CN102495924A - Computer aided design device for integration performance optimization of airliner and fanjet and method thereof - Google Patents
Computer aided design device for integration performance optimization of airliner and fanjet and method thereof Download PDFInfo
- Publication number
- CN102495924A CN102495924A CN2011103894407A CN201110389440A CN102495924A CN 102495924 A CN102495924 A CN 102495924A CN 2011103894407 A CN2011103894407 A CN 2011103894407A CN 201110389440 A CN201110389440 A CN 201110389440A CN 102495924 A CN102495924 A CN 102495924A
- Authority
- CN
- China
- Prior art keywords
- fanjet
- engine
- population
- module
- design
- 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
Images
Classifications
-
- 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
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a computer aided design device for the integration performance optimization of an airliner and a fanjet and a method thereof, which belong to the technical field of aerial engines. The design device is characterized in that an input device, a central processing unit, an internal storage module, a storage device and a display device are connected through a data line. The internal storage module comprises a system program library, a system interactive operation window, a fanjet design module, a fanjet size/weight/resistance estimating module, an airliner flying performance simulation module and an airliner/fanjet integration performance optimizing module. The design device and the method can quickly and fully consider mutual requirements and effect of the technical parameter of the airliner and the fanjet, conduct performance matching calculation and evaluation of the existing airliners and the existing engines and performance matching calculation, optimization and evaluation research of the newly designed air liners and engines.
Description
Technical field
The invention belongs to the aero engine technology field, particularly relate to integrated performance optimization CAD apparatus of a kind of passenger plane and fanjet and method thereof.
Background technology
At present; The instrument that both at home and abroad in the disclosed document gas-turbine unit is carried out performance design and calculating comprises GSP, Turbomach, Gasturb, NPSS and ASP etc.; Document [1] sees reference: MachMillan W.L.Development of a Modular Type Program for the Calculation of Gas Turbine Off-design Performance.Ph.D.Thesis; C.I.T, September, 1974; List of references [2]: Sirinoglou A.Implementation of Variable Geometry for Gas Turbine Performance Simulation Turbomach Improvement.M.Sc.Thesis, C.I.T, September 1992; List of references [3]: Joachim Kurzke, Advanced User-friendly Gas Turbine Performance Calculations on a Personal Computer, ASME 95-GT-147; List of references [4]: Mark G.Turner; John A.Reed; Robert Ryder; Jospeh P.Veres, Multi-fidelity simulation of a turbofan engine with results zoomed into mini-maps for a zero-D cycle simulation, NASA/TM-2004-213076; List of references [5]: Tang Hailong, Zhang Jin.A Study of Object-Oriented Approach for Aero-engine Performance Simulation, Journal of Aerospace Power, 1999-04; List of references [6]: Wang bo, Tang Hai-long, Zhong Ru-hao, Chen Min.Visualize Framework for Aero-engine Performance Simulation [J], Journal of Aerospace Power, 2009-03.The instrument that flying quality is designed and calculates comprises Hermes etc.; Document [7] sees reference: Georgios Dougeris; Maelenn Toure, Anestis Kalfas and Pericles Pilids.Effect of Utilization Strategy on Greenhouse Emissions of a Short Haul Aircraft [J], Journal of Environment and Engineering; 2010 Vol (5), No.2.Yet the weak point of these design tools is that engine performance design tool and aeroplane performance design tool are separate, can't work in coordination with mutual requirement and the influence of considering aircraft and fanjet technical parameter.Yet; In the development process of civilian fanjet; In order to improve its development efficient; Need set up the integrated performance optimization CAD apparatus of passenger plane/fanjet, fast, comprehensively consider the mutual requirement and the influence of aircraft/fanjet technical parameter, satisfy the Performance Match calculating of existing aircraft and existing engine and assess, newly design the Performance Match of aircraft and new designed engines, the requirement of optimizing and assessing.Therefore integrated performance optimization CAD apparatus of passenger plane/fanjet and method thereof are technical matterss that needs to be resolved hurrily.
Summary of the invention
Fundamental purpose of the present invention is to provide a kind of passenger plane and integrated performance optimization CAD apparatus of fanjet and method thereof; Be applied on the computer system, can accomplish the integrated performance optimization design effort of airliner/fanjet efficiently.
The integrated performance optimization CAD apparatus of passenger plane of the present invention and fanjet; Comprise input equipment, central processing unit, memory modules, memory device and display device; Above-mentioned input equipment, memory modules, memory device and display device all are connected with central processing unit through data line; Described memory modules comprises following system module: (a) system library; Wherein prestore the integrated performance optimization program of passenger plane/fanjet, comprise fanjet overall performance simulated program, fanjet size/weight/resistance estimate program, passenger traffic performance simulation program, the integrated performance optimization program of passenger plane/fanjet with C# class libraries form tissue; (b) system interaction formula operating window; The designer can inspire each function design module through the menu in the operating window; Utilize the input of drop-down each the function module design parameter of dialog box completion in the menu option, design result or Optimization result are presented on the computer screen; (c) fanjet design module; Can in operating window, define demand thrust, the loop parameter of fanjet by the designer; The component feature parameter is selected in system library and operation fanjet overall performance simulated program, and the acquisition design result also is presented on the computer screen.(d) fanjet size/weight/resistance estimate module; The designer defines the characteristic dimension and the weight of baseline engine in operating window; Select and operation fanjet size/weight/resistance estimate program, can obtain weight and the outer form drag deviate of institute's design engine with respect to the baseline engine.(e) passenger traffic performance simulation module; The designer defines aircraft geometric parameter, weight parameter, flight parameter and engine bed number in operating window; In system library, select and operation passenger traffic performance simulation program, design result is presented on the computer screen; (f) the integrated performance optimization module of passenger plane/fanjet; Can on operating window, define the range of choice and the constraint of engine installation dimension of engine optimization variable parameter by the designer; Accomplish total amount of fuel minimum that the particular flight task consumed as optimization aim with passenger plane; In system library, select and the integrated performance optimization module of operation passenger plane/fanjet; Obtain optimum engine cycles parameter and each leg performance of passenger plane, and be presented on the computer screen, to carry out the reference frame that the engine cycles parameter is selected as the designer.
