be rotatably dispose on the propeller hub, and set the blade tips to the taper that there is angle of negative torsion degree and deflect or deviate relative to main part, the blade can the aerodynamic moment according to caused by corresponding direction of flow automatically rotate to adjust operating angle of attack, so that longitudinal trim condition that it is zero in aerodynamic moment that the blade, which can be stablized, so that propeller can all have preferable vane efficiency in wider flight envelope.
Description
Technical Field
The embodiment of the invention relates to the technical field of propellers, in particular to a self-adaptive pneumatic variable-pitch propeller.
Background
At present, the screw of fixed wing aircraft has distance screw and variable pitch screw, the pitch of distance screw is fixed, different pitches can only possess better efficiency under specific advance than, its forward that adapts to is narrower than the operating mode, and the variable pitch screw can adjust the pitch, thereby make the screw all have higher efficiency under comparing in the wider forward range of distance screw, variable pitch screw among the prior art adopts the angle of displacement mechanism control blade usually, for example, fluid pressure type variable pitch screw, blade slewing mechanism in this screw is promoted by lubricating oil pressure, rotate with the angle that drives the blade, thereby make the screw all have higher efficiency under the rotational speed of difference.
However, the pitch-varying mechanism is used to control the angle of the blade, and the propeller needs to be equipped with a complicated pitch-varying mechanism, so that the pitch-varying mechanism is usually complex and precise to accurately control the angle of the blade, and brings about a small cost for production cost and maintenance cost. In addition, the pitch mechanism also brings extra weight, so that the power density of the whole power system is reduced. Accordingly, there is a need to ameliorate one or more of the problems with the related art solutions described above.
It is noted that this section is intended to provide a background or context to the embodiments of the invention that are recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
Disclosure of Invention
It is an object of embodiments of the present invention to provide an adaptive pneumatic variable pitch propeller that overcomes, at least to some extent, one or more of the problems due to limitations and disadvantages of the related art.
According to an aspect of an embodiment of the present invention, there is provided an adaptive aerodynamic pitch propeller, the propeller comprising:
a hub;
at least two blades, the blades including a main body portion and a tip portion, the main body portion rotatably disposed on the hub; wherein,
the tip of the blade is a negative torsion tip;
the tip part deflects relative to the main body part by a preset angle in the horizontal direction; and/or the tip portion is offset in a horizontal direction by a predetermined distance relative to the main body portion.
In an embodiment of the present invention, a blade shaft is disposed at a root of the main body portion of the blade, a shaft hole matched with the blade shaft is disposed on a circumferential side wall of the hub, the blade is disposed on the hub by inserting the blade shaft into the shaft hole, and the blade can rotate around an axis of the blade shaft, so that the blade is in a balanced state.
In an embodiment of the present invention, the blade shaft and the shaft hole are connected through an elastic member, so that an elastic moment generated by deformation of the elastic member and an aerodynamic moment of the blade under different working conditions are balanced, so that the blade is in a balanced state.
In an embodiment of the present invention, the blade is located at a first preset position under a first working condition, and rotates to a second preset position under a second working condition, and an included angle between the first preset position and the second preset position is a preset angle.
In an embodiment of the present invention, the first operating condition is a condition of a first forward ratio providing a first thrust at a first incoming flow speed.
In an embodiment of the present invention, the second operating condition is an operating condition of a second forward ratio providing a second thrust at a second incoming flow speed; wherein the second incoming flow velocity is greater than the first incoming flow velocity, the first thrust is greater than the second thrust, and the first advance ratio is less than the second advance ratio.
In one embodiment of the present invention, the blade is divided into a blade front portion and a blade rear portion with reference to the axis of the blade shaft; wherein the blade front is located forward of the blade rear compared to the rotation direction of the propeller; and each focal point generated by the blade under different advancing ratios is positioned on the rear part of the blade.
In an embodiment of the invention, three of said blades are equally spaced circumferentially of said hub about its longitudinal axis.
