CN112520063A - Pneumatic design method suitable for rotor blade - Google Patents

Pneumatic design method suitable for rotor blade Download PDF

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CN112520063A
CN112520063A CN202011414925.2A CN202011414925A CN112520063A CN 112520063 A CN112520063 A CN 112520063A CN 202011414925 A CN202011414925 A CN 202011414925A CN 112520063 A CN112520063 A CN 112520063A
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刘振臣
马铁林
王英勋
钱浩
苗培鑫
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Abstract

The invention provides a pneumatic design method of a rotor blade, which comprises the following steps: determining the number of blades of a rotor blade; determining a diameter of a rotor blade; selecting wing profiles at different radius positions from a rotor shaft; establishing an airfoil aerodynamic performance database; estimating aerodynamic performance parameters of the rotor blade; an optimization algorithm is used to optimize the overall aerodynamic efficiency of the rotor blade. The pneumatic design method can improve the overall pneumatic efficiency of the rotor propeller under the condition of meeting the aerodynamic requirements of the tilt rotor aircraft in the forward flying, hovering and transition states.

Description

Pneumatic design method suitable for rotor blade
Technical Field
The invention relates to the technical field of aircrafts, in particular to a pneumatic design method of a rotor blade.
Background
The tilt rotor aircraft has the high-speed flight capability of the fixed-wing aircraft, and also has the vertical take-off and landing and hovering capabilities of the helicopter, so that the tilt rotor aircraft is a novel aircraft integrating the main advantages of the fixed-wing aircraft and the helicopter, can be widely applied to the fields of logistics transportation, emergency rescue, scientific investigation, environmental monitoring and the like, and has a wide application prospect. In recent years, tiltrotor aircraft have become one of the important development directions in the field of aircraft, and have received high attention from a plurality of countries.
The tiltrotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, has the capability of vertically taking off and landing a common helicopter and hovering the helicopter, has the capability of high-speed cruising flight of a propeller aircraft, is a novel aircraft integrating the main advantages of the fixed-wing aircraft and the helicopter, can be widely applied to the fields of logistics transportation, emergency rescue, scientific investigation, environmental monitoring and the like, and has a wide application prospect. In recent years, tiltrotor aircraft have become one of the important development directions in the field of aircraft, and have received high attention from a plurality of countries.
Tilt rotor aircraft is in the two wing point departments of similar fixed wing aircraft wing, each dress set can be at the rotor system of verting subassembly of rotating between horizontal position and vertical position, when the aircraft takes off perpendicularly and lands, rotor shaft perpendicular to ground, be horizontal formula helicopter flight state, and can hover in the air, fly around and the side, take off after reaching the certain speed at tilt rotor aircraft, the rotor shaft can be forward or backward 45 jiaos of verting, be horizontal state, the rotor uses as lag screw or thrust screw, tilt rotor can do long-range flight like fixed wing aircraft with higher speed this moment, the driving system of tilt rotor aircraft possesses the dual function of screw and rotor simultaneously promptly.
The fixed wing aircraft generally adopts propellers as a power device, the helicopter generally adopts a rotor wing as a power device, the propellers are devices which rotate in the air or water by means of blades and convert the rotating power of an engine into propulsive force, two or more blades can be connected with a hub, and the backward surface of each blade is a helicoid or a propeller similar to the helicoid; the rotor wing is an important part of the helicopter, and plays a dual role in generating lift force and pulling force in the flying process of the helicopter; the rotor is composed of a hub and a plurality of blades, the hub is arranged on a rotor shaft, the blades in the shape of slender wings are connected on the hub, but the rotor shaft of the common rotor is generally arranged along the vertical direction and cannot rotate to the horizontal direction.
Correspondingly, the tilt rotor aircraft adopts a rotor blade or a rotor blade as a power device. This patent will be applied to on the gyroplane that verts, can enough provide horizontal tension for the gyroplane that verts in order to overcome full quick-witted aerodynamic resistance and realize its high-speed flat flight, can provide vertical tension again in order to overcome earth gravitation in order to realize the gyroplane that verts VTOL and the power device definition of hovering steadily be rotor oar or oar rotor, and vertical direction can be followed to the rotor shaft of its rotor, also can rotate to the horizontal direction to distinguish with ordinary rotor.