Utilize the present invention; Can fast, comprehensively consider the mutual requirement and the influence of aircraft and fanjet technical parameter, carry out the Performance Match of existing aircraft and existing engine and calculate Performance Match calculating, optimization and the evaluation studies that with assessment, newly designs aircraft and new designed engines.
Fanjet design module in the memory modules, fanjet size/weight/resistance estimate module, passenger traffic performance simulation module can be carried out corresponding operation separately, satisfy different user's requests.
Description of drawings
Fig. 1 is the Organization Chart of passenger plane provided by the invention and the integrated performance optimization CAD apparatus of fanjet;
Fig. 2 is the structural representation of the input of fanjet design module among the present invention;
Fig. 3 is the detailed structure synoptic diagram of the input of fanjet size/weight/resistance estimate module among the present invention;
Fig. 4 is the detailed structure synoptic diagram of the input of passenger traffic performance simulation module among the present invention;
Fig. 5 is the structural representation of the input of the integrated performance optimization module of passenger plane/fanjet among the present invention;
Fig. 6 is the process flow diagram of passenger plane provided by the invention and the integrated performance optimization computer-implemented method of fanjet;
Fig. 7 is the class formation organization chart of fanjet overall performance simulated program 31-1 among the present invention;
Fig. 8 is the class formation organization chart of fanjet size/weight among the present invention/resistance estimate program 31-2;
Fig. 9 is the class formation organization chart of passenger traffic performance simulation program 31-3 among the present invention;
Figure 10 is the class formation organization chart of passenger plane and the integrated performance optimization program of fanjet 31-4 among the present invention.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is elaborated.
As shown in Figure 1, be the structural representation of the integrated performance optimization CAD apparatus of passenger plane of the present invention and fanjet.This CAD apparatus can be desktop PC or portable computer, and its basic hardware framework comprises input equipment 1, central processing unit 2, memory modules 3, memory device 4 and display device 5.
Described input equipment 1 is used for input and controls instruction or correlation parameter to central processing unit 2, and it comprises a keyboard, mouse or other input media.Described central processing unit 2 is used for carrying out all programs of memory modules 3, and the dominant frequency of central processing unit 2 requires more than 1.0G, and memory modules 3 needed spaces are at least 256M.Memory device 4 is used to preserve the design result of above-mentioned passenger plane and the integrated performance optimization CAD apparatus of fanjet, can be a hard disk or flash memory, and the space guarantees 500M at least.Display device 5 is used to show the operating window of corresponding module, and the prompting designer imports the correlation parameter of appointment, and the display design result, can be LCD or projector equipment.Above-mentioned input equipment 1, memory modules 3, memory device 4 and display device 5 all are connected with central processing unit 2 with power lead through data line.
As shown in Figure 2, be the input parameter of fanjet design module 33 among the present invention and output result's detailed structure synoptic diagram.The designer comprises [input parameter] and [output result] through system interaction formula operating window 32 and fanjet design module 33 mutual data.The ground floor classification of [input parameter] comprises [design point demand performance parameter], [design point loop parameter], [design point height and Mach number], [design point component feature parameter], [off-design point control law].Wherein, [design point demand performance parameter] is meant demand thrust; Second layer classification under [design point loop parameter] comprises [bypass ratio], [turbine inlet temperature], [overall pressure ratio]; Second layer classification under [design point component feature parameter] comprises [rotary part efficient], [rotary part pressure ratio], [on-rotatably moving part total pressure recovery coefficient], [burner efficiency].The ground floor classification of [output result] comprises [data] and [graphic presentation], and wherein, the second layer classification under [data] comprises [design point oil consumption rate], [design point flow] and [takeoff thrust capability]; Second layer classification under [graphic presentation] comprises [speed altitude response] and [temperature characterisitic].After the prompting input designated parameter of designer according to fanjet design operation form; Fanjet design module 33 operation fanjet overall performance simulated program 31-1, acquisition fanjet design point performance and off-design point performance will be exported the result according to above-mentioned output form and be presented on the display device 5.
As shown in Figure 3, be the detailed structure synoptic diagram of the input of fanjet size/weight/resistance estimate module 34 among the present invention.The designer comprises [input parameter] and [output result] through system interaction formula operating window 32 and fanjet size/weight/resistance estimate module 34 mutual data.The ground floor classification of [input parameter] comprises [baseline engine blower diameter], [baseline engine weight], [target engine characteristic parameter].Wherein, the classification of the second layer under [target engine characteristic parameter] comprises [fan design point Mach number], [fan hub ratio], [design point flow].The ground floor classification of [output result] comprises [target engine characteristic dimension], [target engine weight correction], [target engine resistance correction]; Wherein, the classification of the second layer under [target engine characteristic dimension] comprises [nacelle maximum gauge], [nacelle length], [fan diameter].After the prompting input designated parameter of designer according to fanjet size, weight, resistance estimate operating window; Fanjet size/weight/resistance estimate module 34 operation fanjet size/weight/resistance estimate program 31-2 obtain parameter such as fanjet size, weight, outer form drag and will export the result according to above-mentioned output form to be presented on the display device 5.
Fig. 4 is the detailed structure synoptic diagram of the input of passenger traffic performance simulation module 35 among the present invention.The designer comprises [input parameter] and [output result] through system interaction formula operating window 32 and passenger traffic performance simulation module 35 mutual data.The ground floor classification of [input parameter] comprises [geometric parameter], [weight parameter], [aerodynamic parameter], [flight parameter] and [engine bed number].Wherein, the classification of the second layer under [geometric parameter] comprises [fuselage length], [wing area]; Second layer classification under [weight parameter] comprises [Gross Weight Takeoff], [Maximum Fuel], [engine weight correction]; Second layer classification under [aerodynamic parameter] comprises [engine drag correction], [aircraft polar]; Second layer classification under [flight parameter] comprises [voyage], [cruising altitude] and [cruise Mach number], and wherein, the ground floor of [output result] classification comprises [data] and [curve].Second layer classification under [data] comprises [total flight time], [total fuel consume]; Second layer classification under [curve] comprises [passenger plane weight change rule], [motor power Changing Pattern], [passenger plane change in resistance rule] and [passenger plane flight-path angle Changing Pattern].After the prompting input designated parameter of designer according to passenger traffic capability operation form, passenger traffic performance simulation module 35 operation simulated program 31-3, acquisition passenger traffic performance will be exported the result according to above-mentioned output form and be presented on the display device 5.
