CN109969425A - A kind of two sides propelling screws optimization method for compound thrust configuration helicopter - Google Patents
A kind of two sides propelling screws optimization method for compound thrust configuration helicopter Download PDFInfo
- Publication number
- CN109969425A CN109969425A CN201910251284.4A CN201910251284A CN109969425A CN 109969425 A CN109969425 A CN 109969425A CN 201910251284 A CN201910251284 A CN 201910251284A CN 109969425 A CN109969425 A CN 109969425A
- Authority
- CN
- China
- Prior art keywords
- propeller
- power
- pulling force
- geometric parameter
- sides
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Water Turbines (AREA)
Abstract
The present invention discloses a kind of two sides propelling screws optimization method for compound thrust configuration helicopter, this method comprises: the Aerodynamic Model for inputting preset propeller geometric parameter, establishing two sides propeller, by introducing pointer algorithm, calculate separately the required horsepower for flying propeller under state before floating state, cruising condition and maximum speed, then by changing geometric parameter in the reasonable scope, search the parameter point for meeting two constraint condition, after completing default calculating step number, geometric parameter when power smallest point in point is collected in output.Method and system provided by the invention more can easily solve the problems, such as that working efficiency of the compound thrust configuration helicopter two sides propelling screws under different flight state is lower, to further promote its flying quality.
Description
Technical field
The present invention relates to helicopter fields, promote spiral shell more particularly to a kind of two sides for compound thrust configuration helicopter
Revolve paddle optimization method.
Background technique
The compound thrust configuration helicopter of rotor/wing, the configuration helicopter are as shown in Figure 1.
In VTOL, hovering movement flight, rotor makees mainpiston and posture control surface under driven by engine, preceding
Fly transition flight when, as flying speed increases, wing gradually generates lift, for rotor unload, while reduce rotor always away from
And disk angle of attack, when certain speed to be achieved, rotor revolving speed is reduced, until flying the setting value under mode before high speed.
It has two sets of lift systems of rotor and fixed-wing and corresponding operating mechanism.In VTOL, hover and low
Under fast state of flight, by always away from transverse and longitudinal cyclic pitch control.Under high-speed flight state, by aileron, elevator and spiral shell
Revolve the manipulation of paddle pitch.Helicopter had both been played in this way in VTOL, had been hovered, the good aerodynamic characteristic under low speed, and have simultaneously
For high lift-drag ratio characteristic of the fixed wing aircraft in fast state.
The function of the configuration helicopter screw propeller is to provide the forward direction pulling force of helicopter, balance main rotor reaction torque and
Differential control controls course movement.
It is studied by vertical passage trim, in hovering and low-speed stage, the pulling force of side propeller is negative value, another for discovery
Side is positive value, and with the increase of forward flight speed, two sides propeller pulling force is positive value, but initial tensile force is the spiral of negative value
Paddle, since tension variations amplitude is big, the propeller efficiency designed by standard empirical is lower, the efficiency under big Speed Flight state
40% or so is substantially only maintained, single propeller required horsepower is excessive.
The characteristics of pattern propeller is that the amplitude of variation range of generation pulling force is big, needs to meet simultaneously different operating conditions drop-downs
The demand of power, it is therefore necessary to carry out Aerodynamic optimization design for propeller.
Summary of the invention
The object of the present invention is to provide one kind to be able to solve for compound thrust configuration helicopter two sides propelling screws work
Make the method and system of the lower problem of efficiency, to improve the working efficiency of the configuration helicopter two sides propelling screws, thus into
One step promotes its flying quality.
To achieve the above object, the present invention provides following schemes:
A kind of geometric Parameters Optimization method for compound thrust configuration helicopter two sides propelling screws, the method packet
It includes:
Obtain the interrelated geometrical parameters and running parameter of compound thrust configuration helicopter two sides propelling screws；
Propeller design optimization model is established, which includes:
201) determine that the optimized variable in Optimized model, propeller design optimization variable include revolving speed, screw pitch, solidity
And taper ratio.
202) optimization aim in Optimized model, optimization aim are determined are as follows: with propeller works efficiency highest.