For any type of aircraft, a power system is a core part of the aircraft, and main performance (especially, aerodynamic performance) of the power system directly determines multiple indexes of the aircraft, including maximum load, flight time, flight speed and the like, so that the design of the power system is very important for the aircraft, and different from propellers and rotors, in horizontal and vertical use states of rotor paddles (paddle rotors), requirements for flight speed and tension of the rotor paddles (paddle rotors) are greatly different, and a conventional propeller or rotor aerodynamic design method cannot be directly applied to aerodynamic design of the rotor paddles (paddle rotors), and a pneumatic design method suitable for the rotor paddles (paddle rotors) needs to be provided.
Disclosure of Invention
In order to solve the problems, the invention provides a pneumatic design method of a rotor blade.
A method of aerodynamic design of a rotor blade comprising the steps of: determining the number of blades of a rotor blade; determining the diameter D of the rotor blade; selecting wing profiles at different radius positions from a rotor shaft; establishing an airfoil aerodynamic performance database; estimating aerodynamic performance parameters of the rotor blade; an optimization algorithm is used to optimize the overall aerodynamic efficiency of the rotor blade.
Further, the number of blades of the rotor paddle is 2 or 3.
Figure BDA0002818651860000021
Efficiency greater than estimated efficiency ηr≥ηeAnd determining the diameter D of the rotor blade according to the relation curve of the expected efficiency and the diameter of the rotor blade.
Further, according to the Reynolds number distribution and the efficiency coefficient cαDetermining wing profiles at different radius positions away from the axis of the rotor wing;
airfoil efficiency coefficient:
Figure BDA0002818651860000031
in the formula CLIs coefficient of lift, CDIs coefficient of resistance, alphastallIs the stall angle of attack, R is the radius, and R is the distance from the position of the airfoil to the axis of rotation.
Further, establishing a pneumatic performance database of different airfoil profiles under the conditions of different Reynolds numbers and attack angles, wherein the database comprises a lift coefficient CLF (Re, alpha, af), coefficient of resistance CD＝f(Re，α，af)。
Further, the aerodynamic performance parameter includes a propulsive efficiency η of the rotor blade at a cruise condition of level flightcAnd hovering efficiency η in hovering stateh。
Further, the propulsion efficiency ηc＝TV0/Pc(ii) a Wherein T is the drag of the rotor blade, PcFlat flight power; the hovering efficiency ηh＝Ph/Pi. Wherein, PhTo hover power, Pi＝T3/2/(0.25πD2ρ)1/2Is the power in the ideal state; t is the drag of the rotor blade, PcThe flying power ρ is the air density.
Further, the air conditioner is provided with a fan,the aerodynamic performance parameter includes a setting angle
Figure BDA0002818651860000032
And a rotational speed n.
Further, the optimization algorithm preferably employs a genetic algorithm.
Further, optimizing the overall aerodynamic efficiency of the rotor blade using an optimization algorithm includes: determining an optimization variable, determining a constraint condition, determining an optimization target, and selecting an optimization result.
The pneumatic design method can improve the overall pneumatic efficiency of the rotor blade under the condition of meeting the aerodynamic requirements of the tilt rotor aircraft in forward flight, hovering and transition states.
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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 is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a flowchart of a design method in example 1;
FIG. 2 is a schematic view of the cruise state of the rotor blades in embodiment 1;
FIG. 3 is a schematic view showing a hovering state of a rotor blade according to embodiment 1;
fig. 4 is a schematic view of the flight envelope of the tiltrotor aircraft in embodiment 2;
FIG. 5 is a schematic representation of cruise efficiency and hover efficiency versus rotor blade diameter for example 2;
fig. 6 is a schematic view of aerodynamic performance of an airfoil in embodiment 2.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
This patent will be applied to on the gyroplane that verts, can enough provide horizontal tension for the gyroplane that verts in order to overcome full quick-witted aerodynamic resistance and realize its high-speed flat flight, can provide vertical tension again in order to overcome earth gravitation in order to realize the gyroplane that verts VTOL and the power device definition of hovering steadily be rotor oar or oar rotor, and vertical direction can be followed to the rotor shaft of its rotor, also can rotate to the horizontal direction to distinguish with ordinary rotor.
Example 1
As shown in fig. 1, a flow diagram of an aerodynamic design method of a rotor blade (paddle rotor) can improve the overall aerodynamic efficiency of the rotor blade under the condition of satisfying the aerodynamic needs of a tilt rotor aircraft in forward flight, hovering and transition states. As shown in fig. 2, the axis of rotation of the rotor blades is substantially parallel to the direction of flight during cruise flight. As shown in fig. 3, the axis of rotation may be considered approximately completely perpendicular to the horizontal plane in the hovering state.