Fig. 5 is the detailed structure synoptic diagram of the input of the integrated performance optimization module 36 of the passenger plane/fanjet among the present invention.The designer comprises [input parameter] and [output result] through system interaction formula operating window 32 and the integrated performance optimization module 36 mutual data of passenger plane/fanjet.The ground floor classification of [input parameter] comprises [genetic algorithm parameter], [engine optimization parameter] and [constraint of engine installation dimension].Wherein, the classification of the second layer under [genetic algorithm parameter] comprises [initial population number], [optimization algebraically], [variation probability] and [crossover probability]; Second layer classification under [engine optimization parameter] comprises [bypass ratio scope], [overall pressure ratio scope], [turbine inlet temperature scope].The ground floor classification of [output result] comprises [data] and [curve].Second layer classification under [data] comprises [optimal engine overall pressure ratio], [optimal engine turbine inlet temperature], [optimal engine bypass ratio] and [total fuel consumption]; Second layer classification under [curve] comprises [each leg performance].After the prompting input designated parameter of designer according to the integrated performance optimization operating window of passenger plane/fanjet; The integrated performance optimization module 36 operation simulated programs of passenger plane/fanjet 3 1-4, the integrated optimization performance of acquisition passenger plane/fanjet will be exported the result according to above-mentioned output form and be presented on the display device 5.
Fig. 6 is the process flow diagram of the integrated performance optimization computer-implemented method of passenger plane/fanjet of the present invention, and concrete method for designing step is:
The first step; Central processing unit 1 start-up system interactive operation form 32; The designer selects a design subject through the window menu of corresponding fanjet design operation form, fanjet size, weight, resistance estimate operating window, passenger traffic capability operation form and the integrated performance optimization operating window of passenger plane/fanjet in system interaction form 32, described design subject is meant fanjet design module 33, fanjet size/weight/resistance estimate module 34, passenger traffic performance simulation module 35 and the integrated performance optimization module 36 of passenger plane/fanjet in the memory modules 3.
In second step, central processing unit 1 switches to the operating window of corresponding module.The designer is according to the prompting input designated parameters of the operating window of corresponding module; For example; If what switch is fanjet design module 33; Then pairing is exactly fanjet design operation form, needs the designated parameter of input to comprise design point demand performance parameter, design point loop parameter, design point height and Mach number, design point component feature parameter and off-design point control law; If what switch is fanjet size/weight/resistance estimate module 34; Then pairing is exactly fanjet size/weight/resistance estimate operating window, needs the designated parameter of input to comprise baseline engine blower diameter, baseline engine weight and target engine characteristic parameter; If what switch is passenger traffic performance simulation module 35; Then pairing is exactly passenger traffic performance simulation operating window, needs the designated parameter of input to comprise engine bed number on passenger plane geometric parameter, passenger plane weight parameter, passenger plane aerodynamic parameter, passenger traffic parameter and the passenger plane; If what switch is the integrated performance optimization module 36 of passenger plane/fanjet; Then pairing is exactly the integrated performance optimization operating window of passenger plane/fanjet, needs the designated parameter of input to comprise genetic algorithm parameter, engine optimization parameter and the constraint of engine installation dimension.
The 3rd step; The corresponding program of central processing unit 2 operation corresponding modules; For example, fanjet design module 33 corresponding programs are that fanjet overall performance simulated program 31-1, fanjet size/weight/resistance estimate module 34 corresponding programs are that fanjet size/weight/resistance estimate program 31-2, passenger traffic performance simulation module 35 corresponding programs are that the integrated performance optimization module 36 corresponding programs of passenger traffic performance simulation program 31-3, passenger plane/fanjet are the integrated performance optimization program of passenger plane/fanjet 31-4; Obtain corresponding design result, and be presented on the display device 5, as being the Performance Match that newly designs aircraft and new designed engines, the foundation of optimizing and assessing with the form of figure (curve) or data.Described design result is promptly exported the result, the output result shown in Fig. 2-Fig. 5.
The 4th step was saved to design result in the memory device 4, so that directly design result is read from memory device 4 when needing.
In the above-mentioned first step,, then can accomplish the calculating operation of fanjet performance if the design subject of selecting is a fanjet design module 33; If the design subject of selecting is fanjet size/weight/resistance estimate module 34, then can accomplish the estimation operation of size, weight and the resistance of fanjet; If the design subject of selecting is a passenger traffic performance simulation module 35, then can accomplish the simulation operations of passenger traffic performance; If select the integrated performance optimization module 36 of passenger plane/fanjet, then can accomplish the integrated performance optimization operation of passenger plane/fanjet.
If needed, carry out the first step～the 4th step again, the size of change input parameter is to accomplish the integrated optimization in Properties design effort of dissimilar passenger plane/fanjets.
The innovative point of the integrated performance optimization computer-implemented method of passenger plane/fanjet provided by the invention comprises 2 points; One of which is the class institutional framework division methods of fanjet overall performance simulated program 31-1, fanjet size/weight/resistance estimate program 31-2, passenger traffic performance simulation program 31-3, the integrated performance optimization program of passenger plane/fanjet 31-4 in system library 31, and is as follows:
1) fanjet overall performance simulated program 31-1 adopts the Object oriented programming implementation method; Whole procedure is encapsulated as [fanjet performance simulation class]; According to passenger plane in different legs different to the thrust requirements of engine and control law, derive from and be fanjet [taking off], [climbing], [cruising], [downslide] and [landing] five sub-category.Fig. 7 has provided the class formation organization chart of fanjet overall performance simulated program 31-1.
2) fanjet size/weight/resistance estimate program 31-2 adopts the Object oriented programming implementation method, and whole procedure is encapsulated as [propulsion system class], comprises that 3 sub-category are respectively [size compute classes], [weight compute classes] and [calculation of resistance class].Fig. 8 has provided the class formation organization chart of fanjet size/weight/resistance estimate program 31-2.
