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Results for «fuselage»:


Total: 19 results - 0.042 seconds

CartoonAerodynamics 100%

The following section of fuselage demonstrates laminar flow:

https://www.pdf-archive.com/2015/03/05/cartoonaerodynamics/

05/03/2015 www.pdf-archive.com

1-18 Bleriot XI-2 cutaway instructions 98%

These are the front and the rear fuselage frame sections.

https://www.pdf-archive.com/2016/06/19/1-18-bleriot-xi-2-cutaway-instructions/

19/06/2016 www.pdf-archive.com

1-15 Bleriot XI-2 cutaway instructions 98%

These are the front and the rear fuselage frame sections.

https://www.pdf-archive.com/2016/06/19/1-15-bleriot-xi-2-cutaway-instructions/

19/06/2016 www.pdf-archive.com

QC11K-NC Hydraulic Guillotine Shearing Machine-E21S system 80%

The fuselage eliminates internal stress by annealing and vibration, ensuring high strength and precision.

https://www.pdf-archive.com/2017/10/16/qc11k-nc-hydraulic-guillotine-shearing-machine-e21s-system/

16/10/2017 www.pdf-archive.com

Babur LACM 76%

Babur missile has a tubular shaped fuselage with a pair of folded wings attached to the middle section and a tail assembly and propulsion system at the rear.

https://www.pdf-archive.com/2012/06/19/babur-lacm/

19/06/2012 www.pdf-archive.com

page17 72%

The aircraft was to have two rotors positioned longitudinally along the fuselage.

https://www.pdf-archive.com/2013/03/23/page17/

23/03/2013 www.pdf-archive.com

AA 356 72%

1   Alpha Aeronautics   XJ-2 Personal Jet Aircraft    Final Design Report   EMAE 356     Arik Legman, Alexander Borgestedt, Allyson Beach,  Atniel “Otto” Katan, Chanisara Netsuwan, Felipe Gomez  del Campo, Jonathan Goldson, Masihuddin Ahmed, Tyler  Bauer        2             XJ-2          3                             Abstract  Proposed  herein  is  the  preliminary  design  of  a  personal  jet  aircraft  for  personal  ownership.  The  aircraft  costs  under  $200,000,  is  designed  to  carry  two  passengers,  cruise  for  over  1000  nm  and  operate  from 2,000’ runways.  Specifications for the design of the new aircraft  and  engine  are  listed,  and  manufacturing  methods  and  materials  selections  are  presented.  The  economic  feasibility  of  the  aircraft  are  presented,  and  800  whole  aircraft  sold  per  year  are  required to meet the cost goal.  Cost reduction measures for a kit aircraft are also explored.           4 Table of Contents  Alpha Aeronautics  Personal Jet Aircraft  Final Design Report  EMAE 356  1.0 Introduction  1.1 Mission Overview  2.0 System Overview  2.1 Functional Block Diagram  2.2 Critical Interfaces and Interdependencies  2.3 Risk Identification and Mitigation  3.0 Project Management Plan  Organizational Structure/ Assignments/ Leads  Work Breakdown Structure  Schedule (Full Semester)  4.0 Systems Modeling  Trade Studies  Major Driving Factors  Significant Design Decisions  Technology Readiness Level  5.0 Vehicle Design  CAD model  Weight Budget  6.0 Mission and Operational Capabilities  6.1 Concept of Operations (CONOPS)  6.2 Mission Profiles and Options  6.3 Fuel and Range charts  V-n Diagram  Flight Envelope  Stability Arguments  6.5 Logistics  6.6 Economics  6.7 Reliability  5 6.8 Safety  7.4 Fuselage  7.1 Wing Subsystem  7.1.1 Block diagram  7.1.2 Analysis and Trade Studies  7.1.3 Risk/Mitigations  7.1.4 CAD  7.1.5 Weight Budget  7.2 Flight surfaces and Control  7.2.1 Block diagram  7.2.2 Introduction  7.2.3 Flaps  7.2.4 Control Surfaces  7.2.5 Risk Mitigation  7.2.6 Results  7.3 Landing Gear  7.3.1 Landing Gear FBD  7.3.2 Calculations and analysis  7.3.3 Risk Mitigation  7.3.4 CAD  7.3.5 Other Concepts Considered  7.6 Avionics/Power/AUX Subsystem  7.6.1 Block Diagram  7.6.2 Power  7.6.3 Risks/Mitigations  7.6.4 CAD  8.0 Compliance  9.0 Conclusions  9.1.1 Conclusion  9.1.2 Future Work  10.0 References     

https://www.pdf-archive.com/2016/05/30/aa-356/

30/05/2016 www.pdf-archive.com

Reyes Caesar Design Portfolio 72%

It included a fighter style cockpit with pilots sitting front to back, top mounted engines and a fuselage shaped around the retardant tank to minimize empty space.