The technical scheme provided by the embodiment of the invention can have the following beneficial effects:
in the embodiment of the invention, according to the adaptive pneumatic pitch-variable propeller provided by the above, the main body part of the blade is rotatably arranged on the hub, and the tip part of the blade is arranged to have a negative torsion angle and a tip part deflected or offset relative to the main body part, so that the blade can automatically rotate according to the aerodynamic moment generated by the corresponding incoming flow direction to adjust the working attack angle, and the blade can be stabilized in the longitudinal trim state with zero aerodynamic moment, and the propeller can have better blade efficiency in a wider flight envelope.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 shows a schematic view of a propeller in an exemplary embodiment of the invention;
FIG. 2 shows a cross-sectional schematic view of a propeller blade in an exemplary embodiment of the invention;
FIG. 3 shows a schematic side view of a propeller blade in an exemplary embodiment of the invention;
FIG. 4 illustrates a schematic top view of a propeller blade in an exemplary embodiment of the invention;
FIG. 5 shows a schematic side view of a propeller blade in an exemplary embodiment of the invention;
FIG. 6 illustrates a schematic top view of a propeller blade in an exemplary embodiment of the invention;
fig. 7 shows a schematic view of a propeller in an exemplary embodiment of the invention.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of embodiments of the invention, which are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
The conventional pitch-variable propeller generally adopts a pitch-variable mechanism to control the angle of blades, the driving mode of the pitch-variable mechanism generally comprises a hydraulic pitch-variable propeller and an electric pitch-variable propeller, and a blade rotating mechanism of the hydraulic pitch-variable propeller is mainly pushed by lubricating oil pressure; the blade angle of the electric variable pitch propeller is mainly changed by a steering engine. In addition, in order to ensure that the propellers have good performance at each advancing ratio, the flight control system needs to control the pitch-variable mechanism of the propellers separately, so that the flight control system needs to add a control channel to be responsible for adjusting the blade angle. This not only increases flight control system's work burden, has also increased control system's design degree of difficulty. Therefore, it is necessary to provide an adaptive variable pitch propeller to solve the problems of the propeller caused by the addition of the variable pitch mechanism.
An adaptive aerodynamic pitch propeller is provided in the present example embodiment. Referring to fig. 1, the propeller may include: a hub 100, at least two blades 200, and the blades 200 comprise a main body portion 201 and a tip portion 202.
The body 201 is rotatably disposed on the hub 100; the tip 202 of the blade 200 is a negative twist tip, and the tip is deflected by a predetermined angle in the horizontal direction 202 with respect to the main body 201; and/or the tip 202 is offset in a horizontal direction by a predetermined distance with respect to the body 201.
According to the self-adaptive pneumatic pitch-variable propeller, the main body part of the blade is arranged on the propeller hub in a rotating mode, the tip part of the blade is arranged to be the tip part with the negative torsion angle and the sweepback angle, the blade can automatically rotate according to the aerodynamic moment generated in the corresponding incoming flow direction to adjust the working attack angle, the blade can be stabilized in the longitudinal trim state with the aerodynamic moment being zero, and therefore the propeller can have good blade efficiency in a wide flight envelope line.
Next, each part of the above-described adaptive pneumatic variable pitch propeller in the present exemplary embodiment will be described in more detail with reference to fig. 1 to 7.
In one embodiment, the propeller may comprise a hub 100 and at least two blades 200, and the blades 200 comprise a main body portion 201 and a tip portion 202, the main body portion 201 being rotatably disposed on the hub 100; the tip 202 of the blade 200 is a negative twist tip, the tip 202 being offset in a horizontal direction by a predetermined angle with respect to the main body 201, the tip 202 being offset in a horizontal direction by a predetermined distance with respect to the main body 201.