3) passenger traffic performance simulation program 3 1-3 use the Object oriented programming implementation method, and whole procedure is encapsulated as [flying quality emulation class], and such derives [type of taking off], [type of climbing], [type of cruising], [class glides] and [class of landing] five one-level subclasses.[climbing] one-level subclass derives from [the equivalent air speed is climbed] and [waiting Mach number to climb] secondary subclass again, and [downslide] one-level subclass derives [downslide of equivalent air speed] and [waiting Mach number to glide] secondary subclass again.Fig. 9 has provided the class formation organization chart of passenger traffic performance simulation program 31-3.
4) the integrated performance optimization program of passenger plane/fanjet 31-4 adopts the Object oriented programming implementation method; Whole procedure is encapsulated as [aircraft/engine integration performance optimization class], comprises that 5 one-level subclasses are respectively [parent selection class], [parent intersection class], [flying quality fitness compute classes], [genetic mutation class], [population replacement class].Wherein, [flying quality fitness compute classes] derives 3 secondary subclasses [fanjet performance simulation class], [propulsion system class], [flying quality emulation class] again, and Figure 10 has provided the class formation organization chart of integrated performance optimization program 3 1-4 of passenger plane/fanjet.
Another innovative point of the integrated performance optimization computer-implemented method of passenger plane/fanjet provided by the invention is that the integrated performance optimization module 36 of passenger plane/fanjet utilizes genetic algorithm to carry out the optimizing of engine scheme performance.The method step introduction is following:
Optimizing process is since [the engine scheme optimization parameter] of one group of stochastic distribution, and this group [engine scheme optimization parameter] is known as initial population.Individuality in the population specifically is characterized by [engine scheme optimization parameter], comprises [bypass ratio], [turbine inlet temperature], [overall pressure ratio] three parameters.Population individual through [genetic mutation class] with [parent intersect type] variation and intersection and generate new individuality, genetic algorithm always expects that the individuality of filial generation is better than the individuality of parent, fine or not standard is referred to as fitness.In [the integrated performance optimization module of passenger plane/fanjet], utilize [flying quality fitness compute classes] to calculate and accomplish aerial mission needed [total fuel consume] as the individual fitness of population; [total fuel consume] is more little; Fitness is good more, and the individuality of population is just good more.When variation with intersect new population individuality that the back occurred to satisfy under the prerequisite of [size of engine is installed and retrained] fitness good more; Just think that in this algorithm the individual existence appropriateness of this population is than higher; According to the rule of the genetic development survival of the fittest, the chance that it participates in the new population individuality of structure is just big more.Following steps S1-S8 carries out the optimizing step of aircraft/engine integration performance for [the integrated performance optimization module of passenger plane/fanjet] adopts genetic algorithm:
S1. " generation initial population ", promptly given [initial population number] m and [optimization algebraically] n, according to the range of choice of [engine scheme optimization parameter], central processing unit 2 produces initial population at random; Wherein m and n are positive integer.This initial population is as the parent population.
S2. " the individual engine performance of population is calculated "; Promptly to each individuality in the population; The secondary subclass [fanjet performance simulation class] that central processing unit 2 calls among the integrated performance optimization program of the passenger plane/fanjet that leaves in the memory modules 3 31-4 is carried out the individual engine performance calculating of population, and result of calculation comprises [design point oil consumption rate], [design point flow] and [takeoff thrust capability]; Computation process is exactly to realize according to the fanjet design module, like Fig. 2.
S3. " individual size of engine, weight and the resistance correction factor of population calculates "; The secondary subclass [propulsion system class] that [design point flow], [takeoff thrust capability] promptly calculated according to step S2, central processing unit 2 are called among the integrated performance optimization program of the passenger plane/fanjet 31-4 is calculated population individual [target engine characteristic dimension] and [target engine weight correction] and [target engine resistance correction].Wherein, the second layer of [target engine characteristic dimension] classification comprises [nacelle maximum gauge], [nacelle length], [fan diameter].[design point flow] is formula (1) with the correction relation of [fan diameter]:
D
fan＝1.49718+0.00166*W
a-1.9136e-7*W
a 2 (1)
In the formula (1), D
FanBe [fan diameter] that unit is m; W
aBe [design point flow] that unit is kg/s.
The individual engine weight computing formula of population is (2)
W
engine＝(0.16*T
staticmax+921) (2)
In the formula (2), W
EngineBe the individual engine weight of population, T
StaticmaxBe population individual [takeoff thrust capability].
Formula (3) has provided individual [target engine weight correction] the δ W of population
EngineDefinition, wherein, W
BaseBe [baseline engine weight].
δW
engine＝W
engine-W
base (3)
Individual [the target engine resistance correction] of population is formula (4)
δC
D/C
D＝0.15657-0.37544*(D
fan/D
fanbase)+0.21886*(D
fan/D
fanbase)
2 (4)
In the formula (4), δ C
D/ C
DBe population individual [target engine resistance correction], D
Fan/ D
FanbaseBe the engine [fan diameter] of population individuality and the ratio of [baseline engine blower diameter].δ C
D, C
D, D
FanbaseBe respectively resistance correction absolute magnitude, resistance coefficient, baseline engine blower diameter.
S4. " the individual engine fitness of population calculates "; Individual [the target engine resistance correction] of population that central processing unit 2 utilizes step S3 to obtain revised [aircraft polar]; Utilize [target engine weight correction] that [Gross Weight Takeoff] revised; And call secondary subclass [the flying quality emulation class] calculating [total fuel consume] in [the integrated performance optimization program of passenger plane/fanjet], and as the individual fitness of this population.
S5. " calculating of population ideal adaptation degree ": the individuality in 2 pairs of populations of central processing unit repeats S2-S4 step m time; Accomplish the individual fitness calculating of all populations in the initial population, be saved in individuality best in the initial population [GM] in the memory device 4 according to fitness.
