Report Helicopter 4 seat

HO CHI MINH CITY UNIVERSITY OF TECHNOLOGY FACULTY OF TRANSPORTATION ENGINEERING DEPARTMENT OF AEROSPACE ENGINEERING REPORT DESIGN CALCULATIONS HELICOPTERS SEATS ADVISOR: PHD VU NGOC ANH STUDENTS: NGUYEN THANH PHONG G1002398 DINH MINH TUNG G1003867 PHAM TIEN HOANG G1001131 HOANG TIEN DAT G1000610 Ho Chi Minh City, June 19th, 2014 CONTENTS PART 1: QUALITY FUNTION DEPLOYMENT I FOUR PHASES OF QFD & APPLICATION: Four phases of QFD: 2 Application 2.1 Level 2.2 Level & Level 3: II EVALUATION Pugh’s Concept Selection 1.1 Hub 1.2 Landing Gear 11 1.3 Tail rotor 12 Evaluation the concepts using AHP method 15 2.1 Hub’s Selection 15 2.2 Landing Gear’s Selection 17 2.3 Tail Rotor’s Selection 19 PART 2: AERODYNAMIC 22 I MOMENTUM METHOD 22 Basic of the theory 22 Induced Velocities 22 II BLADE ELEMENT METHOD 25 PART 3: PERFORMANCE ANALYSIS 28 PART 4: REFERENCE 42 I EBOOK REFERENCE 42 II CODE MATLAB 42 Helicopter Charateristic 42 Hover Perfomance 43 NACA 0012 44 Vertical Flight 45 Report Aircraft Design PART 01 QUALITY FUNTION DEPLOYMENT HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design PART 1: QUALITY FUNTION DEPLOYMENT I FOUR PHASES OF QFD & APPLICATION: FOUR PHASES OF QFD: Phase 1, Product Planning: is also called The House of Quality Many organizations only get through this phase of a QFD process Phase includes customer requirements, warranty data, competitive opportunities, product measurements, competing product measures, and the technical ability of the organization to meet each customer requirement QFD matrix is used to translate customer requirements into design requirements Design requirements are ways in which the design team is able to satisfy the customer requirements Gathering good information from the customer in Phase is critical to the success of the next QFD process Phase Part deployement: here you can see, there is a matrix between Design Req & Part Quality Characteristics This matrix answers the question, what parts of the product deliver the quality characteristics our customers want? Critical quality characteristics are showed into parts and their characteristics Part 3, Manufacturing Planning: This matrix answers the question, where in our manufacturing process can we affect the critical parts characteristics? Critical parts HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design characteristics are showed into manufacturing steps and parameters So this is where the "voice of the customer," translated into critical process steps and parameters, reaches the factory floor Phase IV, Production Planning: This matrix answers the question, what should the production plans, procedures, and inputs be for the process parameters to produce the key parts to satisfy the customer? So now the "voice of the customer" has reached the machine operators, and it determines the settings on the production machinery HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design 2 APPLICATION 2.1 Level  Affinity Diagram HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design In “Customer Requirement”, we can identify “What does the Customer Want & what does the Customer Needs.” , all of the results is showed by the figure below: - What happen if our helicopter does not Safe, Reliable, Fast, Affordable etc….? This is really the requirement of our customer The more you hear voice of customer, the more you can gather much more informations - My design team showed you 11 basic requirement of customer - In “Engineering Characteristics”, we can identify “What can I control that allows me to meet my customer’s needs?”, “How can I satisfy the Customer?” ,all of the results is showed by the figure below: HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design - For each Customer Requirement, my design team decided to identify 13 components liking a initial for the design - You also know “What is the interaction, the relation” between each of components, identified by correlation matrix - The relationship matrix is where my team determines the relationship between customer needs and the engineering characteristics HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design - By using Excel, you will obtain the result of Relative Weight used for Weighted Decision (unit: %) 2.2 Level & Level 3: - Like what we have done in Level 1, the Level will continue the QFD process, but the ECs (How’s) in Level replaced by new place of What’s position in Level - It’s the same for Level - The most important after level is to define “What is the prefer direction for the selection of design” by calculating Relative Weight & apply it for the Weighted Decision showed after the Pugh Matrix - You will obtain my detail information about Level & Level in my Excel file named “QFD process H2.xlsx” HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design II EVALUATION PUGH’S CONCEPT SELECTION 1.1 Hub - There are types of helicopter rotor hubs  Teetering Hub: - A teetering rotor has two blades that are hinged at the rotational axis - When one blade flaps up, the other flaps down - The teetering design has the advantage of being mechanically simple with a low parts count & it is easy to maintain One disadvantage of the design is that it can have a relatively high parasitic drag in forward flight, in part because of the stabilizer bar  Articulated Hub: - In a fully articulated rotor system, each rotor blade is attached to the rotor hub through a series of hinges, which allow the blade to move independently of the others HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH Report Aircraft Design In operation, the angle of attack can varies to 360 degree, so they estimate the lift - drag charateristics for all over 360 degrees angle of attack Lift coefficient over 360 degrees angle of attack Drag coefficient over 360 degrees angle of attack Compute running thrust loading: HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 31 Report Aircraft Design Intergrate thrust loading from cut-out position to the tip of the blade, we have thrust coeffiction without tip-loss: + Tip loss factor : + Actual thrust coefficient: 10 Compute running profile torque loading: 11 From that we can get the induced torque coefficient: 12 Compute : due to the rotation of the wake using Figure 1.29: HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 32 Report Aircraft Design 13 Diskloading: 14 Calculate: 15 Obtain empirical correction factor: HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 33 Report Aircraft Design 16 Calculate total torque coefficient: 17 Calculate the rotor thrust and power: HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 34 Report Aircraft Design Using MATLAB to follow the previous procedure we have the Helicopter Performance in Hover HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 35 Report Aircraft Design With several different Main Rotor Radius, we can see the ability of rotor in hover performance With solidity = 0.085, Twist angle = -10 degre, collective pitch vary from 10 – 30 degrees we have: R=10 ft The maximum thust that the rotor can create is about 4500lb HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 36 Report Aircraft Design R=15 ft The maximum thust that the rotor can create is about 10000lb R=20 ft The maximum thust that the rotor can create is about 18000lb Althoght we have already figure out the main rotor radius of our helicopter about 22ft at very low disk loading (about 2.5 lb/ft2) The helicopter gross weight GW =4000lb , It seem quite in excesss and limit the collective pitch of the blade So we HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 37 Report Aircraft Design modify it to be about 12.5 ft where the maximum thrust can create is about 7000lb seem more reliable So, the Horsepower the main rotor required to lift the Helicopter 4000lb at sea level is about 450hp HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 38 Report Aircraft Design Vertical performance Induce velocity: To find the induce velocity of the rotor we calculate the local velocity at each element and intergrate to get the averate induce velocity Since we have the differenes power in hover and vertical flight: Where hover induce velocity is: Induce velocity in climb: So we get