abridged list of the specifications provided to us by L-3. The main applications of interest we are comparing our data to are Aeromatic and Datacom. AeroMatic Input AeroMatic Output AeroMatic Input AeroMatic Output # engines speedbrake control [engine config] empty weight engine type engine type CG location (x,y,z) engine layout CL (alpha) horsepower,# ? (X,Y,Z) (CENTER OF PRESSURE?) yaw damper afterburning pilot eye location (x,y,z) CL(elevator deflection) water injection landing gear nose specs dCL(flap) left landing gear specs AeroMatic Output dCL(speedbrake) [propeller config] right landing gear specs engine power, # engine location (x,y,z,pitch, yaw, feed) generated in file (..._engine.xml) Zero lift drag rpm, # thrust location (x,y,z,pitch,yaw) milthrust Induced Drag pitch fuel tank0 size and location (x,y,z,radius, capacity, contents) max thrust CD(mach) propeller dia, # fuel tank1 size and location (x,y,z,radius, capacity, contents) bypass ratio CD(flap) pitch trim idleN1 CD(gear) [aero config] elevator control MAXN1 CD(speedbrakes) aircraft type roll trim MAXN2 CD(Sideslip) TO weight, # left aileron control thrust coeff CD(elevator deflection) wingspan, # right aileron control idle power thrust factor vs. vel and postion plane length,# rudder command military power thrust factor vs. vel and Cy(beta) AeroMatic Input AeroMatic Output AeroMatic Input AeroMatic Output wing area,# rudder control c_thrust (table) Cm(elevator) landing gear flaps control c_power (table) Cm(pitch rate) retractable gear control generated in file (..._aero.xml) Cm(a dot) roll moment, Cl, due to beta horizontal tail area generated in file (..._prop.xml) Cl(roll rate) horizontal tail arm Yaw moment, Cn, due to beta linear blade inches Cl(yaw rate) vertical tail area Cn(yaw rate) Ixx Cl(aileron) Ixx min pitch Cl(rudder) Iyy
*[options] JIALOC location of jet engine *ROUGFC surface roughness factor DEFAULT=.00016in JEALOC *SREF wing area JIEVLOC *CBARR JELLOC *BLREF wingspan JINLTA jet inlet area [aero config] JERAD jet exit radius JEANGL jet exit angle [craft layout] JEVELO jet exit velocity XCG center of gravity location AMBTMP ambient static temp ZCG AMBSTP ambient static pressure XW wing appex location JESTMP jet exit static temp ZW JETOTP jet exit total pressure ALIW wing angle Datcom Output Comments XH horizontal tail location ZH PINF pressure in freestream XV vertical tail location TINF temp in freestram ZV RNNUB ALIH horizontal tail angle VERTUP vertical panel above reference plane (TRUE=DEFUALT) CL_Total • Total Lift Coefficient due to: [body dimension] CLα CL from Basic geometry NX # X locations/segments CLδf CL from Flap deflection X specific x locations CLδe CL from Elevator Deflection R, P, S half-width and/or periphery and /or area at each x CLq CL from Pitch Rate derivative ZU distance to upper body surface CLαdot CL from Angle of Attack Rate derivative ZL distance to lower body surface Cd_Total • Total Drag Coefficient due to: [airfoils] Cdα Cd from Basic geometry NACA speficied Cdδf Cd from Flap deflection User defined (upper and lower surfaces and spefic points or man chord line and thickenss distribution at specific points) Cdδe Cd from Elevator deflection [wing and tail specs] need for wing, h tail, and v tail Cy_Total • Total Side Force Coefficient due to: CHRDTP chord at wing tip Cnβ Cy from Sideslip CHRDR chord at wind root Cnp Cy from Roll Rate
derivative SSPNE semispan exposed panel length Cnr Cy from Yaw Rate derivative SSPN theoretical semispan exposed panel length Cm_Total • Total Pitching Moment Coefficient due to: SAVSI inboard sweep angle Cmα Cm from Basic geometry CHSTAT reference chord station (0.25) Cmδf Cm from Flap deflection TWISTA twist angle Cmδe Cm from Elevator deflection DHDADI dihedral angle Cmq Cm from Pitch Rate derivative TYPE wing shape (1=straight tapered, 2=delta,3=cranked) Cmαdot Cm from Angle of Attack Rate derivative Cl_Total • Total Rolling Moment Coefficient due to: [Aileron, Wing Flaps, and Elevators] Clδa Cl from Aileron Deflection NDELTA # of deflectionangles