S6. " generation progeny population ":
(S6-0) select: the fitness individual according to the parent population, utilize [parent is selected class] that all individualities are sorted, therefrom select two best parent populations individual, directly as 2 individuals in the progeny population;
(S6-1) intersect: according to given [crossover probability], utilize [parent intersection class] to intersect two parent population individualities at random to produce two new offspring individuals;
(S6-2) variation:, utilize [genetic mutation class] that two filial generation individualities of (S6-1) generating step are made a variation and produce two new offspring individuals according to given [variation probability];
Repeat (S6-1)～(S6-2) step (m-2)/2 time, generate remaining m-2 individuals in the progeny population.
S7. " replacement ": the individuality in 2 pairs of filial generation populations of central processing unit repeats the S2-S4 step and carries out fitness calculating for m time; Choose the best individuality [LM] in this generation population according to the size of fitness; And compare with best individuality [GM] in the previous generation population; If the fitness of [LM] is better than [GM], [population replacement class] composed the value of [LM] to [GM] and is saved in the memory device 4, otherwise [GM] remains unchanged;
S8. " test ": according to default [optimization algebraically] n, central processing unit 2 repeats S6-S7 step n time, and is saved in best individuality [GM] and corresponding [total fuel consumption] output thereof in the memory device 4, and on display device 5, shows.In this article, final [GM] refers to the set of [optimal engine pressure ratio], [optimal engine turbine inlet temperature], [optimal engine bypass ratio] these three parameters.
Optimized Algorithm in the integrated performance optimization module 36 of described passenger plane/fanjet can also adopt like optimized Algorithm such as simulated annealing, ant crowd, population except adopting the genetic algorithm.
Combine it; The present invention's [integrated performance optimization CAD apparatus of passenger plane/fanjet and method thereof] is applied on the computer system; The designer selects the design subject on system interaction formula operating window 32; And according to prompting input designated parameters; Accomplish the emulation of fanjet overall performance, fanjet size/weight/resistance estimate, passenger traffic performance simulation, the integrated performance optimization design of passenger plane/fanjet by system of the present invention; And emulation and the design result form with graphic presentation and data declaration is presented on the computer screen, Aided Design personnel accomplish the integrated performance optimization design of passenger plane/fanjet expeditiously.
Claims (8)
1. the integrated performance optimization CAD apparatus of passenger plane and fanjet; It is characterized in that: described design apparatus comprises input equipment (1), central processing unit (2), memory modules (3), memory device (4) and display device (5); Described input equipment (1) is used for input and controls instruction or correlation parameter to central processing unit (2); Described central processing unit (2) is used for carrying out all programs of memory modules (3); Memory device (4) is used to preserve the design result of above-mentioned passenger plane and the integrated performance optimization CAD apparatus of fanjet; Display device (5) is used for the display operation form; The prompting designer imports the correlation parameter of appointment, and the display design result, and above-mentioned input equipment (1), memory modules (3), memory device (4) and display device (5) all are connected with central processing unit (2) through data line;
Be provided with system library (31), system interaction formula operating window (32), fanjet design module (33), fanjet size/weight/resistance estimate module (34), passenger traffic performance simulation module (35) and the integrated performance optimization module of passenger plane/fanjet (36) in the memory modules (3);
Wherein, Four programs of system library (31) storage comprise fanjet overall performance simulated program (31-1), fanjet size/weight/resistance estimate program (31-2), passenger traffic performance simulation program (31-3), the integrated performance optimization program of passenger plane/fanjet (31-4); System interaction formula operating window (32) act as: the designer inspires fanjet design module (33), fanjet size/weight/resistance estimate module (34), passenger traffic performance simulation module (35) and the integrated performance optimization module of passenger plane/fanjet (36) in the memory modules (3) through the menu in the system interaction formula operating window (32); Utilize the input of drop-down each the functional module correlation parameter of dialog box completion in the menu option, design result or Optimization result are presented on the display device (5); Fanjet design module (33) is used to show fanjet design operation form; In fanjet design operation form, define [design point demand performance parameter], [design point loop parameter], [the design point component feature parameter] and [off-design point control law] of fanjet by the designer; In system library (31), select and operation fanjet overall performance simulated program (31-1), the acquisition design result also is presented on the computer screen of display device (5); Fanjet size/weight/resistance estimate module (34) is used to show fanjet size, weight, resistance estimate operating window; The designer imports [baseline engine blower diameter], [baseline engine weight] and [target engine characteristic parameter] in fanjet size, weight, resistance estimate operating window; Select and operation fanjet size/weight/resistance estimate program (31-2), obtain [target engine characteristic dimension], [target engine weight correction] and [target engine resistance correction]; Passenger traffic performance simulation module (35) is used to show passenger traffic performance simulation operating window; The designer defines aircraft [geometric parameter], [weight parameter], [aerodynamic parameter], [flight parameter] and [engine bed number] in passenger traffic performance simulation operating window; In system library (31), select and operation passenger traffic performance simulation program (31-3), simulation result is presented on the computer screen of display device (5); The integrated performance optimization module of passenger plane/fanjet (36) shows the integrated performance optimization operating window of passenger plane/fanjet; On the integrated performance optimization operating window of passenger plane/fanjet, define [genetic algorithm parameter], [engine optimization parameter] and [constraint of engine installation dimension] by the designer; [total fuel consumption] so that passenger plane completion particular flight task is consumed is minimum as optimization aim; In system library (31), select and the operation integrated performance optimization program of passenger plane/fanjet (31-4), optimization Simulation result is presented on the computer screen of display device (5).
2. the integrated performance optimization CAD apparatus of passenger plane according to claim 1 and fanjet is characterized in that: in the fanjet design module (33), [design point demand performance parameter] is meant demand thrust; [design point loop parameter] comprises [bypass ratio], [turbine inlet temperature] and [overall pressure ratio]; [design point component feature parameter] comprises [rotary part efficient], [rotary part pressure ratio], [on-rotatably moving part total pressure recovery coefficient] and [burner efficiency]; Design result i.e. [output result] comprises [data] and [graphic presentation]; Wherein, [data] comprise [design point oil consumption rate], [design point flow] and [takeoff thrust capability]; [graphic presentation] comprises [speed altitude response] and [temperature characterisitic].
