Aerospace Design Project Advanced Pilot Training … Design Project Advanced Pilot Training Aircraft...
Transcript of Aerospace Design Project Advanced Pilot Training … Design Project Advanced Pilot Training Aircraft...
Aerospace Design Project
Advanced Pilot Training Aircraft
Grigorios Dimitriadis
Ludovic Noels
Adrien Crovato
Thomas Lambert
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1. Context
The student groups shall design an aircraft following the requirements of the AIAA 2017-2018
Graduate Team Aircraft Design Competition: http://www.aiaa.org/DesignCompetitions/ . In
particular you will compete in the Request for Proposal for an Advanced Pilot Training Aircraft
(http://www.aiaa.org/2018GradTeamAircraft-APT/)
2. Organization
Each group, of up to maximum 8 students, will elect a coordinator who will be responsible
for:
Ensuring the transfer of information between the group members;
Compiling the group reports from the individual contribution of each group member ;
Submitting the letters of Intent and the Report to AIAA.
Before the start of the project, the work will be organized into tasks for the two Work Packages
(WP1 Conceptual design, WP2 Preliminary Design). For each task one student will be elected
as responsible for its completion.
3. WP1: Conceptual design
The following items will be studied:
1/ Definition of the design missions and requirements:
Following the Request for Proposals of the AIAA 2018 Graduate Team Aircraft Design
Competition (http://www.aiaa.org/GraduateTeamAircraft-APT-RFP/).
Ensure compatibility with MIL-STD-1797 and Mil-F-8785 requirements for static and dynamic
stability and handling characteristics
2/ Wing:
Geometry (taper ratio λ, twist, sweep angle, Croot, Ctip, span…)
Airfoil
Incidence angle
Position on the fuselage/Wing blended description
This task is also part of the Aerodynamics class, see Annex 1
3/ Empennage / canard (foreplane) / fin (common for the two aircrafts):
Geometry (taper ratio λ, twist, sweep angle, Croot, Ctip, span…)
Airfoil
Incidence angle
Position on the fuselage
4/ Fuselage & Landing gear design:
Fuselage geometry
Landing gear position
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Landing gear Design
5/ Propulsion:
Engine selection (see Attachment 4 of Annex 4)
Engines number
Weight of fuel + range
Use of external tanks or not
Performance (payload range diagram)
6/ Structure:
Placard diagram & maneuver/gust envelops (see Attachment 2 of Annex 4)
Cockpit (see Attachment 3 of Annex 4)
Weight and center of gravity position of each component + GTOW, We, mission Wf,
W/S, T/W, Wf /Wto) (see Attachment 5 of Annex 4)
Initial layout of internal structures
This task is also part of the Aeronautical Structures class, see Annex 2
7/ Static stability
Evolution of CG, neutral point, stability
In all the important flight configurations
Calculation of the drag polar
Calculation of the derivatives of CL, CD, Cm, and Cn
8/ Alternative concepts & Trade off-study Develop and present the alternative concepts
Trade-off study with 10 % variation of the main parameters
4. WP2: Preliminary design
For this study, the following points will be addressed:
1/ Drag study
Using the CAD geometry from part 2/, extraction of wetted areas, volume, surfaces etc
Detailed drag evaluation (ask for references)
2/ CAD
Create a solid CAD model (with mass, inertia and system integration)
Evaluate mass, inertia and position of center of gravity
Create a realistic CAD view
Animations of systems integration, crew stations, and landing gear are required
Extract the CAD model of the wing for mokeup, see Annex 1 for details
3/ Aerodynamics
Numerical models, see Annex 1 for details
Re-assess equilibrium and stability (considering different angles of attack, variation of
the CG and dynamic center)
Evaluate the drag and compare to 1/
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This task is also part of the Aerodynamics class, see Annex 1
4/ Structure design
Estimation of aerodynamics forces during manoeuvers/gusts (acceleration etc
following MIL-STD-1797 and Mil-F-8785 requirements) , see Annex 2
Estimation of the structural forces, see Annex 2
First design of the structure using analytical formula, see Annex 2
This task is also part of the Aeronautical Structures class, see Annex 2
5/ Structure study
CAD model with FE simulation, see Annex 2
Discussion of the application of aerodynamic loads, see Annex 2
This task is also part of the Aeronautical Structures class, see Annex 2
6/ Performance
Handling characteristics (envelop altitude/rate of climb in terms of Mach number,
envelop turn rate/turn radius in terms of Mach number)
Reassess Payload range diagram
Evaluate take-off and landing distances (standard day and icy runway balanced field
length at sea level). For single-engine designs runway length requirements may be
approximated by adding take-off and landing distance together. For multi-engine
designs actual balanced field length should be considered.