The design method specifically comprises the following steps:
step S100: the number of blades of a rotor blade (oar rotor) is determined.
In order to reduce the influence of the periodic speed and pressure pulsation in the slip flow area of the rotor blades on the tiltrotor, the number of the blades of the rotor blades (propeller rotors) is 3 in general, and the number of the blades of the rotor blades (propeller rotors) can be reduced to 2 in special cases in order to reduce the complexity of a pitch-variable mechanism.
Step S200: the diameter D of the rotor blades (paddle rotor) is determined.
Tension requirement T according to cruising statecCalculating the estimated efficiency of the rotor blade according to the requirements of the cruising speed V and the cruising height (corresponding to the air density rho) as W/k
Figure BDA0002818651860000051
Making the desired efficiency greater than the estimated efficiency etar≥ηeThe rotor blade diameter D is further determined from the desired efficiency versus rotor blade diameter.
Step S300: and selecting the wing profiles at different radius positions from the rotor shaft.
In order to improve the overall efficiency of different flight regimes, the airfoils are required to have a large lift-to-drag ratio and a maximum stall angle of attack.
Estimating the mean chord length c according to the rotor blade diameter D and the minimum aspect ratio requirement (in general, the aspect ratio of the rotating blade is greater than 6); according to the estimated advance ratio J-V/nsD (where V is the cruising speed, n)sThe number of turns per second of the rotor blade), the maximum speed n of the rotor blade is calculateds(ii) a Calculating the rotation speed V (r) of the leaf element at the radial position r (the distance between the position of the wing section and the rotation axis) to be 2 pi rns(ii) a Preliminarily estimating Reynolds number Re (r) ═ 2 pi rn of chord lengthsc/v (v is the air movement viscosity coefficient);
in order to select the wing profile with better comprehensive aerodynamic performance, the wing profile efficiency coefficient is introduced:
Figure BDA0002818651860000052
in the formula CLIs coefficient of lift, CDIs coefficient of resistance, alphastallStall angle of attack, R is radius;
according to the Reynolds number distribution and the coefficient of performance cαDetermining the wing profiles at different radius positions from the axis of the rotor wing.
Step S400: and establishing an airfoil aerodynamic performance database.
Establishing aerodynamic performance databases of different airfoils under different Reynolds numbers and attack angles by using numerical calculation and other methods, wherein the aerodynamic performance databases comprise lift coefficient CLF (Re, alpha, af), coefficient of resistance CDF (Re, α, af), etc.;
step S500: aerodynamic performance estimation software for rotor blades (oar rotors) was written.
The method comprises the following steps of calculating the tension, the torque and the power of the hovering state and the cruise state by adopting a strip theory:
step S510: calculate the phyllanthus aerodynamic force.
The phylline pulling force dT and the phylline torque dQ at different radial positions are calculated according to the following formula:
Figure BDA0002818651860000061
Figure BDA0002818651860000062
in the formula (I), the compound is shown in the specification,
ρ is the air density;
w is the resultant velocity at radius r,
Figure BDA0002818651860000063
gamma is the lift angle of airfoil at radius r, gamma is arctan (C)D/CL)，
Beta is the interference angle at radius r, through
Figure BDA0002818651860000064
Obtained by iterative solution (where N isBNumber of blades);
step S520: the overall performance is calculated.
Overall rotor blade tension
Figure BDA0002818651860000065
Torque of
Figure BDA0002818651860000066
Sum power P2 pi nsQ。
Step S530: and calculating the aerodynamic efficiency.
Propulsion efficiency eta of rotor blade in level flight cruising statecAnd hovering efficiency η in hovering statehThe calculation methods are respectively as follows:
(1) propulsive efficiency etaCTV/P. Wherein T is the drag of the rotor blade, PcFlat flight power;
(2) efficiency η of hoveringh＝Ph/Pi. Wherein, PhTo hover power, Pi＝T3/2/(0.25πD2ρ)1/2Is in an ideal stateOf the power of (c).
Step S600: an optimization algorithm is used to optimize the overall aerodynamic efficiency of the rotor blades (paddle rotors).
The optimization algorithm preferably employs a genetic algorithm.
Step S610: and determining an optimization variable.
The optimization parameters are selected from a chord length distribution function b (x) and a torsion angle distribution function c (x) of the rotor blade.