In method design, with floating state, cruising speed and the lower three propeller works efficiency of maximum forward flight speed
Maximum is used as objective function, distributes a weight coefficient to each state point.Wherein, floating state 0.3, cruising speed state are
0.5, maximum forward flight speed state is 0.2.
203) two constraint conditions are set in a model, and one is pulling force demand condition, and the propeller of body two sides needs
Meets the needs of respective forward direction pulling force.Secondly being reaction torque demand condition, the resultant moment that propeller generates needs to meet rotor anti-
The needs of torque.
Optimization method:
301) propeller geometric parameter is determined；
The determination method of airscrew diameter are as follows:
Wherein, MaR,kIndicate blade tip Mach number critical value, V indicates forward flight speed, nsIndicate revolution speed of propeller.
By setting the requirement of blade tip Mach number, airscrew diameter is found out.
The determination of propeller blade number is determined by required aerodynamic characteristic, efficiency and solidity.
Blade require foline must have in velocity interval and range of angles of attack big as far as possible higher lift resistance ratio and
More stable aerodynamic force.
The high performance airscrew that bladepiston drives high-power engine, according to airflow characteristic, thus preferably
Engine power is absorbed, it can be using rectangle or fan-shaped blade.
The screw pitch of propeller according in realistic model by the balance of power based on, provided after calculating.In view of two spirals
The sum of pulling force of paddle, provides preceding Xiang Lali, the difference of the pulling force of two propellers, the equalising torque antitorque of rotor of generation, therefore two
Difference is answered in the screw pitch setting of a propeller.It is negative value in the pulling force of hovering and low-speed stage, side propeller, the other side is positive
Value, with the increase of forward flight speed, two sides propeller pulling force is positive value.
Tentatively given propeller geometric parameter is as shown in table 1:
Table 1
| Project | Numerical value |
| Diameter (m) | 2.0 |
| Revolving speed (rpm) | 2200 |
| Aerofoil profile | Clark Y |
| Blade the piece number | 4-6 |
| Established angle (always away from) | It is variable |
| Right side airscrew pitch (inch) | 60 |
| Left screw screw pitch (inch) | 20 |
| Blade solidity | 0.191 |
| Taper ratio | 1 |
| Chord length b (m) | 0.1 |
302) propeller power model is established:
Propeller force modeling: rotor is dextrorotation, and floating state left screw provides positive pulling force, and right side propeller mentions
For negative pulling force to balance reaction torque.Propeller power, which calculates, uses momentum-foline combinatorial theory.Before required propeller
The pitch of left-and-right spiral paddle at this time is found out to pulling force, and the torque of two propellers is found out according to pitch.
303) by introducing pointer algorithm, for 304) required horsepower of floating state propeller, 305) cruising condition
Propeller required horsepower under the required horsepower of propeller and 306) max level speed state is calculated.
304) under floating state propeller required horsepower by calculate rotor reaction torque obtain the pulling force of each propeller,
It finds out the corresponding torque of propeller and the corresponding power of each propeller is calculated again.
P=M ω (2)
Wherein, M indicates that the torque of propeller, ω indicate propeller angular speed.
305) before -306) fly state under propeller required horsepower by calculate rotor reaction torque and it is preceding winged when full machine resistance
The pulling force of each propeller of power finds out the corresponding torque of propeller and the corresponding power of each propeller is calculated again.
307) often primary by 303) calculating, judge whether to reach default step number；
If 308) not up to default step number, which executes, first determines whether 304) -306) propeller pulling force calculate the result is that no full
Foot 202) -203) constraint requirements；
If not satisfied, then executing 309), propeller geometric parameter is modified, returns 301), recalculates；
If satisfied, then executing 310), the parameter point is collected, then is executed 309), propeller geometric parameter is modified, returns
301) it, recalculates；
If reaching default step number, execute 311), is searched in all bleeding points corresponding when propeller required horsepower minimum
Parameter point；
312) the propeller geometric parameter point is exported, operation is terminated；
The specific embodiment provided according to the present invention, the invention discloses following technical effects:
Compound thrust configuration helicopter more can be quickly and easily solved under different flight state using the present invention
The lower problem of two side-thrust propeller works efficiency, and the configuration range being applicable in includes but is not limited to as shown in Figure 1
Configuration.Pulling force amplitude range caused by propeller of the present invention for the configuration is larger and needs while meeting under different operating conditions
The characteristics of pulling force demand, using revolving speed, screw pitch, solidity and taper ratio as optimized variable, by Isight software, with propeller work
Make the minimum optimization aim of required horsepower generated, the parameter after being optimized, the propeller works after verifying discovery optimization
Efficiency is obviously improved before relatively optimizing.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
The attached drawing that need to be used is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention,
For those of ordinary skill in the art, without any creative labor, it can also obtain according to these attached drawings
Obtain other attached drawings.