Dynamic stability and handling characteristics
7/ Costs evaluation
Estimate the non-recurring development and production costs of the airplane
(engineering, production tooling, facilities and labor)
Estimate the recurring production costs (average incremental cost for an additional
aircraft)
Estimate the fly away cost for aircraft buys ranging from 100 to 700 in 100-aircraft
increments
Estimate the unit price so that a profit of at least 10% is generated (at production rates
ranging from 4 to 10 airplanes per month)
Estimate the direct operating cost per airplane flight hour: fuel, oil, tires, brakes, and
other consumables & maintenance cost per flight hour (annual inspection)
5. Reports and presentation
Reports
◦ In English
◦ Demonstrate a thorough understanding of the Request for Proposal (RFP)
requirements
◦ Describe the proposed technical approaches to comply with each of the requirements
specified in the RFP, including phasing of tasks. Legibility, clarity, and
completeness of the technical approach are primary factors in evaluation of the
proposals.
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◦ Particular emphasis should be directed at identification of critical, technical problem
areas. Descriptions, sketches, drawings, systems analysis, method of attack, and
discussions of new techniques should be presented in sufficient detail to permit
engineering evaluation of the proposal. Exceptions to proposed technical
requirements should be identified and explained.
◦ Include tradeoff studies performed to arrive at the final design.
◦ Provide a description of automated design tools used to develop the design.
◦ Each proposal should be no more than 100 double-spaced pages (including graphs,
drawings, photographs, and appendices) if it were to be printed on 8.5” x 11.0”
paper, and the font should be no smaller than 10 pt. Times New Roman.
◦ Intermediate reports shall be of up to 50 pages.
◦ Fill the (relevant) parameters table as appendix (for all the reports), see Annex 3.
Presentations
◦ In English
◦ Describe and justify your design choices
◦ Describe your methodology
◦ Insist on the interactions between the parts
◦ Around 20 minutes
Important dates
◦ Document (1-2 pages) with WPs, Gantt chart, task leaders, and deliverables: 6
November 2017 ◦ Register to AIAA (with receipt): before 2 February 2018, process to be defined
◦ Letter of intent: to be submitted to AIAA
(http://www.aiaa.org/DesignCompetitions/ ) by 10 February 2018 11:59pm
(MIDNIGHT) Eastern Time !!!Require AIAA account!!!!
◦ First report (Conceptual Design) for feedback/grading: 14 February 2018
◦ First presentation for feedback: 19 February 2018 at 2pm
◦ Second report (Corrected Conceptual Design and Preliminary Design) for
feedback/grading: 23 April 2018
◦ Final report to be submitted to AIAA Headquarters
(http://www.aiaa.org/DesignCompetitions/ ): 10 May 2018 11:59pm (MIDNIGHT)
Eastern Time !!!Requires AIAA account!!!