The chord length distribution is described by a third-order Bessel function:
b(x)＝(1-x)3b0+3x(1-x)2b1+3x(1-x)x2b2+x3b3where x is R/R is the relative radial position, b0、b1、b2、b3To optimize the variables;
the twist angle distribution is also described using a third order bessel function:
c(x)＝(1-x)3c0+3x(1-x)2c1+3x(1-x)x2c2+x3c3(ii) a Wherein c is0、c1、c2、c3To optimize the variables.
Step S620: a constraint is determined.
Tension T of rotor propeller in hovering statehW (W is the maximum takeoff weight of the tiltrotor aircraft in newton N); tension T of rotor blade in level flight cruising statecsW/k (k is the full lift-drag ratio of the tiltrotor aircraft in the cruise state).
Step S630: an optimization objective is determined.
The overall aerodynamic efficiency is taken as an optimization target.
Defining the overall aerodynamic efficiency η of the rotor bladep＝c*×ηc+h*×ηh；
Figure BDA0002818651860000071
The cruise efficiency weight;
Figure BDA0002818651860000072
an efficiency weight for the hover state;
tcfor total cruising time, t, determined from the flight envelopehIs the total hover time determined from the flight envelope.
Step S640: and selecting an optimization result.
According to limitation of mach number of blade tips, i.e.
Figure BDA0002818651860000073
And selecting an optimization result.
Example 2
The present embodiment further illustrates the aerodynamic design method of the rotor blades (paddle rotors) in embodiment 1 according to a specific design requirement.
The design requirements of the present embodiment include: the total weight W of the tilt rotor aircraft is 100kg, the cruising height is 3000m, the designed cruising speed is 120km/h, the climbing speed is 100km/h, and the descending speed is 110 km/h. The lift-drag ratio k of the whole machine is designed to be 9.5. A typical flight profile is shown in FIG. 4, with a total time for a single flight of about 6 hours, with a total time for near-ground hover of 1 hour, and a total time for climb and descent of 1 hour. According to the overall requirements, the hub mechanism of the rotor blade is as simple as possible, requiring a cruising efficiency ηcNot less than 84%.
Step S100: the number of blades of a rotor blade (oar rotor) is determined.
To reduce the complexity of the mechanism, the number of rotor blades of the rotor blade is designed to be 2, depending on the design requirements of the hub.
Step S200: the diameter of the rotor blades (paddle rotors) is determined.
Calculating the total tension T of two rotor blades to be 100 multiplied by 9.8/9.5 to be 103.2N according to the total weight of the tilt rotor aircraft, so that the tension of each rotor blade is 51.6N;
according to a design cruising height of 3000m, the corresponding air density rho is 0.903kg/m3；
According to the design that the cruising speed is 120km/h, and the cruising speed after unit conversion is V is 120/3.6 or 33.3 m/s;
in accordance with the estimated efficiency definition,
Figure BDA0002818651860000081
by substituting the above parameters, the method can be obtained
Figure BDA0002818651860000082
From this expression, the obtained relation between the diameter and the propulsive efficiency is shown in FIG. 5, according to the propulsive efficiency requirement ηeThe D is more than or equal to 1.6m after being solved for more than or equal to 0.84. The diameter of the rotor blade is thus set to 1.6 m.
Step S300: and selecting the wing profiles at different radius positions from the rotor shaft.
Estimating the average chord length c to be less than or equal to 0.13m according to the diameter D which is 1.6m (the radius R is 0.8m) and the requirement of the minimum aspect ratio (generally, the aspect ratio of the rotating blade is more than 6);
according to the estimated advance ratio J-V/nsD is 0.8, the maximum rotating speed of the rotor blade is calculated to be 1560rpm, and the reynolds number Re (r) of the chord length r multiplied by 1.5 multiplied by 10 is preliminarily estimated6；
According to Reynolds number distribution and coefficient of performance
Figure BDA0002818651860000083
Preferably, the relative radius R/R is 0.7, and one airfoil is selected from the conventional airfoils of the propeller. And determining the distribution of the airfoil family according to the efficiency coefficient and the database of the airfoils with different thicknesses. For the embodiment, the airfoil profile with the standard Clark Y of 0.7 half-diameter is selected, and the thickness distribution adopts quadratic function distribution.
Step S400: and establishing an airfoil aerodynamic performance database.
Using the CFD method and the disclosed Xfoil software, a database of airfoil aerodynamics for different radial positions is obtained, as shown in FIG. 6. And constructing a database according to the estimated Reynolds numbers corresponding to the different radius positions.