The compound thrust configuration helicopter three-view diagram that Fig. 1 is applicable in but is not limited to for the present invention；
Fig. 2 is optimization system structure chart of the present invention to compound thrust configuration helicopter two sides propelling screws；
Fig. 3 is optimized flow chart of the present invention to compound thrust configuration helicopter two sides propelling screws operating condition
In obtained optimum results under different flying speeds rotor and propeller required horsepower comparison diagram；
Fig. 4-5 is the optimum results that the present invention obtains, i.e., the working efficiency of two sides propeller under different flying speeds；
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, this carries out the technical solution in inventive embodiments clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is with reference to the accompanying drawing and specific real to make above-mentioned purpose of the invention, feature and a little can be more obvious and easy to understand
Applying mode, the present invention is described in further detail.
Fig. 2-3 is system and method corresponding to the present invention.
Obtain the interrelated geometrical parameters and running parameter of compound thrust configuration helicopter two sides propelling screws；
201) propeller design optimization model is established, which includes:
202) determine that the optimized variable in Optimized model, propeller design optimization variable include revolving speed, screw pitch, solidity
And taper ratio.
203) optimization aim in Optimized model, optimization aim are determined are as follows: with propeller works efficiency highest.
In method design, with floating state, cruising speed and the lower three propeller works efficiency of maximum forward flight speed
Maximum is used as objective function, distributes a weight coefficient to each state point.Wherein, floating state 0.3, cruising speed state are
0.5, maximum forward flight speed state is 0.2.
204) two constraint conditions are set in a model, and one is pulling force demand condition, and the propeller of body two sides needs
Meets the needs of respective forward direction pulling force.Secondly being reaction torque demand condition, the resultant moment that propeller generates needs to meet rotor anti-
The needs of torque.
205) optimization method:
301) propeller geometric parameter is determined；
The determination method of airscrew diameter are as follows:
Wherein, MaR,kIndicate blade tip Mach number critical value, V indicates forward flight speed, nsIndicate revolution speed of propeller.
By setting the requirement of blade tip Mach number, airscrew diameter is found out.
The determination of propeller blade number is determined by required aerodynamic characteristic, efficiency and solidity.The propeller of more blades
It can reduce the diameter and blade width of propeller, to reduce frontal resistance, while can also effectively absorb engine and increase
The whole power given when adding forward flight speed and height.On the contrary, the efficiency of propeller can be reduced by increasing blade number, increase simultaneously
The quality of propeller.
In conjunction with the pulling force and duty requirements of sample helicopter, propeller blade number is determined as 6.
Blade require foline must have in velocity interval and range of angles of attack big as far as possible higher lift resistance ratio and
More stable aerodynamic force.By comparison Clark Y, Eppler 387, GOE 801, NACA 0009, S1012, five kinds of aerofoil profiles are waited,
It was found that the lift resistance ratio and torque coefficient of Clark Y aerofoil profile are more excellent.
The high performance airscrew that bladepiston drives high-power engine, according to airflow characteristic, thus preferably
Engine power is absorbed, it can be using rectangle or fan-shaped blade.
The screw pitch of propeller according in realistic model by the balance of power based on, provided after calculating.In view of two spirals
The sum of pulling force of paddle, provides preceding Xiang Lali, the difference of the pulling force of two propellers, the equalising torque antitorque of rotor of generation, therefore two
Difference is answered in the screw pitch setting of a propeller.It is negative value in the pulling force of hovering and low-speed stage, side propeller, the other side is positive
Value, with the increase of forward flight speed, two sides propeller pulling force is positive value.