◦ Final Presentations for grading: 14 May 2018 at 2pm (to be confirmed)
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Appendix 1: Aerodynamic part guidelines
1. Tasks
1/ Conceptual Design
Review similar aircraft wing design and understand the effect of the main wing design
parameters (AR, taper, twist, …) on aircraft efficiency
Design the wing and estimate aerodynamic quantities (L, D, M, L/D, AoA, …)
o Optimize for most probable (cruise) flight condition
o Check that other flight conditions can be achieved
2/ Preliminary Design
Model the wing in TRANAIR (viscous)
o Make a quick (volume and surface) mesh convergence analysis
o Takeoff
o Cruise
o High-speed
o [BONUS] Maneuver
Compute the drag analytically and compare to TRANAIR results
o Low-speed
o Cruise
[BONUS] Model the whole aircraft in TRANAIR (inviscid/viscous) in cruise
2. Resources
[Lectures] Aircraft Design (aerodynamics & conceptual design)
[Presentation] TRANAIR introduction & example
[Document] TRANAIR install notes
[Lectures] Aerodynamics (available Q2)
3. Deliverables
1/ Conceptual Design
Written chapter Wing design (or equivalent) included in conceptual design report
Weekly short oral report on project progress
2/ Preliminary Design
Written chapter Wing design (or equivalent) included in final design report
Written chapter Aerodynamics (or equivalent) included in final design report
Short written report on mesh convergence analysis to be delivered by end of March
Weekly short oral report on project progress
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4. Organization
1/ Calendar Months Aerospace Design Project Aerodynamics
September Aircraft design lectures
Conceptual design
TRANAIR introduction & example
October
November
December
January
February Conceptual Design Theory lectures 2D/3D inviscid flows
2D panel code implementation
2D TRANAIR (viscous/inviscid) 3D Prandtl lifting line implementation
March Preliminary design
3D TRANAIR (viscous) for takeoff,
cruise and high-speed
Analytic drag computations (low-
speed and cruise)
April Design & manufacturing of wing
mockup
Wind tunnel test at takeoff condition May
2/ Short description of tasks (Aerodynamics course)
Implement a linear source-vortex (Hess&Smith) 2D panel code on MATLAB and
compute aerodynamic quantities for given airfoils
Compute aerodynamic quantities for given airfoils with TRANAIR in inviscid and
viscous modes and compare to the MATLAB panel method
Implement Prandtl lifting line on MATLAB and compute aerodynamic quantities of
the wing designed in the ADP at takeoff condition
Design, manufacture and test a wing mockup in the wind tunnel at takeoff condition,
and compare to Prandtl lifting line and to TRANAIR results (obtained in ADP)
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Appendix 2: Structure part guidelines
1. Tasks
1/ Conceptual Design
Placard diagram & maneuver/gust envelops (see Attachment 2 of Annex 4)
Weight and center of gravity position of each component + GTOW, We, mission Wf,
W/S, T/W, Wf /Wto) (see Attachment 5 of Annex 4)
Initial layout of internal structures
2/ Preliminary Design
Estimation of aerodynamics forces during manoeuvers/gusts
o Acceleration etc. following MIL-STD-1797 and Mil-F-8785 requirements
o Wing loading
o Empennage/canard loading
Evaluation of the structural loads
o Of fuselage directly aft the wing
o At wing root
o In different flight configurations
First design of the structure using analytical formula
o Using the most critical structural loads
Finite element verification
o Using shell models based on a CAD representation
o Discussion of the applied aerodynamics loads and boundary conditions
o Verification of the structure integrity
2. Resources
[Lectures] Aircraft Design (Structure & conceptual design)
[Lectures] Aeronautical structures (available Q2)
3. Deliverables
1/ Conceptual Design
Written chapter Structure/weight (or equivalent) included in conceptual design report
Weekly short oral report on project progress
2/ Preliminary Design
Written chapter Structure (or equivalent) included in final design report
Weekly short oral report on project progress
3/ Aeronautical structures
Extended version of the written chapter Structure (or equivalent), with all the details
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4. Organization
1/ Calendar
Months Aerospace Design Project Aeronautical structures
September Aircraft design lectures Conceptual design
October
November
December
January
February Conceptual Design Theory lectures Theory lectures Design example
March Preliminary design: analytical design CAD model & FEM Final report