Specifically, two blades 200 may be disposed on the hub 100, or a plurality of blades 200 may be disposed at equal intervals in the circumferential direction, for example, three blades 200 or four blades 200 are disposed at equal intervals in the circumferential direction of the hub 100, and the rotation of the hub 100 drives the blades 200 to rotate to generate corresponding thrust, so as to enable the aircraft to take off or hover. It should be noted that, the hub 100 is disposed on a power device, such as an electric motor, for providing power for an aircraft, and the specific structure can be understood with reference to the prior art, and will not be described herein again.
For clarity, as shown in fig. 1 and 2, the blade 200 may be described as being divided into a main body 201 and a tip 202, the main body 201 is a part of the blade 200 close to the hub 100, and the main body 201 is rotatably disposed on the hub 100, that is, the main body 201 may rotate not only clockwise or counterclockwise with the rotation of the hub 100, but also the main body 201 may rotate in the pitch direction, that is, the blade 200 may rotate around the axis of a blade shaft 2011; the negative torsion design may make the working angle of attack of the tip 202 smaller than that of the main body 201, and the tip 202 may have a predetermined angle of deflection in the horizontal direction with respect to the main body 201, as shown in fig. 4, that is, the tip 202 may have a predetermined angle of sweep back, or as shown in fig. 6, the tip 202 may have a predetermined distance of offset in the horizontal direction with respect to the main body 201, or the tip 202 may have both a predetermined angle of deflection and a predetermined distance of offset in the horizontal direction with respect to the main body 201, which is not limited in particular herein, and may be set according to the actual situation.
It will be particularly appreciated that, with reference to fig. 3 to 6, to provide the blade 200 with greater efficiency, the blade 200 requires the use of a positive camber airfoil, but the positive camber airfoil generates a low head moment, the blade 200 is a blade 200 with a positive camber airfoil, and therefore, it is necessary to match with a negative twist and a swept-back tip 202 to achieve longitudinal balancing of the blade 200, specifically, the blade 200 is mounted on the hub 100 by a blade shaft 2011, and the blade 200 is able to rotate about the blade axis 2011, when the aircraft is operating in different conditions, that is, under different forward ratios, the blade 200 can automatically rotate around the blade shaft 2011 according to the aerodynamic moment generated in the corresponding incoming flow direction to adjust the working attack angle, finally stabilize in the longitudinal trim state with zero aerodynamic moment, and the aerodynamic efficiency in the trim state is high so that the propeller can have good blade 200 efficiency at different forward ratios.
More specifically, the main body 201 is formed by a positive camber airfoil, the aerodynamic load of each section of the blade 200 is relatively backward, and thus the resultant acting point of the integrated aerodynamic force, i.e., the pressure center, is generally located behind the focal point, so that the blade 200 has a low head moment; the working angle of attack of the tip 202 with negative twist and sweep is small relative to the body 201, and the overall tip 202 loading is low, i.e. the loading of the blade area behind the blade shaft axis, i.e. the blade rear 204, is reduced, more aerodynamic loading is concentrated in front of the blade shaft axis, i.e. the area of the blade front 203, at which time the pressure center can be moved forward to move to the position of the blade shaft, thus ensuring that the aerodynamic moment around the blade shaft 2011 is zero, so as to achieve the longitudinal trim condition of the blade 200. It should be noted that the tip offset a predetermined distance from the body 201 in the horizontal direction acts the same as the sweepback tip, so that the tip load is reduced to concentrate more aerodynamic load on the area in front of the blade shaft axis, i.e. in front of the blade, so that the pressure core is advanced to ensure zero aerodynamic moment around the blade shaft.
Meanwhile, in one example, the blade 200 is divided into a blade front portion 203 and a blade rear portion 204 with reference to the axis of the blade shaft 2011; wherein the blade front 203 is located in front of said blade rear 204 compared to the rotation direction of the propeller; each focal point C produced by the blade 200 at different ratios of advance is located on the blade rear portion 204.