to test Clβ Cl from Sideslip DELTA specific deflection angles Clp Cl from Roll Rate derivative SPANFI dimension of flap Clr Cl from Yaw Rate derivative SPANFO Cn_Total • Total Yawing Moment Coefficient CHRDFI (Cyδa) Cn from Aileron deflection CHRDFO (Cyβ) Cn from Sideslip NTYPE nose type (1=round, 2=elliptical, 3=sharp) v(Cyp) Cn from Roll Rate derivative CB average balance chord (Cyr) Cn from Yaw Rate derivative TC average thickness • Misc PHETE tangent of arifoil trailing edge angle ε Horizontal Tail Downwash Angle PHETEP tangent of arifoil trailing edge angle δε/δα Derivative of Downwash Angle Chα Elevator-surface derivative with respect to alpha [power] prop or jet but not both (no turboprop) Chδ Elevator-surface derivative due to Elevator deflection [prop] PROPELLER ENGINE All above values calculated using a moment moment
stability axis system AIETLP incidence angle of engine thrust CN Normal force coefficient (body axis) NENGSP # engines CA Axial force coefficient (body axis) Table : AeroMatic and DATCOM Abridged Inputs and Outputs Table 3. Research Related to Project Definition 3.1. Existing similar projects and products Our project is to get a unique set of force and torques measurements of an aircraft, and from our research we have not come across products or projects that does exactly what we’re pursuing, however we have come across products or projects that does a particular part of what we’re pursuing. For instance, one of the goals of our project is to measure the discrete distribution of pressure over an aircraft, so that we may have real-time measurements of forces, torques and pressures. We are planning to use relatively low cost piezoelectric sensors placed at discrete locations over the surfaces of the aircraft. There are some wind tunnel experiments that aim measuring pressure distributions, and a common and novel method employs a small-scale model of an actual airplane like we do, coated in pressure sensitive paint (PSP). They generate a continuous pressure distribution over the aircraft’s entire surface by coating the entire plane’s surface, and utilize the principle of molecular luminescence by emitting for example ultraviolet light on the plane and measuring how much red light is emitted. We do not however have the budget to purchase pressure paint, the optical equipment and software, and a wind tunnel and all the other equipment to utilize this method of measuring pressure distribution. Besides, we want get the pressure distribution in actual flight and during various maneuvers, where the plane experiences up- and down-drafts or air, and air of various moisture levels, temperature, altitudes, and densities. PSP paint also doesn’t meet our requirement for a general method for instrumenting an aircraft, because after an aircraft is completely painted it’s not very simple to
$345.57 Table : Plane Parts List EQUIPMENT DESCRIPTION TOTAL Ardupilot Mega Fully Assembled -includes GPS $250.00 Telemetry Kit Ground Control Station - Ability to change waypoints live - Two way communication: monitor plane electronics status e.g., remaining flight time, battery life, altitude, onboard temp, etc.) $150.00 Protective Case PCB SHIELD $24.95 $424.95 Table : Autopilot Parts List EQUIPMENT Function Unit Price TOTAL 3D Gyroscope -Torque coeff. 1 $13.57 $13.57 3D Accelerometer - Drag Force - Normal Force 1 $14.85 $14.85 Rotary Position Sensor - 333.3 DEG - AOA, AOS 2 $5.50 $11.00 Temperature Sensor -Air Density -Calibration of other parts 1 FREE SAMPLE $0.00 Humidity Sensor -Air Density 1 $13.00 $13.00 Force Sensor - FSR 30 $6.44 $193.20 Differential Pressure Sensor -TAS 1 $12.13 $12.13 Barometric Pressure Sensor -Altitude 1 $3.81 $3.81 $261.56 Table : Sensor Parts List EQUIPMENT DESCRIPTION Unit Price TOTAL 8:1 Multiplexer -Probe for force sensor lines 4 FREE SAMPLE $0.00 AMPLIFIER -Voltage followers for FSR sensors -Integrator/Differentiator configs 4 $1.66 $6.64 Resistors Normal functioning of Ics * FREE SAMPLE $0.00 Capacitors -Control Power up/down switching transients * FREE SAMPLE $0.00