April Theory lectures Final report May
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Appendix 3: List of parameters
Parameters USI US/Imp
Fuselage
Height: HEIGHTfus
Width:
WIDTHfus
Length: LENGTHfus
Wing
span: b
Aspect Ratio: AR
Gross Surface: S
Exposed: S_exp
Taper Ratio: Lambda
Cord at root: Croot
Cord at tip: Ctip
Sweep angle at chord quarter:
Lambda_quart
Geometric twist: Eps_gtip
Mean Aerodynamic Chord:
MAC
X coordinate of Aerodynamic
center: Xac
Y coordinate of Aerodynamic
center: Yac
Compressibility parameter:
BETA
Cruise Mach: M
Average airfoil thickness:
t_bar
Fuel volume: V_fuel
Wetted wing surface:
S_wetted_w
Wing lift coefficient in cruise:
C_L_w
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Wing lift coefficient
derivative: a
Angle of attack at root
(cruise): Alpha_root
Zero-lift angle of attack at
root: Alpha_L0
Zero-lift angle of attack of the
profile:
Alpha_l0
Aerodynamics twist
coefficient: Alpha_01
Aerodynamics twist:
Eps_a_tip
Maximum lift coefficient of
the wing (flaps in): CLmax
Stall velocity (flaps in): Vs
Stall velocity (flaps out): Vs0
Reynolds number: Re
Airfoil lift coefficient
derivative: c_l_a
Airfoil design lift coefficient:
c_l_i
Maximum camber: cmax
Lift coefficient (cruise): LW
Stability (for each flight configuration)
Plane lift coefficient (cruise):
CL
Empennage/canard plane lift
coefficient (cruise): CLT
Surface of the
empennage/canard: ST
Fuselage angle of attack:
Alpha_f
Zero-lift fuselage angle of
attack: Alpha_f0
Pitching moment coefficient:
Cm
Wing pitching moment
coefficient: Cm0
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X-coordinate of the gravity
center: Xcg
Empennage/canard pitching
moment coefficient: CmT
Empennage/canard lift: LT
Non-dimensional center of
gravity position: h
Non-dimensional AC
position: h0
Non-dimensional stability
limit of the center of gravity
position: hn
Incidence angle of the wing
on the fuselage: iw
Plane lift coefficient
derivative: CL_alpha_plane
Empennage/canard angle of
attack: Alpha_T
Downwash: Eps
Downwash gradient:
d_eps_d_alpha
Vertical distance between
wing and empennage/canard:
m
Stability margin: Kn
Incidence angle of the
empennage/canard on the
fuselage: iT
Horizontal empennage/canard
Span: bT
Aspect Ratio: AR_T
Taper ratio: Lamba_T
Sweep angle at chord quarter:
Lambda_quart_T
Chord at root: CTroot
Chord at tip: CTtip
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Distance between the plane
gravity center and the
empennage AC: lT
Vertical empennage
Height: bF
Aspect Ratio: ARF
Surface: SF
Taper Ratio: Lambda_F
Sweep angle at chord quarter:
Lambda_quart_F
Chord at root: CFroot
Chord at tip: CFtip
Distance between the plane
gravity center and the
empennage AC: lF
Lift coefficient (critical case):
CLF
Lift coefficient (critical case):
LF
Yaw moment coefficient
(critical case): CN
Yaw moment coefficient
derivative: CNbeta
Rudder height: hr
Rudder surface: Sr
Drag
Drag (cruise): D
Drag coefficient: CD
Zero-lift drag coefficient:
CD0
e-factor: E
Compressibility drag
coefficient: CompCD
Security velocity: V2
Drag coefficient at security
velocity: CDV2s
Engine
SLS thrust: Tt0
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Take-off thrust: Tto
Specific fuel consumption:
CT
Cruise thrust: T
Weights
Wing: Ww
Empennage/canard weight:
WT
Vertical empennage weight
(without rudder): WF1
Vertical empennage weight
(with rudder): WF2
n_ultime
Cabin pressure: DeltaPmax
n_limite
Fuselage weight: Wfus
Gear weight: Wgear
Control weight: Wsc
Propulsion weight: Wprop
Instrument weight: Winst
Electrical devices weight:
Welec
Electronical devices weight:
Wetronic
Payload: Wpayload
Fuel weight for take-off: Wto
Fuel weight for landing:
Wland
Reserve fuel weight: Wres
Fuel weight for climb:
Wclimb
Fuel weight for cruise: Wf
Manufacturer empty weight:
MEW
Zero-fuel-weight: ZFW
Take-off weight: Wto
Wing loading W/S
Thrust to weight T/W
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Fuel ratio Wf /Wto
Range at maximum payload:
d_etoile
Landing gear
Maximum pitch angle: Theta
Maximum roll angle: Phi
Dihedral angle: Gamma
Hauteur de l'aile: Hg
Distance between landing
gears: t
Angle of attack at lift-off:
AlphaLOF
Lift-off speed: V_LOF
Touch down angle: ThetaTD
Distance between plane
gravity center and aft landing
gear: lm
Plane gravity center height:
Zcg
Positions of centres of gravity:
Xwing
XempH
XempV
Xfus
Xsyst_elec
Xelec_instr
Xpayload
Xfuel
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Appendix 4: AIAA 2018 Graduate Team Aircraft Design Competition
Downloadable on http://www.aiaa.org/2018GradTeamAircraft-APT/