It is specifically understood that, with reference to fig. 4 and 6, the focal point C generated by the blade 200 at each forward ratio is located on the blade rear portion 204 and is closest to the axis of the blade shaft 2011, and the distance between the focal point C and the axis of the blade shaft 2011 should satisfy certain stability requirements to ensure that the blade 200 has sufficient longitudinal stability at each forward ratio, so that the propeller can have good blade efficiency within a wide flight envelope.
The present exemplary embodiment provides aerodynamic design of the blades 200 themselves without an additional pitch mechanism, and adopts a trim principle similar to a flying wing layout, and designs the blades 200 to have aerodynamic static stability, so that the propeller can have better blade efficiency at different forward ratios.
The numerical table of the twist angle (BETA) of the blade 200, the efficiency (FM) of the blade 200, the propulsion efficiency (eta) and the Thrust (Thrust) is obtained by simulating the working condition of the incoming flow velocity (Vel) at different advancing ratios (J) when the rotating speed (RPM) of the blade is 3000 r/min.
As can be seen from the above table, with the propeller provided in the above embodiment, the twist angle of the blade 200 automatically changes at different incoming flow speeds, so that the blade efficiency and the propulsion efficiency of the blade 200 are both at a higher value under different working conditions.
In one embodiment, a blade shaft 2011 is disposed at a root of the main body 201 of the blade 200, a shaft hole 101 matched with the blade shaft 2011 is disposed on a circumferential side wall of the hub 100, the blade 200 is disposed on the hub 100 by the blade shaft 2011 extending into the shaft hole 101, and the blade 200 can rotate around an axis of the blade shaft 2011, so that the blade has a degree of freedom in a pitch direction, and angles under different forward ratio working conditions can be automatically adjusted to achieve an aerodynamic moment balance state.
For example, as shown in fig. 2, a plurality of symmetrical shaft holes 101 may be disposed on a circumferential sidewall of the hub 100 at equal intervals, and the shaft holes 101 are matched with the blade shafts 2011 at the root of the blade 200, so that the blade 200 is mounted on the hub 100 to be capable of rotating clockwise or counterclockwise along with the rotation of the hub 100 through the matching connection of the blade shafts 2011 and the shaft holes 101, and a limiting member may be disposed in the shaft hole 101 to prevent the blade 200 from falling off from the hub 100, which is not limited specifically. The blades 200 can rotate around the axis of the blade shaft 2011, when the aircraft works in different states, that is, in different forward ratios, the blades 200 can automatically rotate around the blade shaft 2011 according to the aerodynamic moment generated in the corresponding incoming flow direction to adjust the working attack angle, and finally, the aircraft is stabilized in a longitudinal balancing state of aerodynamic moment balance, and the aerodynamic efficiency in the balancing state is high, so that the propeller can have good blade efficiency in different forward ratios.
Alternatively, in one embodiment, three of the blades 200 are equally spaced circumferentially of the hub 100 about the longitudinal axis of the hub 100.
Specifically, as shown in fig. 2 and 4, three blades 200 may be disposed at equal intervals in the circumferential direction of the hub 100, the three blades 200 have the same shape and structure, and each of the three blades 200 can rotate along the blade axis 2011 thereon to adjust the operational attack angle, so that the blades 200 are stabilized in the longitudinal trim state of aerodynamic moment balance, thereby ensuring the efficiency of the propeller. It should be noted that, the plurality of blades 200 may be arranged in the circumferential direction of the hub 100 at equal intervals, specifically according to the actual situation, and not limited herein.
In one embodiment, the blade shaft 2011 is connected with the shaft hole 101 through an elastic member 2012, so that the elastic moment generated by the deformation of the elastic member 2012 is balanced with the aerodynamic moment of the blade 200 under different working conditions, so that the blade 200 is in a balanced state.
