MANAGERIAL DESIGN REVIEWP10232 – UAV AIRFRAME C

Daniel Graves – Project Lead

James Reepmeyer – Lead Engineer

Brian Smaszcz – Airframe Design

Alex Funiciello – Airfoil Design

Michael Hardbarger – Control Systems

Customer Needs

Key Project Goals: Airframe must be able to carry a fifteen pound payload Easy integration with measurement controls box and

different aerial imaging systems Ability to remotely control aircraft and activate payload Ability for flight communication between aircraft and

ground relay Aircraft provides twenty minutes of flight time for local

area photography Aircraft has the potential to take off and land on site Easy assembly and disassembly of the aircraft for

transportation

Lessons Learned From P09232 The aircraft’s wings sheared off shortly before

impact. The failure was determined to be from the bending stress applied to the wings during the banked turned.

After analysis, it was concluded that the main

fiberglass spar used to support the wing was not selected properly to handle the flight loading.

High bend in the wing during flight inhibited the pilot’s control of the aircraft by reducing the effectiveness of the control surfaces.

Design goals based on lessons learned from P09232

Reduce wingspan (reduced bending moment)

Re-enforce wing spar

Reduce plane weight

Re-evaluate electric propulsion

Project Status CAD model – Nearly done, ready to start creating

laser drawings Propulsion / Controls – Ready to place order on

motor and battery Landing Gear – Re-use last year’s Wing Spar – One piece spar is satisfactory; pending

confirmation from supplier on specs and availability Airfoil – Airfoil will lift plane and allow for flight control Wing box / wing design – Pending wing spar

information

Action Items

Action Items

Prove control surface equations viable with analysis

Optimum lift/drag and airspeed Optimum rate of climb with analysis Look into carbon fiber rod

cost/practicality of constructing our own

Action items

Look into carbon fiber rod cost/practicality of constructing our ownCarbon Fiber is the best option for the main sparQuality control on home-made carbon fiber spars

is very lose Maximum bending load of carbon fiber rod

Carbon Fiber rod should be sufficient to support plane weight; pending supplier specifications

Action Items

Approximation of distributed load as a point load at wing centerPrior analysis was correct, action item

dismissed Check loading analysis loading vectors

(banked turn FBD)Analysis deemed unnecessary

Action Items

Tabulate detailed calculationDetailed calculations are being updated and

documented Correct ply-wood B.O.M. error

Actual ply-wood required: 3 sheets, not 44Total ply-wood costs is approx. $73.00

Run some numbers on the loading and aero CGThe aero CG is located at the 3/4 chord of

the wing

Action Items

Notch the corner for the bottom plate of the main payload bayThe plane body has been adapted to receive the

wing mounting Provide proof airframe is stable at 40mph

Airframe can be controlled and stabilized at cruise speed using designed control surfaces

Provide proof airframe can power itself at 40 mphThe airframe requires approximately 734 watts of

power to maintain 40 mph

Action Items

Look into an analysis of torque on the elevatorServos will be able to control all flight control

surfaces Crush load on wood for wing mount

The plane body has been adapted to receive the wing mounting

Nail down wing box designWing box mounting design has not yet been

finalized

Action Items

Nail down tail mount designTail mount has been finalized, similar to

mount from airframe B

Customer Requirements

Airframe must be able to carry a fifteen pound payload

The aircraft shall have a maximum weight of 25 lbs without payload (40 lbs gross)

The aircraft shall be capable of stable flight with a 15 lb payload

The aircraft shall be able to take off under its own power from a 1000 ft grass runway

Easy integration with measurement controls box and different aerial imaging systems

The aircraft shall utilize an open architecture payload interface

The aircraft shall be capable of stable flight with a 15 lb payload

The aircraft shall provide a secure anchoring connection for the photographic instrument payload

The aircraft shall provide a secure mounting location for the flight control electronics package (P10236)

Ability to remotely control aircraft and activate payload

The aircraft shall utilize an open architecture payload interface

The aircraft shall provide a mechanical interface to the payload

The aircraft shall provide a secure anchoring connection for the photographic instrument payload

The aircraft shall provide a secure mounting location for the flight control electronics package (P10236)

Ability for flight communication between aircraft and ground relay

The aircraft shall provide a secure mounting location for the flight control electronics package (P10236 and P10231)

Aircraft provides twenty minutes of flight time for local area photography

The aircraft shall have a flight ceiling of 1000 ft The aircraft shall be able to sustain a flight of at

least 40mph in calm conditions The aircraft shall be capable of stable flight with a

15 lb payload The propulsion system shall provide uninterrupted,

constant power for at least 20 min The servos shall be of sufficient power to control

the plane’s control surfaces at speeds up to 50 mph The aircraft shall be structurally sound; no parts

shall leave the aircraft while in flight

Aircraft has the potential to take off and land on site

The aircraft shall be able to take off under its own power from a 1000 ft grass runway

The landing gear shall hold the plane at an optimal angle of attack while on the ground

The aircraft shall be able to navigate while on the ground

Easy assembly and disassembly of the aircraft for transportation

The aircraft shall be able to be transported in a motor vehicle when disassembled

The aircraft should be easy to assemble and disassemble by one person

Risk Management

https://edge.rit.edu/content/P10232/public/Risk%20Managment%20Rev%202.pdf