The range of attack angles in the built airfoil profile data should include the lift coefficient C of which the effective attack angle should cover the range of 0-20 degreesLCoefficient of resistance CD；
Since the Xfoil calculation regime is generally limited to stall angle of attack αstallCalculating internal aerodynamic force, and adopting a CFD method for the aerodynamic calculation of the part exceeding the stall attack angle;
step S500: the aerodynamic performance parameters of the rotor blades (paddle rotors) are estimated.
Calculating the mounting angle
Figure BDA0002818651860000091
The tension T, the power P and the efficiency eta are all combined working conditions within the range of 1-15 ℃ and the rotating speed n of 500-3000rpm and are according to the tension T in the cruising statecTension T in hovering statehCalculating a mounting angle that satisfies the design requirements
Figure BDA0002818651860000092
And speed n, and simultaneously gives the corresponding propulsion efficiency etacAnd hovering efficiency ηh。
Step S600: an optimization algorithm is used to optimize the overall aerodynamic efficiency of the rotor blades (paddle rotors).
The optimization algorithm used is a genetic algorithm.
Step S610: and determining an optimization variable.
According to the specific requirements of the application example, the following optimization variables are determined:
four constant terms b in the chord length distribution function0、b1、b2、b3(ii) a Four constant terms c of the distribution function of torsion angle0、c1、c2、c3；
Step S620: a constraint is determined.
Determining the constraint conditions as follows: the hovering pulling force is 490N, and the cruising pulling force is 51.6N.
Step S630: an optimization objective is determined.
The optimization target is as follows: overall efficiency ηp＝0.5×ηc+0.5×ηh。
Step S640: and selecting an optimization result.
According to the limit of the tip Mach number being less than 0.65, i.e.
Figure BDA0002818651860000101
And finally, selecting an optimization result. The specific parameters are as follows:
item Parameter(s)
Diameter of 1.6m
Rotational speed 1670rpm
Efficiency of hovering 65％
Efficiency of propulsion 85％
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (10)

1. A method of pneumatically designing a rotor blade, comprising the steps of:
determining the number of blades of a rotor blade;
determining the diameter D of the rotor blade;
selecting wing profiles at different radius positions from a rotor shaft;
establishing an airfoil aerodynamic performance database;
estimating aerodynamic performance parameters of the rotor blade;
an optimization algorithm is used to optimize the overall aerodynamic efficiency of the rotor blade.
2. A method according to claim 1, wherein the number of blades of the rotor paddle is 2 or 3.
3. A method according to claim 1, characterised in that the tension T according to the cruising regime is such that it is a function of the rotor blade's aerodynamic designcCalculating the estimated efficiency of the rotor blade according to the air density rho corresponding to the cruising speed V and the cruising height
Figure FDA0002818651850000011
Making the desired efficiency greater than the estimated efficiency etar≥ηeAnd determining the diameter D of the rotor blade according to the relation curve of the expected efficiency and the diameter of the rotor blade.
4. A method of aerodynamic design of a rotor blade according to claim 1, characterized by the distribution of reynolds numbers and the coefficient of performance cαDetermining wing profiles at different radius positions away from the axis of the rotor wing;
airfoil efficiency coefficient:
Figure FDA0002818651850000012
in the formula CLIs coefficient of lift, CDIs coefficient of resistance, alphastallIs the stall angle of attack, R is the radius, and R is the distance from the position of the airfoil to the axis of rotation.
5. The method of claim 1, wherein a database of aerodynamic performance of different airfoils at different reynolds numbers and angles of attack is established, including lift coefficient CLF (Re, alpha, af), coefficient of resistance CD＝f(Re，α，af)。
6. A method according to claim 1, wherein the aerodynamic performance parameter comprises a propulsion efficiency η of the rotor blade in a cruise level flight conditioncAnd hovering efficiency η in hovering stateh。
7. A method of pneumatically designing a rotor paddle according to claim 6,
the propulsion efficiency etac＝TV0/Pc(ii) a Wherein T is the drag of the rotor blade, PcFlat flight power;
the hovering efficiency ηh＝Ph/Pi. Wherein, PhIn order to suspend the power in the air,Pi＝T3/2/(0.25πD2ρ)1/2is the power in the ideal state; t is the drag of the rotor blade, PcThe flying power ρ is the air density.
8. A method of aerodynamically designing a rotor blade according to claim 1, wherein the aerodynamic performance parameter comprises an angle of incidence
Figure FDA0002818651850000021
And a rotational speed n.