For example, as shown in fig. 7, a spring may be disposed on the blade shaft 2011, and the blade shaft 2011 is disposed in the shaft hole 101 through the spring, which is not limited to this. Because the blade main body 201 uses the positive camber airfoil, the aerodynamic load of each section of the blade 200 is relatively backward, so the resultant action point of the integrated aerodynamic force, i.e. the pressure center, is usually located behind the focus, so that the blade 200 has a low head moment; the tip part with negative torsion and sweepback angle or the tip part 202 which is deviated backwards relative to the main body part 201 has a small working attack angle relative to the main body part 201, and the whole load of the tip part 202 is lower, that is, the load of the blade area behind the axis of the blade shaft, that is, the blade area of the blade rear part 204 is reduced, more aerodynamic load is concentrated in front of the axis of the blade shaft, that is, the area of the blade front part 203, at this time, the pressure core can be moved forwards to expect to move to the position of the blade shaft, if the pressure core can not be moved to the position of the blade shaft to ensure that the aerodynamic torque around the blade shaft 2011 is zero, at this time, the elastic torque generated by the spring deformation needs to be utilized to balance the aerodynamic torque of the blade 200 in different working states, and the aerodynamic efficiency in the balancing state is higher, so that the propeller can have better blade efficiency under different forward ratios. It should be noted that the stiffness of the spring can be designed during the design process, i.e. the balance state of the blade 200 achieved during operation is adjusted manually.
In one embodiment, the vane 200 is located at a first predetermined position a under a first operating condition, and rotates to a second predetermined position B under a second operating condition, and an included angle between the first predetermined position a and the second predetermined position B is a predetermined angle.
Specifically, the blade 200 can rotate around the axis of the blade shaft 2011, when the propeller works in different states, that is, in different forward ratios, the blade 200 can automatically rotate around the blade shaft 2011 according to the aerodynamic moment generated in the corresponding incoming flow direction to adjust the working attack angle, that is, the blade 200 rotates between the angle formed by the first preset position a and the second preset position B, the attack angle is trimmed, and finally the blade is stabilized in a longitudinal trim state where the aerodynamic moment is zero, and the aerodynamic efficiency in the trim state is high, so that the propeller can have good blade 200 efficiency in different forward ratios.
The first working condition is a working condition of a first advancing ratio for providing first thrust when the first incoming flow speed is higher than the first incoming flow speed; the second working condition is a working condition of a second advancing ratio for providing second thrust when the speed of the second incoming flow is high; wherein the second incoming flow velocity is greater than the first incoming flow velocity, the first thrust is greater than the second thrust, and the first advance ratio is less than the second advance ratio.
For example, the first incoming flow speed is a small incoming flow speed or a zero incoming flow speed, the first thrust is a large thrust, and the first forward ratio is a low forward ratio or a zero forward ratio, that is, the first operating condition may be further understood as a low forward ratio or a zero forward ratio operating condition that provides a large thrust at a small incoming flow speed or a zero incoming flow speed; similarly, the second incoming flow speed is a large incoming flow speed that is large relative to the first incoming flow speed, the second thrust is a small thrust that is small relative to the first thrust, and the second forward ratio is a high forward ratio that is high relative to the first forward ratio, and thus the second operating condition may be further understood as a high forward ratio operating condition that provides a small thrust at large incoming flow speeds. Moreover, the propeller can rotate around the blade shaft 2011 in a self-adaptive manner to adjust the working attack angle through the difference of incoming flow speeds, so that the blade 200 is stabilized in a longitudinal balancing state in which aerodynamic moment is zero or the aerodynamic moment is balanced with the elastic moment of the elastic element, and the propeller can have better blade 200 efficiency under different forward ratios.
According to the adaptive pneumatic pitch-variable propeller provided by the above, the main body part of the blade is rotatably arranged on the hub, and the tip part of the blade is arranged to have a negative torsion angle and a tip part deflected or offset relative to the main body part, so that the blade can automatically rotate according to the aerodynamic moment generated in the corresponding incoming flow direction to adjust the working attack angle, the blade can be stabilized in the longitudinal trim state in which the aerodynamic moment is zero or the aerodynamic moment is balanced with the elastic moment of the elastic element, and the propeller can have better blade efficiency in a wider flight envelope.