https://www.pdf-archive.com/2016/10/05/reyes-caesar-design-portfolio/

05/10/2016 www.pdf-archive.com

412EP ProductSpecs02-2012 67%

Whitney PT6T-3D Twin Pac engines with more than 25 million flight hours in more than 2,000 aircraft worldwide •• High retirement and overhaul intervals -- 5,000 hour drive system TBO -- 4,000 hour engine overhaul interval -- On-condition composite main rotor blades •• 25,000 hours between premature engine removals •• Excellent Category A / JAR OPS 3 capability •• Rugged fuselage with rollover bulkhead protection and rupture resistant fuel cells The data set forth in this document are general in nature and may vary with conditions.

https://www.pdf-archive.com/2012/05/16/412ep-productspecs02-2012/

16/05/2012 www.pdf-archive.com

W11 series 3 rolls mechanical symmetrical rolling machine 57%

The fuselage eliminates internal stress by annealing and ensures higher precision and strength All machines are designed using SOLID WORKS 3D programming and made with enhanced ST44-1 quality steel with the latest technology.

https://www.pdf-archive.com/2017/10/16/w11-series-3-rolls-mechanical-symmetrical-rolling-machine-1/

16/10/2017 www.pdf-archive.com

W11 series 3 rolls mechanical symmetrical rolling machine 57%

The fuselage eliminates internal stress by annealing and ensures higher precision and strength All machines are designed using SOLID WORKS 3D programming and made with enhanced ST44-1 quality steel with the latest technology.

https://www.pdf-archive.com/2017/10/16/w11-series-3-rolls-mechanical-symmetrical-rolling-machine/

16/10/2017 www.pdf-archive.com

Wing Structural Technical Paper 1 57%

Nomenclature Basic Geometry BL = FS = WL = x = y = y’ = Butt-line (in) Fuselage Station (in) Water Line (in) Ordinate aligned with global fuselage station reference frame Ordinate aligned with global butt-line reference frame Ordinate aligned with local, wing axis semi-span reference frame Aircraft Geometry and Load Factors Nz = Load factor in the z (Water Line) direction (g’s) Sref = Wing Planform Area (ft2) W = Weight representing Mass at 1g (lbm) MTOW = Maximum Takeoff Weight (lbm) MLW = Maximum Landing Weight (lbm) t/c = Thickness to Chord Ratio of Wing Section (%) b = Span of Wing (tip-to-tip) (ft) c = Chord of Wing (ft) t = Dimensional Thickness of Wing Sections (ft) AR = Aspect Ratio (span / chord ) TR = Taper Ratio (ratio of tip-chord to center-line chord) Λc/2 = Mid Chord Sweep Angle (o) Structural Analysis Equations A = Cross Sectional Area of Structure (in2) I = Area Moment of Inertia (in4) L = Length (in) 1 Professor of Practice, Aerospace and Mechanical Engineering, School for Engineering of Matter, Transport &

https://www.pdf-archive.com/2014/12/31/wing-structural-technical-paper-1/

31/12/2014 www.pdf-archive.com

WC67K NC Hydraulic Plate Press Brake With E21 Controller 56%

The fuselage eliminates internal stress by annealing and ensures higher precision and strength.

https://www.pdf-archive.com/2017/10/16/wc67k-nc-hydraulic-plate-press-brake-with-e21-controller/

16/10/2017 www.pdf-archive.com

Order form ADxC-DC 39-001 Blanik STC engl 55%

wings, fuselage sections). Definitions/notes:

https://www.pdf-archive.com/2011/04/18/order-form-adxc-dc-39-001-blanik-stc-engl/

18/04/2011 www.pdf-archive.com

K07112014120000 47%

The fuselage came to rest on its left side against a tree, 280 feet down the wreckage path.

https://www.pdf-archive.com/2014/07/11/k07112014120000/

11/07/2014 www.pdf-archive.com

Geoffrey Andrews AIAA MMA Design Competition Paper 38%

designing an aircraft fuselage capable of withstanding slamming loads during water operations is non-trivial, and structural weight of seaplanes increases as a result.

https://www.pdf-archive.com/2017/05/10/geoffrey-andrews-aiaa-mma-design-competition-paper/

10/05/2017 www.pdf-archive.com

So you want to fly the wooden wonder 32%

right/left outboard (RO/LO), right/left inboard (RI/LI), and an auxiliary fuselage tank (AUX).

https://www.pdf-archive.com/2014/05/30/so-you-want-to-fly-the-wooden-wonder/

30/05/2014 www.pdf-archive.com