3. the integrated performance optimization CAD apparatus of passenger plane according to claim 1 and fanjet; It is characterized in that: in fanjet size/weight/resistance estimate module (34), [target engine characteristic parameter] comprises [fan design point Mach number], [fan hub ratio], [design point flow]; Design result i.e. [output result] comprises [target engine characteristic dimension], [target engine weight correction] and [target engine resistance correction]; Wherein, [target engine characteristic dimension] comprises [nacelle maximum gauge], [nacelle length] and [fan diameter].
4. the integrated performance optimization CAD apparatus of passenger plane according to claim 1 and fanjet is characterized in that: in the passenger traffic performance simulation module (35), comprise [fuselage length] and [wing area] at [geometric parameter]; [weight parameter] comprises [Gross Weight Takeoff], [Maximum Fuel] and [engine weight correction]; [aerodynamic parameter] comprises [engine drag correction] and [aircraft polar]; [flight parameter] comprises [voyage], [cruising altitude] and [cruise Mach number], and wherein, simulation result i.e. [output result] comprises [data] and [curve], and [data] comprise [total flight time] and [total fuel consume]; [curve] comprises [passenger plane weight change rule], [motor power Changing Pattern], [passenger plane change in resistance rule] and [passenger plane flight-path angle Changing Pattern].
5. the integrated performance optimization CAD apparatus of passenger plane according to claim 1 and fanjet; It is characterized in that: in the integrated performance optimization module of passenger plane/fanjet (36), [genetic algorithm parameter] comprises [initial population number], [optimization algebraically], [variation probability] and [crossover probability]; [engine optimization parameter] comprises [bypass ratio scope], [overall pressure ratio scope] and [turbine inlet temperature scope]; Design result i.e. [output result] comprises [data] and [curve], and [data] comprise [optimal engine overall pressure ratio], [optimal engine turbine inlet temperature], [optimal engine bypass ratio] and [total fuel consumption]; [curve] is meant [each leg performance] curve.
6. the integrated performance optimization CAD apparatus of passenger plane according to claim 1 and fanjet; It is characterized in that: fanjet overall performance simulated program (31-1) adopts the Object oriented programming implementation method; Whole procedure is encapsulated as [fanjet performance simulation class]; According to passenger plane in different legs different to the thrust requirements of engine and control law, derive from and be fanjet [taking off], [climbing], [cruising], [downslide] and [landing] five sub-category;
Fanjet size/weight/resistance estimate program (31-2) adopts the Object oriented programming implementation method, and whole procedure is encapsulated as [propulsion system class], comprises that 3 sub-category are respectively [size compute classes], [weight compute classes] and [calculation of resistance class];
Passenger traffic performance simulation program (31-3) is used the Object oriented programming implementation method; Whole procedure is encapsulated as [flying quality emulation class]; Such derives [type of taking off], [type of climbing], [type of cruising], [class glides] and [class of landing] five one-level subclasses; [climbing] one-level subclass derives from [the equivalent air speed is climbed] and [waiting Mach number to climb] secondary subclass again, and [downslide] one-level subclass derives [downslide of equivalent air speed] and [waiting Mach number to glide] secondary subclass again;
The integrated performance optimization program of passenger plane/fanjet (31-4) adopts the Object oriented programming implementation method; Whole procedure is encapsulated as [aircraft/engine integration performance optimization class]; Comprise that 5 one-level subclasses are respectively [parent selection class], [parent intersection class], [flying quality fitness compute classes], [genetic mutation class], [population replacement class]; Wherein, [flying quality fitness compute classes] derives 3 secondary subclasses [fanjet performance simulation class], [propulsion system class], [flying quality emulation class] again.
7. the integrated performance optimization computer-implemented method of passenger plane and fanjet is characterized in that comprising the steps:
The first step; Central processing unit (1) start-up system interactive operation form (32); The designer selects the design subject in system interaction form (32), described design subject is meant fanjet design module (33), fanjet size/weight/resistance estimate module (34), passenger traffic performance simulation module (35) and the integrated performance optimization module of passenger plane/fanjet (36) in the memory modules (3);
In second step, central processing unit (1) switches to the operating window of corresponding module in the first step, and the designer is according to the input parameter of the prompting input appointment of the operating window of corresponding module;
The 3rd step; The corresponding program of central processing unit (1) operation corresponding module, the program that fanjet design module (33) is corresponding are that fanjet overall performance simulated program (31-1), the corresponding program of fanjet size/weight/resistance estimate module (34) are that fanjet size/weight/resistance estimate program (31-2), the corresponding program of passenger traffic performance simulation module (35) are that passenger traffic performance simulation program (31-3), the corresponding program of the integrated performance optimization module of passenger plane/fanjet (36) are the integrated performance optimization program of passenger plane/fanjet (31-4); Obtain corresponding design result after the program run, and be presented on the display device (5) with the form of graph curve or data;
In the 4th step, design result is saved in the memory device (4); This has promptly accomplished an integrated performance optimization computer-aided design (CAD) of passenger plane/fanjet.
