preliminary design review
Download
Skip this Video
Download Presentation
Preliminary Design Review

Loading in 2 Seconds...

play fullscreen
1 / 31

Preliminary Design Review - PowerPoint PPT Presentation


  • 126 Views
  • Uploaded on

Preliminary Design Review. Miguel Alanis Aaron Mayne Tim Block Jason Olmstead Becca Dale Adeel Soyfoo Joseph Fallon Sarah Weise. Review of Concept and Market . Multi-functional, Rugged, Non- petroleum fueled Airplane to serve:

loader
I am the owner, or an agent authorized to act on behalf of the owner, of the copyrighted work described.
capcha
Download Presentation

PowerPoint Slideshow about 'Preliminary Design Review' - walker


An Image/Link below is provided (as is) to download presentation

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.


- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -
Presentation Transcript
preliminary design review

Preliminary Design Review

Miguel Alanis Aaron Mayne

Tim Block Jason Olmstead

Becca Dale Adeel Soyfoo

Joseph Fallon Sarah Weise

AAE 451 Senior Design Team 1

review of concept and market
Review of Concept and Market
  • Multi-functional, Rugged, Non- petroleum fueled Airplane to serve:
    • Air charters, governments (surveying, mail), medical transport, or supplies delivery companies
  • Operates in rural, developing areas of the world such as Australia, South America, or even rural parts of Canada

AAE 451 Senior Design Team 1

design requirements
Design Requirements
  • Payload:
    • 2000 lbs, or
    • 10 passengers
  • Range: 1200 nm
    • One-way full load
  • Takeoff Field Length: 2000 ft
  • Service ceiling: 25000 ft
  • Max speed: 250 kn
  • Weight: ≤ 12,500 lbs
  • Acquisition Cost: < $2.5 million
  • Alternate Fuel Source

AAE 451 Senior Design Team 1

design concept
Design Concept
  • Main Features:
    • Tapered Wing
    • High Wing with Strut Support
    • T-Tail
    • Non Pressurized Cabin
    • Fixed Landing Gear
    • 66” Cargo Door
    • 4 ft Ground Clearance

AAE 451 Senior Design Team 1

design concept5
Design Concept

AAE 451 Senior Design Team 1

concept configurations
Concept Configurations

1

4

2

  • 10 seats
  • Executive
  • Combination seats/shipping container
  • 3 shipping containers (LD-3 Standard)

3

AAE 451 Senior Design Team 1

sizing of aircraft
Sizing of Aircraft
  • TOGW: 12,432 lbs
  • W/S: 31.3 lb/ft2
  • P/W: 0.0875
  • AR: 9
  • λ = 0.3
  • Acquisition cost: $3.24 million
  • Operating cost: $424.64/hr
  • Sizing done using FLOPS Flight Optimization System, Release 6.11(internal cost model not used)
  • Calibrated Using Cessna Grand Caravan
    • TOGW error ≈ 2%

AAE 451 Senior Design Team 1

constraint analysis
Constraint Analysis

AAE 451 Senior Design Team 1

compliance with design requirements
Compliance with Design Requirements

AAE 451 Senior Design Team 1

structure wing and tail
Structure - Wing and Tail

Main and Rear Spar

Rib Members

Stringers

Fuel tanks

AAE 451 Senior Design Team 1

structure fuselage
Structure - Fuselage

Length = 38 ft

  • Forward Section used for main payload/passengers
  • Aft Section for stability purposes
  • 2 main keel beams running longitudinally in forward section, used to support heavy payload
  • 12 transverse square ribs/frames along fuselage length
  • 16 longitudinal stringers/longerons

AAE 451 Senior Design Team 1

structure landing gear
Structure - Landing Gear
  • Non-retractable
  • Tricycle Layout
  • 2024-T6 Aluminum
  • Need to carefully choose specific tires (depends on type of runway landing)

50.76 deg

Tread = 10.54 feet

Wheelbase = 17 feet

AAE 451 Senior Design Team 1

structural material selection
Structural Material Selection

AAE 451 Senior Design Team 1

aerodynamics
Aerodynamics
  • Airfoil NACA 4412 has the Highest cLmax
  • Slotted Flap on Entire Wing
  • CLcruse=0.4
  • [email protected]/Dmax =0.6
  • CLmax=2.4
  • Wing Area=400 ft2
  • Taper Ratio=0.3