Tentatively given propeller geometric parameter is as shown in table 1:
Table 1
| Project | Numerical value |
| Diameter (m) | 2.0 |
| Revolving speed (rpm) | 2200 |
| Aerofoil profile | Clark Y |
| Blade the piece number | 6 |
| Established angle (always away from) | It is variable |
| Right side airscrew pitch (inch) | 60 |
| Left screw screw pitch (inch) | 20 |
| Blade solidity | 0.191 |
| Taper ratio | 1 |
| Chord length b (m) | 0.1 |
The initial value of optimized variable and its value range are as shown in table 2:
Table 2
| Variable | Lower limit | The upper limit | Initial value |
| Solidity | 0.1 | 0.25 | 0.19 |
| Screw pitch | 0 | 100 | 20 |
| Taper ratio | 0.5 | 1 | 1 |
| Revolving speed | 1800 | 2600 | 2200 |
302) propeller power model is established:
Propeller force modeling: rotor is dextrorotation, and floating state left screw provides positive pulling force, and right side propeller mentions
For negative pulling force to balance reaction torque.Propeller power, which calculates, uses momentum-foline combinatorial theory.Before required propeller
The pitch of left-and-right spiral paddle at this time is found out to pulling force, and the torque of two propellers is found out according to pitch.
303) by introducing pointer algorithm, for 304) required horsepower of floating state propeller, 305) cruising condition
Propeller required horsepower under the required horsepower of propeller and 306) max level speed state is calculated.
304) under floating state propeller required horsepower by calculate rotor reaction torque obtain the pulling force of each propeller,
It finds out the corresponding torque of propeller and the corresponding power of each propeller is calculated again.
P=M ω (2)
Wherein, M indicates that the torque of propeller, ω indicate propeller angular speed.
305) before -306) fly state under propeller required horsepower by calculate rotor reaction torque and it is preceding winged when full machine resistance
The pulling force of each propeller of power finds out the corresponding torque of propeller and the corresponding power of each propeller is calculated again.
307) often primary by 303) calculating, judge whether to reach default step number；
If 308) not up to default step number, which executes, first determines whether 304) -306) propeller pulling force calculate the result is that no full
Foot 202) -203) constraint requirements；
If not satisfied, then executing 309), propeller geometric parameter is modified, returns 301), recalculates；
If satisfied, then executing 310), the parameter point is collected, then is executed 309), propeller geometric parameter is modified, returns
301) it, recalculates；
If reaching default step number, execute 311), is searched in all bleeding points corresponding when propeller required horsepower minimum
Parameter point；
312) the propeller geometric parameter point is exported, operation is terminated；
The propeller works efficiency value obtained under different flight state specifically includes following steps:
The first step determines the initial geometric parameter of compound thrust configuration helicopter two sides propeller.
Second step establishes two sides propeller power model.
Third step introduces pointer algorithm, and is calculated and hanged according to the configuration helicopter screw propeller required horsepower calculation method
Stop/cruise/maximum forward flight speed under propeller required horsepower.Calculate propeller required horsepower, wherein by rotor required horsepower
Antitorque of rotor is obtained, is generated when being calculated and flown before fuselage and wing at this time by the lift and helicopter forward flight speed of wing-borne
The reaction torque of resistance and its angle of attack, the resistance and rotor that generate when by flying before fuselage and wing obtains propeller collective effect at this time
The forward direction pulling force of generation finally calculates the required horsepower of propeller according to blade momentum theory method；
4th step judges whether to complete default calculating step number；
5th step, judges whether the propeller pulling force of three state points meets constraint condition；If not satisfied, then modifying spiral
Paddle geometric parameter, is recalculated；If satisfied, then collecting the parameter point, then propeller geometric parameter is modified, recalculated；
6th step completes default calculating step number, seeks propeller required horsepower smallest point in all bleeding points；
7th step exports propeller geometric parameter corresponding to the power smallest point after screening.