8. the integrated performance optimization computer-implemented method of passenger plane according to claim 7 and fanjet; It is characterized in that: [the integrated performance optimization module of passenger plane/fanjet] adopts genetic algorithm to carry out the optimizing of the integrated performance of passenger plane/fanjet, and concrete steps are following:
S1. " generation initial population ", promptly given [initial population number] m and [optimization algebraically] n, according to the range of choice of [engine scheme optimization parameter], central processing unit (2) produces initial population at random; Wherein m is positive even numbers and m >=100, and n is positive integer and n >=100; This initial population is as the parent population;
S2. " the individual engine performance of population is calculated "; Promptly to each individuality in the population; The secondary subclass [fanjet performance simulation class] that central processing unit (2) calls in the integrated performance optimization program of the passenger plane/fanjet that leaves in the memory modules (3) (31-4) is carried out the individual engine performance calculating of population, and result of calculation comprises [design point oil consumption rate], [design point flow] and [takeoff thrust capability]; Computation process is exactly to realize according to the fanjet design module;
S3. " individual size of engine, weight and the resistance correction factor of population calculates "; [design point flow], [takeoff thrust capability] promptly calculated according to step S2; The secondary subclass [propulsion system class] that central processing unit (2) calls among the integrated performance optimization program of the passenger plane/fanjet 31-4 is calculated population individual [target engine characteristic dimension] and [target engine weight correction] and [target engine resistance correction]; Wherein, The second layer classification of [target engine characteristic dimension] comprises [nacelle maximum gauge], [nacelle length], [fan diameter], and [design point flow] is formula (1) with the correction relation of [fan diameter]:
D
fan＝1.49718+0.00166*W
a-1.9136e-7*W
a 2 (1)
In the formula (1), D
FanBe [fan diameter] that unit is m, W
aBe [design point flow] that unit is kg/s;
The individual engine weight computing formula of population is (2)
W
engine＝(0.16*T
staticmax+921) (2)
In the formula (2), W
EngineBe the individual engine weight of population, unit is lb, T
StaticmaxBe population individual [takeoff thrust capability] that unit is lb;
Formula (3) has provided individual [target engine weight correction] the δ W of population
EngineDefinition, wherein, W
BaseBe [baseline engine weight]:
δW
engine＝W
engine-W
base (3)
Individual [the target engine resistance correction] of population is formula (4)
δC
D/C
D＝0.15657-0.37544*(D
fan/D
fanbase)+0.21886*(D
fan/D
fanbase)
2 (4)
In the formula (4), δ C
D/ C
DBe population individual [target engine resistance correction], D
Fan/ D
FanbasBe the engine [fan diameter] of population individuality and the ratio of [baseline engine blower diameter], δ C
D, C
D, D
FanbaseBe respectively population individual target engine resistance coefficient, resistance correction absolute magnitude, baseline engine blower diameter;
S4. " the individual engine fitness of population calculates "; Individual [the target engine resistance correction] of population that central processing unit (2) utilizes step S3 to obtain revised [aircraft polar]; Utilize [target engine weight correction] that [Gross Weight Takeoff] revised; And call secondary subclass [the flying quality emulation class] calculating [total fuel consume] in [the integrated performance optimization program of passenger plane/fanjet], and as the individual fitness of this population;
S5. " calculating of population ideal adaptation degree ": central processing unit (2) repeats S2-S4 step m time to the individuality in the population; Accomplish the individual fitness calculating of all populations in the initial population, be saved in individuality best in the initial population [GM] in the memory device (4) according to fitness;
S6. " generation progeny population ":
(S6-0) select: the fitness individual according to the parent population, utilize [parent is selected class] that all individualities are sorted, therefrom select two best parent populations individual, directly as 2 individuals in the progeny population;
(S6-1) intersect: according to given [crossover probability], utilize [parent intersection class] to intersect two parent population individualities at random to produce two new offspring individuals;
(S6-2) variation:, utilize [genetic mutation class] that two filial generation individualities of (S6-1) generating step are made a variation and produce two new offspring individuals according to given [variation probability];
Repeat (S6-1)～(S6-2) step (m-2)/2 time, generate remaining m-2 individuals in the progeny population;
S7. " replacement ": central processing unit (2) repeats the S2-S4 step to the individuality in the filial generation population and carries out fitness calculating for m time; Choose the best individuality [LM] in this generation population according to the size of fitness; And compare with best individuality [GM] in the previous generation population; If the fitness of [LM] is better than [GM], [population replacement class] composed the value of [LM] to [GM] and is saved in the memory device (4), otherwise [GM] remains unchanged;
S8. " test ": according to default [optimization algebraically] n, central processing unit (2) repeats S6-S7 step n time, and is saved in best individuality [GM] and corresponding [total fuel consumption] output thereof in the memory device (4), and upward shows at display device (5); Final [GM] refers to the set of [optimal engine pressure ratio], [optimal engine turbine inlet temperature], [optimal engine bypass ratio] these three parameters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110389440A CN102495924B (en) | 2011-11-30 | 2011-11-30 | Computer aided design device for integration performance optimization of airliner and fanjet and method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110389440A CN102495924B (en) | 2011-11-30 | 2011-11-30 | Computer aided design device for integration performance optimization of airliner and fanjet and method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102495924A true CN102495924A (en) | 2012-06-13 |
| CN102495924B CN102495924B (en) | 2012-10-10 |
Family
ID=46187749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110389440A Expired - Fee Related CN102495924B (en) | 2011-11-30 | 2011-11-30 | Computer aided design device for integration performance optimization of airliner and fanjet and method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102495924B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103267644A (en) * | 2012-06-28 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine performance simulation method |
| CN104748967A (en) * | 2013-12-27 | 2015-07-01 | 中航商用航空发动机有限责任公司 | Method for optimizing turbofan engine performance simulation platform under the condition of rain absorption |
| CN105069281A (en) * | 2015-07-17 | 2015-11-18 | 中国空间技术研究院 | Spacecraft orbit maneuver motor installing parameter optimizing method based on Runge-Kutta algorithm |
| CN105117563A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for calculating flow of air led into aircraft engine |