AAE 451 Senior Design Team 1

drag polar
Drag Polar

AAE 451 Senior Design Team 1

weight balance
C.G. Location:18.5ft

Weight Breakdown:

Payload: 2000 lbs

Crew: 410 lbs

Empty Weight: 6,113 lbs

Fuel Weigh: 3,903 lbs

Weight & Balance

Green loading plane, Blue unloading plane

AAE 451 Senior Design Team 1

stability
Stability
  • AC of wing
  • CG location
  • Neutral Point
  • AC of Vertical Tail
  • AC of Horizontal Tail

AAE 451 Senior Design Team 1

stability18
Stability
  • Static Margin (SM): 16.1%
  • Neutral Point: 19.6 ft

AAE 451 Senior Design Team 1

performance
Performance
  • Optimal Performance Values
  • V-n Diagram

gustnormal

AAE 451 Senior Design Team 1

performance20
Performance
  • Operating Envelope

Constant energy heights

Stall limit

Ps=0

q limit

Cruise Height

AAE 451 Senior Design Team 1

engine
Engine
  • Pratt & Whitney Canada PT6A-67D
  • Delivers up to 1271 hp (1250 hp required)
  • High power to weight ratio
  • High reliability
  • Low fuel consumption (sfc at full power: 0.546 lb/hp/h)

AAE 451 Senior Design Team 1

propeller thrust produced
Propeller & Thrust produced
  • 4-bladed aluminum propeller
  • Integrated design lift coefficient cL = 0.500
  • Activity factor 140
  • Diameter 110 in
  • Rotational speed 1700 rpm
  • Blade Tip Speed Ma = 0.78

AAE 451 Senior Design Team 1

slide23
Cost
  • Acquisition cost
  • DOC

AAE 451 Senior Design Team 1

conclusion
Conclusion
  • Will concept be successful?
    • Feasible design
    • New concept will give market advantage
    • Derived versions could offer more cabin space but shorter range
    • Competition from remodeled petrol fueled aircraft
  • Significant “open” issues
    • Stall characteristics (T-tail)
    • Finalize wing design (flap size)
    • Improve Takeoff and Landing Performance
    • Develop Bio-fuel kit for PT6A turbine

AAE 451 Senior Design Team 1

questions
Questions?

AAE 451 Senior Design Team 1

acquisition cost breakdown
Acquisition Cost Breakdown:
  • Power series function
  • Depends on wing span, AR, GTOW, thrust, cruise speed, and range

ln(cost)= {constants}*{vector of ln(parameters)}

AAE 451 Senior Design Team 1

rdt e and flyaway costs
RDT&E and Flyaway Costs:
  • DAPCA model outlined in Raymer’s text
  • Did not give an accurate acquisition cost
  • Did give accurate percentages for the RDT&E and Flyaway cost break down

RDT&E = 0.64*(Acquisition Cost)

Flyaway = 0.36*(Acquisition Cost)

AAE 451 Senior Design Team 1

slide28
DOC:
  • DAPCA model outlined in Raymer’s text
  • Did not give an accurate DOC, but calculated value was off by a consistent percentage
  • Calculated our DOC at current fuel prices
  • Adjust DOC according to:

real DOC = 0.64*(calculated DOC) 

  • Added in addition costs due to increased fuel price

AAE 451 Senior Design Team 1

cost assumptions
Cost Assumptions:
  • RDT&E and Flyaway Costs:
    • 200 aircraft to break even
    • 2 flight test aircraft
    • Avionics are 7% of the flyaway cost
  • DOC:
    • 1000 FH/year
    • 1 MMH/FH
    • Properties of our fuel are the same as kerosene
    • Current fuel: $2.40 1/gal, FT: $7.40 1/gal

AAE 451 Senior Design Team 1

constraint analysis30
Constraint Analysis

AAE 451 Senior Design Team 1

sizing
Sizing
  • Method
    • FLOPS
      • Input parameters
        • T/W, converted from P/W with prop numbers
        • Geometric Characteristics
        • Mission and Performance Constraints
        • Engine Definition
        • Wing Definition
      • Calibration
        • Cessna Grand Caravan
          • TOGW error aprrox. 2%

AAE 451 Senior Design Team 1

ad