According to Fig. 4, Fig. 5 before optimization after, two sides propeller not ditto fly state under efficiency value, it can be seen that for
Left screw, its efficiency is inherently higher before optimizing, and optimization behind efficiency is further promoted, and substantially remains in close to 80% left side
The right side, and its efficiency value is too low for right side propeller, before optimizing, only 40% or so, and pass through the optimization of aerodynamic parameter, efficiency
It is worth up to 60%-80%, thus illustrates that this optimization method is feasible and effective.
Table 4 gives the parameter value of optimization front and rear sides propeller:
The present invention has the advantages that
(1) compound thrust configuration helicopter more can be easily solved using the present invention to work under different flight state
The lower problem of efficiency, and the configuration range being applicable in includes but is not limited to configuration as shown in Figure 1.
(2) pulling force amplitude range caused by propeller of the present invention for the configuration is larger and needs while meeting difference
The characteristics of operating condition lower pulling force demand, using revolving speed, screw pitch, solidity and taper ratio as optimized variable, by Isight software, with spiral shell
Revolve the minimum optimization aim of required horsepower that paddle work generates, the parameter after being optimized, the spiral after verifying discovery optimization
Paddle working efficiency is obviously improved before relatively optimizing.
Compared with prior art, the characteristics of present invention is according to compound thrust configuration helicopter, to pass through setting weight coefficient
Seeking propeller works efficiency under different flight state is up to target, and by efficiency highest, this optimization aim determines that two sides push away
Into the geometric parameter of propeller, to solve the compound thrust configuration helicopter of rotor/wing two sides under stable state state of flight
The lower problem of propelling screws working efficiency.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, similar portion may refer to each other between each embodiment.For the system disclosed in the embodiment,
Since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is referring to method part illustration
It can.
Used herein a specific example illustrates the principle and implementation of the invention, and above embodiments are said
It is bright to be merely used to help understand method and its core concept of the invention；At the same time, for those skilled in the art, foundation
Thought of the invention, there will be changes in the specific implementation manner and application range.In conclusion the content of the present specification is not
It is interpreted as limitation of the present invention.
Claims (7)
1. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws, which is characterized in that the method
The geometric parameter and running parameter for obtaining compound thrust configuration helicopter two sides propelling screws first, are then based on and establish spiral
Paddle pneumatic design Optimized model；The process specifically includes the following steps:
The first step determines that the optimized variable in Optimized model, propeller design optimization variable include revolving speed, screw pitch, solidity
And taper ratio；
Second step determines the optimization aim in Optimized model, optimization aim are as follows: with propeller works efficiency highest；With the shape that hovers
State, cruising speed and the maximum lower three propeller works efficiency maximums of forward flight speed give each state point as objective function
Distribute a weight coefficient；
Two constraint conditions are arranged in third step in a model, and first is pulling force demand condition, and the propeller of body two sides needs full
The demand of the respective forward direction pulling force of foot, second is reaction torque demand condition, and the resultant moment that propeller generates needs to meet rotor anti-twisted
The needs of square.
2. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws according to claim 1,
It is characterized in that, the process of the geometric parameter for obtaining two sides propeller and its running parameter specifically:
Firstly, determining airscrew diameter:
Wherein, MaR,kIndicate blade tip Mach number critical value, V indicates forward flight speed, nsIndicate propeller
Revolving speed,
By setting the requirement of blade tip Mach number, airscrew diameter is found out；
Secondly, the determination of propeller blade number is determined by required aerodynamic characteristic, efficiency and solidity；
Blade requires foline to have higher lift resistance ratio and more stable in velocity interval and range of angles of attack big as far as possible
Aerodynamic force；
The high performance airscrew that bladepiston drives high-power engine, according to airflow characteristic, to preferably absorb
Engine power, using rectangle or fan-shaped blade；
Finally, the screw pitch of propeller according in realistic model by the balance of power based on, obtained after calculating.
3. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws according to claim 1,
It is characterized in that, it is described according to the objective function, determine that propeller power required horsepower is minimum under different flight state, and look for
To corresponding geometric parameter values, specifically include:
By optimization algorithm, the optimal solution of the objective function is obtained；
The optimal solution is geometric parameter values corresponding to minimal power values in power library.