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| CN105868874A (en) * | 2015-01-19 | 2016-08-17 | 恺亿讯捷（北京）科技有限公司 | Method and device for selecting models of pump and fan based on energy efficiency evaluation |
| CN106021648A (en) * | 2016-05-06 | 2016-10-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | An optimizing method and an evaluation system for secondary energy of planes |
| CN106777517A (en) * | 2016-11-24 | 2017-05-31 | 东北大学 | Aero-engine high-pressure turbine disk Optimum Design System and method based on population |
| CN107784362A (en) * | 2016-08-31 | 2018-03-09 | 奥维通信股份有限公司 | A kind of distributed genetic algorithm of improved TD SCDMA systems |
| CN110492522A (en) * | 2018-05-14 | 2019-11-22 | 上海国孚电力设计工程股份有限公司 | Micro-capacitance sensor configuration method, device, equipment and its medium based on genetic algorithm |
| CN117521528A (en) * | 2024-01-03 | 2024-02-06 | 中国核动力研究设计院 | Turbine equipment simulation model evolution method, device, medium and computing equipment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080234994A1 (en) * | 2007-03-22 | 2008-09-25 | General Electric Company | Method and system for accommodating deterioration characteristics of machines |
| CN101418808A (en) * | 2008-12-11 | 2009-04-29 | 北京航空航天大学 | Multi-vane cycling air blowing and sucking flow control method for aviation turbofan engine compression system |
-
2011
- 2011-11-30 CN CN201110389440A patent/CN102495924B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080234994A1 (en) * | 2007-03-22 | 2008-09-25 | General Electric Company | Method and system for accommodating deterioration characteristics of machines |
| CN101418808A (en) * | 2008-12-11 | 2009-04-29 | 北京航空航天大学 | Multi-vane cycling air blowing and sucking flow control method for aviation turbofan engine compression system |
Non-Patent Citations (1)
| Title |
|---|
| 陈玉春等: "多用途战斗机_涡扇发动机一体化循环参数优化", 《航空学报》 * |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103267644A (en) * | 2012-06-28 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine performance simulation method |
| CN104748967A (en) * | 2013-12-27 | 2015-07-01 | 中航商用航空发动机有限责任公司 | Method for optimizing turbofan engine performance simulation platform under the condition of rain absorption |
| CN104748967B (en) * | 2013-12-27 | 2017-10-31 | 中国航发商用航空发动机有限责任公司 | Inhale the fanjet performance simulation pad optimization method under rain operating mode |
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| CN105868874A (en) * | 2015-01-19 | 2016-08-17 | 恺亿讯捷（北京）科技有限公司 | Method and device for selecting models of pump and fan based on energy efficiency evaluation |
| CN105069281A (en) * | 2015-07-17 | 2015-11-18 | 中国空间技术研究院 | Spacecraft orbit maneuver motor installing parameter optimizing method based on Runge-Kutta algorithm |
| CN105069281B (en) * | 2015-07-17 | 2018-01-05 | 中国空间技术研究院 | Spacecraft orbit maneuver motor installation parameter optimization method based on Runge Kutta algorithm |
| CN105117563A (en) * | 2015-09-15 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for calculating flow of air led into aircraft engine |
| CN105117563B (en) * | 2015-09-15 | 2019-12-31 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for calculating flow of air introduced into aircraft engine |
| CN106021648A (en) * | 2016-05-06 | 2016-10-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | An optimizing method and an evaluation system for secondary energy of planes |
| CN107784362A (en) * | 2016-08-31 | 2018-03-09 | 奥维通信股份有限公司 | A kind of distributed genetic algorithm of improved TD SCDMA systems |
| CN106777517A (en) * | 2016-11-24 | 2017-05-31 | 东北大学 | Aero-engine high-pressure turbine disk Optimum Design System and method based on population |
| CN106777517B (en) * | 2016-11-24 | 2019-10-18 | 东北大学 | Aero-engine high-pressure turbine disk Optimum Design System and method based on population |
| CN110492522A (en) * | 2018-05-14 | 2019-11-22 | 上海国孚电力设计工程股份有限公司 | Micro-capacitance sensor configuration method, device, equipment and its medium based on genetic algorithm |
| CN117521528A (en) * | 2024-01-03 | 2024-02-06 | 中国核动力研究设计院 | Turbine equipment simulation model evolution method, device, medium and computing equipment |
| CN117521528B (en) * | 2024-01-03 | 2024-03-15 | 中国核动力研究设计院 | Turbine equipment simulation model evolution method, device, medium and computing equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102495924B (en) | 2012-10-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102495924B (en) | Computer aided design device for integration performance optimization of airliner and fanjet and method thereof | |
| Mavris et al. | Application of deterministic and probabilistic system design methods and enhancements of conceptual design tools for era project | |
| Seitz | Advanced methods for propulsion system integration in aircraft conceptual design | |
| Berton et al. | Multi-objective optimization of a turbofan for an advanced, single-aisle transport | |
| McDaniel et al. | Hpcmp createtm-av kestrel new and emerging capabilities | |
| Kirner et al. | An assessment of distributed propulsion: Advanced propulsion system architectures for conventional aircraft configurations | |
| Goulos et al. | Aerodynamic design of separate-jet exhausts for future civil aero-engines—part ii: design space exploration, surrogate modeling, and optimization | |
| Goulos et al. | Rotorcraft engine cycle optimization at mission level | |
| Goulos et al. | Variable rotor speed and active blade twist for civil rotorcraft: Optimum scheduling, mission analysis, and environmental impact | |
| Perullo et al. | Effects of advanced engine technology on open rotor cycle selection and performance | |
| Aygun et al. | Comprehensive exergo-sustainability analysis for a next generation aero engine | |
| Tejero et al. | Impact of droop and scarf on the aerodynamic performance of compact aero-engine nacelles | |
| Schutte et al. | Updates and modeling enhancements to the assessment of NASA environmentally responsible aviation technologies and vehicle concepts | |
| Perullo et al. | Effects of advanced engine technology on open rotor cycle selection and performance | |
| Vouros et al. | Enabling the potential of hybrid electric propulsion through lean-burn-combustion turbofans | |
| Navaratne et al. | Generic framework for multi-disciplinary trajectory optimization of aircraft and power plant integrated systems | |
| Häßy et al. | Hybrid surrogate-based rubber engine model for aircraft multidisciplinary design optimization | |
| Yalcin | Thrust performance evaluation of a turbofan engine based on exergetic approach and thrust management in aircraft | |
| Chai et al. | Tradeoff study between cost and environmental impact of aircraft using simultaneous optimization of airframe and engine cycle | |
| Thacker et al. | Modeling of a Modern Aircraft Through Calibration Techniques | |
| Gallagher et al. | Validation and Calibration of Conceptual Design Tool SUAVE | |
| Carter et al. | The Development of an NPSS Engine Cycle Model to Match Engine Cycle Data, Using a Multi-Design-Point Method | |
| Voss et al. | Automated Optimisation of the MULDICON Inlet with Minimum Losses and Reduced Sight onto the Compressor Front Face | |
| Baltman et al. | A methodology for determining the interdependence of fuel burn and LTO noise of a commercial supersonic transport | |
| Hughes et al. | Common core engine design for multiple applications using a concurrent multi-design point approach |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121010 Termination date: 20131130 |