9. A method according to claim 1, wherein the optimization algorithm is preferably a genetic algorithm.
10. The method of claim 1, wherein optimizing the overall aerodynamic efficiency of the rotor blade using the optimization algorithm comprises: determining an optimization variable, determining a constraint condition, determining an optimization target, and selecting an optimization result.
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Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2058250C1 (en) * 1992-03-19 1996-04-20 Акционерное общество Научно-производственное предприятие "Аэросила" Method of manufacture of propeller composite blades
JP2000211594A (en) * 1999-01-26 2000-08-02 Mitsubishi Heavy Ind Ltd Adjustment method for mounting moving blade of aircraft
CN101423117A (en) * 2008-12-05 2009-05-06 北京航空航天大学 Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder
US20140061392A1 (en) * 2005-08-15 2014-03-06 Abe Karem Aircraft With Integrated Lift And Propulsion System
CN106945846A (en) * 2017-03-01 2017-07-14 中国航天空气动力技术研究院 A kind of low reynolds number air propeller profile determines method
CN107609243A (en) * 2017-09-04 2018-01-19 西北工业大学 A kind of design method of propeller blade
CN108021772A (en) * 2017-12-26 2018-05-11 南京航空航天大学 A kind of method and system of the reduction rotor noise based on jet stream
CN108170939A (en) * 2017-12-26 2018-06-15 南京航空航天大学 A kind of method and system of the reduction rotor noise based on trailing edge flap
CN109558650A (en) * 2018-11-09 2019-04-02 中国直升机设计研究所 The analysis method that lifting airscrew icing influences rotary wing performance
CN109693807A (en) * 2018-12-28 2019-04-30 西北工业大学 A kind of adaptive pneumatic variable-pitch propeller design method
CN109992893A (en) * 2019-04-03 2019-07-09 中南大学 A kind of propeller profile optimization design method
CN111056036A (en) * 2019-12-27 2020-04-24 北京电子工程总体研究所 Rapid iteration generation method for high-altitude propeller
CN111216920A (en) * 2020-04-16 2020-06-02 北京清航紫荆装备科技有限公司 Rotor wing T-head bearing model selection method and device of unmanned helicopter
CN111611652A (en) * 2020-06-04 2020-09-01 电子科技大学 Flapping wing aerodynamic characteristic analysis method based on active flexible deformation
CN111674546A (en) * 2020-06-19 2020-09-18 南京航空航天大学 Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2058250C1 (en) * 1992-03-19 1996-04-20 Акционерное общество Научно-производственное предприятие "Аэросила" Method of manufacture of propeller composite blades
JP2000211594A (en) * 1999-01-26 2000-08-02 Mitsubishi Heavy Ind Ltd Adjustment method for mounting moving blade of aircraft
US20140061392A1 (en) * 2005-08-15 2014-03-06 Abe Karem Aircraft With Integrated Lift And Propulsion System
CN101423117A (en) * 2008-12-05 2009-05-06 北京航空航天大学 Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder
CN106945846A (en) * 2017-03-01 2017-07-14 中国航天空气动力技术研究院 A kind of low reynolds number air propeller profile determines method
CN107609243A (en) * 2017-09-04 2018-01-19 西北工业大学 A kind of design method of propeller blade
CN108021772A (en) * 2017-12-26 2018-05-11 南京航空航天大学 A kind of method and system of the reduction rotor noise based on jet stream
CN108170939A (en) * 2017-12-26 2018-06-15 南京航空航天大学 A kind of method and system of the reduction rotor noise based on trailing edge flap
CN109558650A (en) * 2018-11-09 2019-04-02 中国直升机设计研究所 The analysis method that lifting airscrew icing influences rotary wing performance
CN109693807A (en) * 2018-12-28 2019-04-30 西北工业大学 A kind of adaptive pneumatic variable-pitch propeller design method
CN109992893A (en) * 2019-04-03 2019-07-09 中南大学 A kind of propeller profile optimization design method
CN111056036A (en) * 2019-12-27 2020-04-24 北京电子工程总体研究所 Rapid iteration generation method for high-altitude propeller
CN111216920A (en) * 2020-04-16 2020-06-02 北京清航紫荆装备科技有限公司 Rotor wing T-head bearing model selection method and device of unmanned helicopter
CN111611652A (en) * 2020-06-04 2020-09-01 电子科技大学 Flapping wing aerodynamic characteristic analysis method based on active flexible deformation
CN111674546A (en) * 2020-06-19 2020-09-18 南京航空航天大学 Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft

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