4. according to any one of claims 1 to 3 a kind of for compound thrust configuration helicopter two sides propelling screws
Optimization method, which is characterized in that the optimization method the following steps are included:
301) propeller geometric parameter is determined；
302) establish propeller power model: propeller force modeling: rotor is dextrorotation, and floating state left screw mentions
For positive pulling force, right side propeller provides negative pulling force to balance reaction torque；
Propeller power, which calculates, uses momentum-foline combinatorial theory；
Two spirals are found out according to the pitch for finding out left-and-right spiral paddle at this time before required propeller to pulling force, and according to pitch
The torque of paddle；
303) it by introducing pointer algorithm, needs to use for the required horsepower of floating state propeller, cruising condition propeller
Propeller required horsepower under power and max level speed state is calculated；
304) it is often calculated once by step 303), judges whether to reach default step number；
If not up to default step number, first determines whether each power computation of propeller meets constraint requirements；
If not satisfied, then modifying propeller geometric parameter, return step 301), it recalculates；
If satisfied, then collecting the parameter point, then modify propeller geometric parameter, return step 301), it recalculates；
If reaching default step number, execute: searching parameter point corresponding when propeller required horsepower minimum in all bleeding points；
308) the propeller geometric parameter point is exported, operation is terminated.
5. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws according to claim 4,
It is characterized in that, under floating state propeller required horsepower by calculate rotor reaction torque obtain the pulling force of each propeller,
It finds out the corresponding torque of propeller and the corresponding power of each propeller is calculated again:
P=M ω
Wherein, MaR,kIndicate blade tip Mach number critical value, V indicates forward flight speed, nsIndicate revolution speed of propeller；
Under preceding winged state propeller required horsepower by calculate rotor reaction torque and it is preceding winged when the complete each propeller of machine resistance
Pulling force, obtain the corresponding torque of propeller and the corresponding power of each propeller be calculated again.
6. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws according to claim 4,
It is characterized in that, propeller required horsepower computing module includes:
Floating state, lower propeller required horsepower obtain the pulling force of each propeller by calculating the reaction torque of rotor, find out spiral shell
The corresponding power of each propeller is calculated in the rotation corresponding torque of paddle again.Preceding winged state, is revolved according to rotor required horsepower
Wing reaction torque, the resistance generated when being calculated and flown before fuselage and wing at this time by the lift and helicopter forward flight speed of wing-borne and
Its angle of attack, the reaction torque of the resistance and rotor that generate when by flying before fuselage and wing obtain what propeller collective effect at this time generated
Forward direction pulling force calculates the required horsepower of propeller according to blade momentum theory method.
7. a kind of optimization method for compound thrust configuration helicopter two sides propelling screws according to claim 6,
It is characterized in that, obtaining the optimal solution of the objective function by optimization algorithm；The optimal solution is minimum power in power library
Parameter included in the corresponding propeller geometric parameter of value in optimized variable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251284.4A CN109969425B (en) | 2019-03-29 | 2019-03-29 | Optimization method for two-side propulsion propeller of composite thrust configuration helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251284.4A CN109969425B (en) | 2019-03-29 | 2019-03-29 | Optimization method for two-side propulsion propeller of composite thrust configuration helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109969425A true CN109969425A (en) | 2019-07-05 |
| CN109969425B CN109969425B (en) | 2022-07-08 |
Family
ID=67081775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910251284.4A Active CN109969425B (en) | 2019-03-29 | 2019-03-29 | Optimization method for two-side propulsion propeller of composite thrust configuration helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109969425B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
| CN112052532A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Helicopter dry running power spectrum design method |
| CN113742846A (en) * | 2021-09-08 | 2021-12-03 | 西北工业大学 | Optimization method, system and equipment for propelling optimal power unit of near space aircraft |