the vertical performance of the helicopter HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 39 Report Aircraft Design So if we wish the Helicopter have the maximum vertical rate of climb about 3000 lf/min, then the power increment required about 270hp HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 40 Report Aircraft Design PART REFERENCE HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 41 Report Aircraft Design PART 4: REFERENCE I EBOOK REFERENCE [1] Prouty Raymon - Helicopter Performance, Stability and Control - 2002 [2] Leishman J.G, Principles of Helicopter Aerodynamics, (Cambridge Aerospace Series), 2006 [3] Bill, R.C, Advanced Rotorcraft Transmission Program, NASA-TM-103276, Washington D.C, 1990 [4] Hiller Aircraft Company, Preliminary Design of a Light Observation Helicopter [5] www.wikipedia.com-Key word: Teetering, Bearingless, Articulated Hub, Fenestron, Notar [6] George F.Dieter, Engineering Design, 4th edition II CODE MATLAB HELICOPTER CHARATERISTIC %%% Helicopter Charateritics temperature = 15; % Celcius height = 000 ; % ft %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%% Main Rotor Charateristic %%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% main.b=4 ; % number of blade main.R= 20 ; % Rotor radius in ft main.c=1.2 ; % Chord in ft main.cutout = 15/100 ; main.twist=-10 ; % from root of blade in degree main.tipspeed = 650 ; % ft/sec main.collectivepitch = 17.5 ; % degree %%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%% Tail Rotor Charateristic %%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% tail.b=3 ; tail.R= 6.5 ; tail.c=1 ; % tail.cutout = 15/100 ; tail.twist=-5 ; tail.tipspeed = 650 ; tail.collectivepitch = 12.5 ; %%%%%%%%%%%%%%%%%%%%%%%%%%%%% % number of blade % Rotor radius in ft Chord in ft % % % from root of blade in degree ft/sec degree lT=37; % Tail rotor moment armn in ft GW=20000; % Gross Weight rho = 68.18 *exp(-((height- -7.646e+04)/7.436e+04)^2)*10^-4; % slug/ft3 ref: http://www.engineeringtoolbox.com/standard-atmosphere-d_604.html collectivepitch = 10:5:30 for i=1:length(collectivepitch) HELICOPTER SEATS – GT10HK ADVISOR: PHD VU NGOC ANH 42 Report Aircraft Design [mainCtsigma(i),mainCQsigma(i),mainthrust(i),mainhp(i)]=HoverPerfomance(main.b,m ain.R,main.c,main.cutout,main.collectivepitch,main.twist,main.tipspeed,temperatu re,rho); [tailCt(i),tailCQ(i),tail.thrust(i),tailhp(i)]=HoverPerfomance(tail.b,tail.R,tai l.c,tail.cutout,tail.collectivepitch,tail.twist,tail.tipspeed,temperature,rho); end %VC=0:100:4000; %for i = 1: length(VC) %[deltahp(i)]=VerticalFlight(VC(i),GW,main.thrust,main.b,main.R,main.c,main.cuto ut,main.tipspeed,main.collectivepitch,main.twist,tail.thrust,lT,rho,temperature) %end %plot(VC,deltahp) HOVER PERFOMANCE %%%%%%%% Hovering Perfomance %%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% clear all; %%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%% Rotor Charateristic %%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%% b=4 ; % number of blade R= 30 ; % Rotor radius in ft c=2.001 ; % Chord in ft cutout = 15/100 ; twist=-8.5 ; % degree tipspeed = 650 ; % ft/sec collectivepitch = 16 ; % degree %%%%%%%%%%%%%%%%%%%%%%%%%%%%% temperature = 15; % Celcius height = ;% ft rho = 68.18 *exp(-((height- -7.646e+04)/7.436e+04)^2)*10^-4; % slug/ft3 ref: http://www.engineeringtoolbox.com/standard-atmosphere-d_604.html Vsound = (331.3+0.606*temperature)*3.28084; % ft/sec % Divide blade into (n-1) section n=15; for i=1:n rR(i)= cutout + (1-cutout)/(n-1)*(i-1); cR(i)=c/R; localMach(i)=rR(i)*tipspeed/Vsound; pitch(i) = collectivepitch + twist*((rR(i)-cutout)/(1-cutout)); a(i) = 1/sqrt(1-localMach(i)^2)-.01*localMach(i); vOmegar(i)=a(i)/pi*180*b*cR(i)/(16*pi*rR(i))*(1+sqrt(1+(32*pi*(pitch(i)*pi/180)*rR(i))/(a(i)/pi*180*b*cR(i)))); alpha(i)=pitch(i)-atan(vOmegar(i))*180/pi; [cl(i),cd(i)]=NACA0012(localMach(i),alpha(i)); dCtdrR(i)=b*rR(i)^2*cR(i)*cl(i)/2/pi; dCQ0drR(i)=(b*rR(i)^3*cR(i)*cd(i))/2/pi; dCQidrR(i)=b*rR(i)^3*cR(i)*cl(i)*vOmegar(i)/2/pi; end Ctnotiploss=trapz(rR,dCtdrR); CQ0=trapz(rR,dCQ0drR); CQi=trapz(rR,dCQidrR); %calculate tiploss if Ctnotiploss