It is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like in the foregoing description are used for indicating or indicating the orientation or positional relationship illustrated in the drawings, and are used merely for convenience in describing embodiments of the present invention and for simplifying the description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the embodiments of the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the embodiments of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrated; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In embodiments of the invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise the first and second features being in direct contact, or the first and second features being in contact, not directly, but via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
Claims (8)
1. An adaptive pneumatic variable pitch propeller, the propeller comprising:
a hub;
at least two blades, the blades including a main body portion and a tip portion, the main body portion rotatably disposed on the hub; wherein,
the tip of the blade is a negative torsion tip;
the tip part deflects relative to the main body part by a preset angle in the horizontal direction; and/or the tip portion is offset in a horizontal direction by a predetermined distance relative to the main body portion.
2. The adaptive pneumatic variable pitch propeller of claim 1, wherein a blade shaft is provided at a root portion of the main body portion of the blade, and a shaft hole matching the blade shaft is provided in a circumferential side wall of the hub, the blade is provided on the hub by the blade shaft extending into the shaft hole, and the blade is rotatable about an axis of the blade shaft so that the blade is in a balanced state.
3. The adaptive pneumatic variable pitch propeller of claim 2, wherein the blade shaft and the shaft hole are connected by an elastic member, so that an elastic moment generated by deformation of the elastic member is balanced with an aerodynamic moment of the blade under different working conditions, so that the blade is in a balanced state.
4. The adaptive pneumatic variable pitch propeller of claim 3 wherein the blades are in a first predetermined position under a first operating condition and are rotated to a second predetermined position under a second operating condition, and the first predetermined position and the second predetermined position form a predetermined angle.
5. The adaptive pneumatic variable pitch propeller of claim 4, wherein the first operating condition is a first forward ratio operating condition providing a first thrust at a first incoming flow rate.
6. The adaptive pneumatic variable pitch propeller of claim 5, wherein the second operating condition is a second forward ratio operating condition providing a second thrust at a second incoming flow rate; wherein the second incoming flow velocity is greater than the first incoming flow velocity, the first thrust is greater than the second thrust, and the first advance ratio is less than the second advance ratio.
7. The adaptive pneumatic variable pitch propeller of claim 2, wherein said blades are divided into a blade front portion and a blade rear portion with respect to a blade shaft axis; wherein the blade front is located forward of the blade rear compared to the rotational direction of the propeller; and each focal point generated by the blade under different advancing ratios is positioned on the rear part of the blade.
8. The adaptive pneumatic variable pitch propeller of claim 1 wherein three of said blades are equally spaced circumferentially about the longitudinal axis of said hub.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112052529A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Calculation method for improving large-advancing-ratio rotor wing trim convergence |
| CN112918669A (en) * | 2019-12-06 | 2021-06-08 | 北京二郎神科技有限公司 | Rotor of rotor craft and rotor craft |
| CN113492966A (en) * | 2020-03-19 | 2021-10-12 | 拉季埃-菲雅克有限责任公司 | Propeller blade arrangement |
| CN113955083A (en) * | 2021-10-26 | 2022-01-21 | 上海磐拓航空科技服务有限公司 | Passive variable-pitch propeller fan |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112918669A (en) * | 2019-12-06 | 2021-06-08 | 北京二郎神科技有限公司 | Rotor of rotor craft and rotor craft |
| CN113492966A (en) * | 2020-03-19 | 2021-10-12 | 拉季埃-菲雅克有限责任公司 | Propeller blade arrangement |
| CN112052529A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Calculation method for improving large-advancing-ratio rotor wing trim convergence |
| CN112052529B (en) * | 2020-09-25 | 2023-03-17 | 中国直升机设计研究所 | Calculation method for improving large-advancing-ratio rotor wing trim convergence |
| CN113955083A (en) * | 2021-10-26 | 2022-01-21 | 上海磐拓航空科技服务有限公司 | Passive variable-pitch propeller fan |
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