| CN113734425A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN114180076A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Composite thrust configuration helicopter/engine comprehensive control system and method |
| CN114818150A (en) * | 2022-06-28 | 2022-07-29 | 尚良仲毅(沈阳)高新科技有限公司 | Method and device for calculating dynamic tension of propeller |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4730795A (en) * | 1984-03-26 | 1988-03-15 | David Constant V | Heliplane |
| US20050151001A1 (en) * | 2003-07-02 | 2005-07-14 | Loper Arthur W. | Compound helicopter |
| CN101559832A (en) * | 2008-03-25 | 2009-10-21 | 尤洛考普特公司 | Fast hybrid helicopter with large range |
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN109018422A (en) * | 2018-07-10 | 2018-12-18 | 南京航空航天大学 | Determine revolving speed to vert corridor calculation method with the quadrotor that verts of feathering |
-
2019
- 2019-03-29 CN CN201910251284.4A patent/CN109969425B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4730795A (en) * | 1984-03-26 | 1988-03-15 | David Constant V | Heliplane |
| US20050151001A1 (en) * | 2003-07-02 | 2005-07-14 | Loper Arthur W. | Compound helicopter |
| CN101559832A (en) * | 2008-03-25 | 2009-10-21 | 尤洛考普特公司 | Fast hybrid helicopter with large range |
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN109018422A (en) * | 2018-07-10 | 2018-12-18 | 南京航空航天大学 | Determine revolving speed to vert corridor calculation method with the quadrotor that verts of feathering |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
| CN110588878B (en) * | 2019-09-20 | 2021-06-22 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
| CN112052532A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Helicopter dry running power spectrum design method |
| CN113742846A (en) * | 2021-09-08 | 2021-12-03 | 西北工业大学 | Optimization method, system and equipment for propelling optimal power unit of near space aircraft |
| CN113734425A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN113734425B (en) * | 2021-11-05 | 2022-02-08 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN114180076A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Composite thrust configuration helicopter/engine comprehensive control system and method |
| CN114180076B (en) * | 2021-11-19 | 2023-04-28 | 中国直升机设计研究所 | Composite thrust configuration helicopter/engine comprehensive control system and method |
| CN114818150A (en) * | 2022-06-28 | 2022-07-29 | 尚良仲毅(沈阳)高新科技有限公司 | Method and device for calculating dynamic tension of propeller |
| CN114818150B (en) * | 2022-06-28 | 2022-09-16 | 尚良仲毅(沈阳)高新科技有限公司 | Method and device for calculating dynamic tension of propeller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109969425B (en) | 2022-07-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109969425A (en) | A kind of two sides propelling screws optimization method for compound thrust configuration helicopter | |
| KR102471407B1 (en) | VTOL aircraft using rotors to simulate the dynamics of a rigid wing | |
| US8066219B2 (en) | Anhedral tip blades for tiltrotor aircraft | |
| CN109543271B (en) | Trimming control design method applied to coaxial high-speed helicopter with thrust propeller | |
| CN110334368B (en) | Flight dynamics modeling method for composite thrust configuration helicopter | |
| JP7401545B2 (en) | Rotor blades and their design methods | |
| US9061758B2 (en) | Noise and performance improved rotor blade for a helicopter | |
| CN109969426B (en) | Lift force distribution method and system for helicopter with composite thrust configuration | |
| CN205327411U (en) | Composite wing aircraft | |
| RU2716470C1 (en) | Method of blade improvement in order to increase its negative critical angle of attack | |
| JPH0341399B2 (en) | ||
| CN110901890A (en) | High-speed rotor craft with rotor capable of being designed in classification mode | |
| CN111907699A (en) | Helicopter rotor dynamic stall control structure based on whale fin-imitated leading edge | |
| CN109263932A (en) | A kind of multi-rotor aerocraft being vertically moved up or down | |
| CN211364914U (en) | Rotor craft's paddle and rotor craft | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN110228607A (en) | A kind of optimum design method based on round mixing parafoil | |
| CN111674546A (en) | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft | |
| CN112052528B (en) | Method for designing aerodynamic profile of novel rotor blade of helicopter | |
| CN103057703A (en) | Dual-rotor coaxial helicopter with wing-shaped rotors | |
| JP6856930B2 (en) | Rotor, drone and helicopter | |
| CN112572787A (en) | Coaxial dual-rotor high-speed helicopter tip airfoil with low resistance and high divergence Mach number | |
| KR20220038165A (en) | lift reinforcement assembly | |
| CN106218886A (en) | Many rotorcraft blades and many gyroplanes | |
| JPH11124093A (en) | Aerofoil for helicopter blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |