team microsaps - virginia techmason/mason_f/mmapsfinalpres.pdf · team microsaps adam dubinskas...

Team MicroSAPs

Adam DubinskasConor HainesRivers LambJennifer LinLee McCoyShan Mohiuddin

Christopher NickellMonsid Poovantana

Binh TranMichael Tuttle

Whitney WaldronJia-Qi Zhou

April 24, 2003

MicroMAPSMeasurement of Air Pollution from Space (and small)

USC UnitsSI UnitsItem

14 lb62.8 NWeight

6.75 in17.1 cmWidth5.75 in14.6 cmHeight

10 in25.4 cmLength

Gas Filter Correlation Radiometer Detects absorption spectra in IR Compares with known gases in

cells Altitude profiling

Originally for NASAs SSTI Lewis and Clark

Lewis failed in orbit Clark cancelled on ground

Saved in a box at NASA LaRC

CAD drawing courtesy of Resonance Ltd.

Science Mission

Figure courtesy of University of Wisconsin.

Chemical and Transport Processes in Troposphere

CO - indicator for global warming Reduces atmospheres cleaning

capacity

MicroMAPS Goals Map the following:

Concentration 3-D distribution Evolution/Transportation

Track specific emissions events Validate existing data and models

CO concentrations downwind of large-scale biomass burning, Sept. 2000, MOPPITT

Three Platforms

MicroMAPS1

(1) Resonance Ltd., (2) Scaled Composites

Proteus2

DedicatedAircraft

DedicatedSpacecraft

Spacecraft Advantages

Pre-existing spacecraft plan

Near global coverage

Observe transport processes over time

Instrument environment

Spacecraft Layout

Velocity Vector Nadir

Spacecraft Features 3 year lifetime

425 km BOL altitude degrade to 300 km Launch as secondary payload

Designed for Athena II, Delta II, Taurus Physical Quantities

Mass: 131.7 kg Span: 4.9 m; Height: 0.81 m

3-axis stabilized Communication in S-band

Proteus Advantages Allows low risk opportunity to prove

instrumentation technology Low Cost Altitude Profiling Variable Flight Schedule Proven/Current Support Technology Easy/Modular Construction Preexisting knowledge base Low Cost

Instrument Suite

Instrument Suite Attributes

Sealed Nitrogen atmosphere with desiccates Pump/purge environmental regulation Base platform doubles as large thermal mass Thermal monitoring system Power management and filtration system Internal and external data retrieval systems Easily detachable from Proteus Room for future additions to payload

Dedicated AircraftPlatform Advantages More detailed local data Respond to and track emissions

events Multi-aircraft, multi-instrument

coordinated missions Lower cost

Aircraft RFP Cruise altitude > 60,000 ft Endurance > 36 hours Range > 7,000 NM Cruise Velocity = 250 ktas Modular Payload < 250 lb capacity

I hope theres something interesting down there.

ANYTIME, ANYWHERE

Figure courtesy of NASA

Aircraft Layout

Aircraft Features UAV Low-wing monoplane

High aspect ratio wing Axi-symmetric fuselage, tail booms A-tail

Modular payload bay in fuselage nose Rear-mounted turbofan Retractable tricycle landing gear

QuantityItem

1,200 lbSL Trust

62.0 ftSpan3,000 lbTOGW

28.0 ftLength

Aiolos Spacecraft DesignRivers Lamb

Jen LinBinh Tran

Mike TuttleJosh Zhou

Synopsis Orbit analysis

Subsystem solutions

Cost analysis

Summary

Orbit AnalysisPropulsion?

Launch:June 1, 2007

Orbit Analysis Orbital decay depends on

altitude, density, and ballistic coefficient

Goal: 3 year lifetime Use EOL altitude of 300

km for design BOL altitude of 425 km

(CB = 74 kg/m2)

Inclination

Orbit Determination

Surrey GPS Receiver (SGR-10) Two antennas Position Accuracy: 15 m Velocity Accuracy: 1.5 m/s Power Consumption: 5.5-7.0 W Size: 160 x 160 x 50 mm Mass: 1 kg

Launch VehicleForeign

GTO

Cost Comparison

0 5 10 15 20 25 30

Cost per kg to LEO (FY00$K/kg)

Athena I

Athena II

Delta II (7920)

Pegasus XL

Space Shuttle

Titan II

Taurus

Athena IIProperties

1650Payload (kg to 425km, 64)20Orbit Injection Accuracy (km)

6.1 x 2.3Payload Faring (m)8.0Axial Load (g)1.8Lateral Load (g)30Mid Longitudinal Frequency (Hz)

KLCLaunch Site (for 64)

0-2Flight Rate (units per year)

13.3Cost per kg to LEO ($K/kg)3/5Flight Record

26Unit Cost ($M)

12Mid Lateral Frequency (Hz)

Delta II 7920Properties

4000Payload (kg to 425km, 64)9.3Orbit Injection Accuracy (km)


VAFBLaunch Site (for 64)



50Unit Cost ($M)


TaurusProperties

1050Payload (kg to 425km, 64)29.6Orbit Injection Accuracy (km)


VAFBLaunch Site (for 64)



20Unit Cost ($M)


First Choice?

Ranked the vehicles: Cost Environment Reliability Availability Mass to Orbit Payload Volume0

5

10

15

20

Athena II Delta II Taurus

ADCS


Attitude Determination

Two Ithaco Conical Earth Sensors Roll and pitch Accuracy: 0.1 Power Consumption: 8 W Size: 0.99d x 1.18 mm Mass: 1.1 kg

Requirement: 0.5

Attitude DeterminationFive Surrey Sun Sensors

Accuracy: 0.5 Power Consumption: 100 mW Size: 95 x 107 x 35 mm Mass: 0.3 kg

Ithaco Magnetometer (IM-103) Power Consumption: 100 mW Size: 55 x 42 x 36 mm Mass: 0.227 kg

Attitude ControlRequirement: 2.5 (nadir)

EOL(10-6 N-m)

BOL(10-6 N-m)

Torque

3003.8Aerodynamic

2.62.6Solar Radiation5351Magnetic

7.67.2Gravity Gradient

37064Worst Case

Attitude ControlIthaco Momentum Wheel (TW-16B32)

Momentum Capacity: 16.6 N-m-s Reaction Torque: 32 mN-m Power Consumption: 6.5 W Size: 255 x 93 mm Mass: 5.9 kg

Three Ithaco Torquer Rods (TR30CFN) Linear Moment: 12 A-m2 Power Consumption: 0.9 W Size: 18d x 381 mm Mass: 1 kg

Electric Power System

Power Operating Conditions Who needs how much power and when

Two major operating environments Daylight Eclipse

Subsystem needs based on average and peak power conditions

Power Usage Profile

551Computer111Receiver

75.51GPS Unit0.50.55Sun Sensor0.10.11Magnetometer16162Earth Sensor4.82.73Torque Rod50171Reaction Wheel

Peak (W)Average (W)QuantityComponent

Power Usage Profile

167.684.9526Totals771

Charge ControlUnit

27.216.151MicroMAPS14142

Solar ArrayDrive

502Solar ArrayDeployment

3001TransmitterPeak (W)Average (W)QuantityComponent

Solar Array Supply component power

needs in daylight Recharge batteries Use of Spectrolab triple

junction cells

24.5 %Efficiency (Production)26 %Efficiency (Lab)2.275 VVoltage2.352 gMass191 mThickness28 cm2Area

Solar Cell Info

Solar Array

Solar Array Power Requirements PSA (425 km) 181 W PSA (300 km) 188 W

Beginning and End of Life Capabilities PBOL 254 W/m2 PEOL 250 W/m2

Array Area and Mass ASA 0.75 m2 mSA 7.24 kg

Solar Array

14Cells in series20Cells in parallel280Total cells in array

Composed of 2 panels 490 mm by 800 mm

2 axis of rotation Pitch and Yaw Achieved using Moog

biaxial gimbals

Energy Storage Provide power in eclipse and

augment array power in peak condition

Use of SAFT lithium-ion batteries

0.25 mHeight0.054 mDiameter1.132 kgMass

3.6 VVoltage125 Wh/kgSpecific Energy Density

Battery Info

Energy Storage 30% depth of discharge and ~17000

cycle lifetime

Required battery capacity: 371 Wh 3 cells in parallel (to achieve capacity) 8 cells in series (to achieve bus voltage)

Total pack mass: 17.5 kg

Communication

CommunicationAeroAstro S-Band

Transmitter w/HPA 2.2-2.3 GHz Power supply: 28 V, < 30 W 127 x 50.8 x 25.4 mm Up to 10 Mbps RF output power

2 to 5 W 0.5 kg

Communication

AeroAstro S-Band Receiver 2.025 2.120 GHz Power supply: 5 V, < 1 W 76.2 x 50.8 x 25.4 mm 1 to 9.6 kbps 0.18 kg

Communication

SSTL S-Band QuadrifilarHelix Antenna ~0.5 kg 2.01-2.1 GHz uplink 2.22-2.29 GHz downlink 100 X 100 X 500 mm

Command and Data Handling

Command and Data Handling

SSTL OBC 386 Intel 386EX 128 MByte ramdisk Power supply: 28 V, 5 W 330 x 330 x 32 mm 1.7 kg

Structural Design

Structural Design

Material Properties Aluminum 7075-T73 plates

Structural Design Structural dimensions Subsystem specifications

Optimization and Final Design

Material Properties

150 W/mKThermal Conductivity, kAL27 GPaModulus of Elasticity, GAL0.321Poissons Ratio, AL

20 MPam1/2Fracture Toughness, KALIC

0.08 %Elongation, eAL

71 GPaYoungs Modulus, EAL

390 MPaYield Strength, ys

460 MPaUltimate Tensile Strength, ult

24 (106.K)-1Coefficient of Thermal Expansion, AL

ValueQuantity

Aiolos Dimensions

Deck Height

Face Width

Edge Width

263.9Face Width609.6Edge Width

6.4Ceiling Thickness15.9Wall Thickness

812.8Total Height406.4Deck Height304.8Inscribed Radius

Value (mm)Quantity

Aiolos Mass Profile

74.7Empty Structure

6.4MicroMAPS57.0Subsystem Total

4.25Thermal

131.7Aiolos Total

25.9Power1.0Orbit Design1.2Communication1.7C&DH

16.6ADCSMass (kg)Subsystem

Structural Design


Thermal Management

Temperature Limits

50-20AeroAstro S-Band Transmitter

532---Aluminum 7075-T73

400-269Aluminized Kapton (MLI)

300SAFT Lithium Ion batteries

60-40AeroAstro S-Band Receiver

50-5Computer

90-90Surrey 2-Axis Sun Sensors

60-20Ithaco 3-Axis Magnetometer

71-34Ithaco Magnetic Torquer rods

70-55Ithaco Reaction Wheel

48.9-6.67MicroMAPS instrumentMax Temp (C)Min Temp (C)Component

Internal Power Dissipation

2.42.4SAFT Lithium Ion batteries

2.82.2GPS Unit

Active (W)Non-Active (W)Component

2.02.0Computer/Processor

2.82.8Battery Charge Control Unit71.9839.26Total Power Dissipation

0.40.4AeroAstro S-Band Receiver120SSTL S-Band Transmitter

0.20.22-Axis Sun Sensors (x5)0.040.04Ithaco 3-Axis Magnetometer

6.46.4Conical Earth sensors (x2)1.921.08Magnetic Torquer rods (x3)

206.8Ithaco Reaction Wheel10.886.48MicroMAPS instrument

Environmental Fluxes

246220Earth IR36%28%Albedo

13530Solar

Daylight (W/m2)Eclipse(W/m2)

Source

1687.56281.6Total

Thermal Insulation Aluminized Kapton outer layer

Indium oxide coating 2 mil thickness BOL: =0.39, =0.75 EOL: =0.47, =0.75

Mylar film middle layers (18) Aluminum backing 0.5 mil thickness =0.15, =0.34

Aluminized Kapton inner layer

Thermal Insulation Layers separated by non-conductive

nets made of Dacron Evacuate air using vent paths

Prevent MLI from billowing during depressurization of launch

Small perforations in all layers Held together by stitch or buttons

at interval Attach to Aiolos using Velcro strips

Passive Components

Radiator Aluminum, located on

side panels Coated with white paint

Barium Sulfate w/ polyvinyl alcohol

=0.06, =0.88

Production Cost Analysis

1,386.716.927 kgADCS5,050.14Total

902.991.7 kgC&DH1,409.5125.86 kgPower148.064.25 kgThermal

1,029.0774.67 kgStructure173.791.18 kgComm

TFU Cost(FY03$K)

Mass Parameter

Aiolos Summary Functional platform for achieving

instrument science goals

Provides 3 year continuous monitoring of transport processes

Subsystems designed for maximum performance at reasonable cost

Questions

Proteus Instrument DesignAdam Dubinskas

Lee McCoyChris Nickell

Whit Waldron

Overview Instrument Suite Overview and Structures

Computer and Data Acquisition

Environmental Telemetry

Power

Instrument Suite Overview and Structures

Instrument Suite MicroMAPS Instrument PC104 Stack MicroMAPS Power Supply (2) NBF50 NB50S CB5S Gasket Nose cone/platform assembly

Instrument SuiteMicroMAPS Instrument

Dimensions in inches

Instrument SuitePC104 Stack


Instrument SuiteMicroMAPS Power Supply


Instrument SuiteAuxiliary Power Supply Elements

CB5S EMI Filter

NB50S Main Power

NBF50 EMI Filter


Instrument SuitePlatform


Instrument SuiteNose Cone


Instrument SuiteNosecone/Platform Assembly

Courtesy of Dr. John Companion

Computer and Data Acquisition

ComputerCPU Board MZ104+

www.tri-m.com

ComputerCPU Board MZ104+ ZFx86

Dual Intel 82559ER 10/100 BaseT EthernetDual 16550 compatible RS232 Serial

Up to 115.2K BaudDual IDEDual USB v1.1Enhanced Bidirectional Parallel PortPhoenix BiosDual Watchdog timersDiskOnChip

ComputerCPU Board Utility/Interface Board

Computer Operating System

Linux RAM

64 Megabytes SDRAM single Dimm Power Consumption

Depends on amount of RAM and CPU bus frequency

CPU Board

ComputerCPU Board Mechanical Specifications

PC104+ compliant form factor3.55x3.775x0.9 (90mm x 96mm x 23mm)

Weight0.15 lb (0.07 kg)

Heat Distribution33, 66, and 100 MHz operation

-40F to 185F (-40C to 85C)133 MHz operation (over-clocked)

-4F to 158F (-20C to 70C)

ComputerVehicle Grade Power Board HE104

www.tri-m.com

ComputerPower Board HE104

50 Watt DC-DC High Efficiency ConverterCleans and filters power for the PC104 computer

+5V, +12V Outputs (-5V, -12V optional)6V - 40V Input RangeHeavy Duty Load Dump Transient 5000W

SuppressorsUp to 95% Efficiency in Load RegulationRemote On/Off Logic Level control

ComputerPower Board Mechanical and Electrical

Specifications

ComputerCT104 PC104 Enclosure

www.tri-m.com

ComputerCT104 Enclosure

Anodized Aluminum constructionAnti-shock mounting padI/O interface EndcapsSecurely mounts PC104 cards using four

rubber corner guides

ComputerEnclosure Mechanical Overview

Holds PC104+ compliant form factor3.55x3.775 (90mm x 96mm)

Customizable endcaps for various I/O setupsSelected 6 Heightfor later expandability

Environmental Data Acquisition

Instrument Suite Environment Internal Environment

Pressurized at 5 psi using Ultra High Pure Nitrogen (UHP) Humidity will be kept at or near 0 percent

Temperature will not be regulated Instrument and component temperatures will be

monitored

Instrument Suite Environment

1-Wire Bus Supplies control, signaling, and power over a single-wire

connection Monitor temperature, pressure, and humidity We will utilize a linear topology type of 1-Wire network

Instrument Suite Environment

TEMP05 Serial Interface between

1-Wire network and PC104

Able to read up to 60 temperature, pressure and humidity sensors

Produced by MidonDesign

Instrument Suite Environment Temperature Sensor

DS18S20 Digital 1-Wire Thermometer by Dallas

Semiconductor Operating range of -55 to

125 degrees Celsius Internal pod temperature will

vary between -10 to 50 degrees Celsius during flight

3.0 to 5.5V supply voltage range

Instrument Suite Environment Pressure Sensor

BAR-2001S by Point Six, Inc. Internal pod pressure held

constant at 5 psi 5.0 V supply voltage

Humidity Sensor HMP-2001S by Point Six, Inc Internal pod humidity at or

near 0 percent 5.0 V supply voltage

Instrument Suite Environment Sensor Placement

Power Configuration Proteus power: 28 +/- 0.5 V-DC

Voltage must be cleaned and regulated to within MicroMAPS limits

Power must be supplied for the PC-104 and environmental sensors

Manufacturers

Martek Power Commercial off the shelf DC-DC

converters Military Grade screened to environmental

conditions DigiKey

D-sub 9, 15, 50 connectors and pins #20 AWG hook-up wire

Components Primary Converter: NB50S

50W 28V-28V DC converter Cleans and regulates power input from Proteus NBF50S EMI Filter to minimize noise on input signal 3 x 1.5 x 0.38

PC104 Converter: CB5S 5W 28V-15V DC Converter Provides ample voltage and current for the data

acquisition and environmental monitoring suite 1.0 x 1.0 x 0.38

NB50S, CB5S, Martek Power Abbott, Inc. , http://abbottelectronics.com

Components MicroMAPS Converter Option 1: NB45T

45W 28V 5, 15V DC converter Compact power supply capable of providing all necessary

power to MicroMAPS Used in conjunction with secondary NBF50 EMI filter to

minimize noise 3.0 x 3.0 x 0.38

MicroMAPS Converter Option 2 Supplied by NASA 28V Input; 5, 15V DC output Significantly larger than NB45T No further information currently available

Components EMI Filter: NBF50

Thermally non-dissipative device Less than 1.0 volt drop across the NBF50 Does not require external components 2 EMI Filters:

NBF50S (primary) NB45T (MAPS)

1.75 x 1.5 x 0.38

NBF50 EMI Filter, Martek Power Abbott, Inc. , http://abbottelectronics.com

Power Layout

MAPS

Proteus

PC-104

Instrument Requirements

30 Watts14 Watts (max)15V Power Consumption15 Watts14 Watts (max)5V Power Consumption 100 mV 250 mVPeak-Peak 11Hz - 200kHz 50 mV 100 mVNoise RMS 1hz 200kHz 25 mV 50mVLoad Regulation 1% 2%Power Balance

25 mV5% (750 mV)15V fluctuation 25 mV5% (250 mV)5V fluctuation

MAPS NB45T Power Supply (per channel)

MAPS LimitsInstrument Power Requirements

Environmental Concerns

21.4 W**Total Power Dissipated:*10 W80%NB50S50W< 35WMain Power

1 W76%CB5S5W< 5WPC104

10.4 W73%NB45T45W28W MAPS Option 1:

NB45T

Power Dissipated

EfficiencyModel#Avail.ReqdComponent

* EMI Filters generate no heat** Average value. Maximum = 33.5W

Review Instrument Suite Overview and Structures

Aluminum Construction to be built by Raytheon and Scaled Composites

Computer and Data Acquisition PC104

Environmental Telemetry 1-wire Bus

Power Cleaned 28V DC Power filtered though EMI Filters

Questions

Menelaus

Conor HainesShan Mohiuddin

Monsid Poovantana

Aircraft Outline RFP Chosen Concept, Sizing Aerodynamics, Stability

and Control Materials, Structure,

Weights Propulsions, Mission

Analysis, Systems, Cost Conclusions

Aircraft RFPBenefits of an Aircraft-Based Platform:

Instrument Operations Stronger infrared signal Multi-aircraft missions for greater

coverage and data redundancy Maintenance without Astronauts

Mission Flexibility No fixed orbit Local data over long periods of time Variable mission paths Immediate response to emission

events (volcano, fire) Interchangeable payload

configurations Mission Cost

No launch cost Less rigorous platform criteria

250 ktasVcruise36 hrsEndurance

>60,000 ftAltitude

Endurance Mission

Chosen Design

BUT Big (length) Complicated heavy Large Ks Empennage design

Revised Chosen Design

Compact, simpler, lighter A-tail, communications dome Fuel in wings, systems in booms

Sizing Two pronged approach

(1) Weighted averages of existing aircraft(2) Raymer algorithms

48.453.3Span Loading (lb/ft)62.058.8Span (ft)

Final ValueTarget ValueParameter

0.400.38Thrust-to-Weight Ratio1,2001,141SL Thrust (lb)0.961.10Lift Coefficient

18.818.2Wing Loading (lb/ft2) 160.0164.8Wing Area (ft2)3,0003,000TOGW (lb)

Wing A-Tail

Area (ft^2) 160 10.5 Aspect Ratio 24.4 6.9 Taper Ratio 0.5 1.0 Span (ft) 62.0 12.0 Root Chord (ft) 3.25 1.75 MAC (ft) 2.64 1.75 Tip Chord (ft) 1.63 1.75 Thickness (%) 17 12 Incidence (deg) 3.0 0.0 Dihedral (deg) 0.0 0.0

Aerodynamic Data

Menelaus Virginia Tech Aerospace Engineering Scale Dimensions feet Date 4/22/2003 Prepared by Shan Mohiuddin File Name MenelausThreeViewX

TOGW (lb) 3,000 Empty Weight (lb) 1,200 Fuel Weigh (lb) 1,800 Max Payload (lb) 250 SL Thrust (lb) 1,200

General Data

A

A

Section A-A3x drawing scale

Aerodynamics

Goals of This Analysis Minimum drag at cruise

Promote laminar flow Guide configuration design

Systematically alter S, b, , i Tradeoff with fuel capacity

thickness-to-chord ratio

DragFriction.f Model aircraft components

Fuselage, booms as average radius cylinders

Wings, tail as plates, finite thickness

-0.01679CD00.029

0.002370.01442

550Value

-CD Cruise

UnitElement

-Friction Drag-Form Drag

ft2Total Swet

Configuration Design Tornado VLM code Checked with VLMpc

Results

3.2 deg1.5 deginc.2.64 ftMAC

33.1L/D

0.96CL Cruise0.029

2462 ft

160 ft2Value

CD Cruise

Element

bAR

S

Thickness-to-Chord

Airfoil Choices

Wing - LS(1)-0417 Fuel Structure Laminar flow

Tail NACA 64-012 Structure Laminar flow

Figures courtesy of University of Illinois

Stability and Control

Goals of This Analysis Justify configuration

geometry Characterize the stability Size control surfaces

Tail Design

Nose Right Yaw V-tail

roll right Traditional

roll right

A-Tail

Proverse Roll-Yaw Coupling Works well with booms Supports satellite communications dome

Static StabilityStatic MarginAircraft

0.0 to 0.15Fighter0.0 to 0.05Menelaus

0.05 to 0.10Commercial Transport

Method of Analysis Tornado Cm, CL Validated by VLMpc

Ks = 0.022 (2.2% stable) @ beginning of missionKs = 0.005 (0.5% stable) @ end of mission

Control Surface Sizing

Dimensions in feet

Method Raymer Tornado for stability

derivatives Aileron Results

20% chord Area = 4.2 ft2 39% to 67% the semispan

Control Surface Sizing

Ruddervator Results 25% chord Area = 2.4 ft2

Dimensions in feet

Materials Selection

Driving Factors Weight Strength CostTwo Chosen Aluminum Carbon fiber

Trade off Aluminum

Heavier Lower tensile/yield strength Cheaper

Carbon fiber Lighter Higher tensile/yield strength More expensive

$3,459 Cost $1,779 Cost

Approximate Material

Approximate Material

1218.38Total1778.57Total250.00AlPayload250.00AlPayload

260.00AlInstalled Engine260.00AlInstalled Engine

148.20AlLanding Gear148.20AlLanding Gear54.38CFBooms108.77AlBooms

127.80CFFuselage255.60AlFuselage7.00CFV. Tail14.00AlV. Tail

21.00CFH. Tail42.00AlH. Tail350.00CFWings700.00AlWings(lb)(lb)

WeightMatlComponentWeightMatlComponent

Materials Cost

Materials Selection

Carbon Fiber Fuselage Wings Booms A-tail

Different materials for each component

Aluminum Main and nose

landing gears Bulkheads Ring frames

Weights Table

3,000609449

1,942

Weight (lb)

477,147TOGW

Total Moment (in-lb)

Component

99,195Propulsion80,711Systems

297,241Structure and Fuel

CG = 13.34 ft from noseh = 0.47

Maximum Gust Loads

More emphasis on Gust envelopeDesign to fly in steady flightNo high G maneuvering

Positive ultimate load = 4.04Negative ultimate load = -2.04

Fuselage and Booms

Booms Same construction as

fuselage Flight controls and navigation

system in each boom

Fuselage Bi-directional carbon fiber-

Nomex sandwich Eight tophat longitudinal

stiffeners Two bulkhead wing box Three ring frames

Cross section of fuselage near payload attachment

Wing Structure

Wings Composite material Wing box with box beams Ribs every three feet

along the length of the wings

Ample fuel tanks

Figures courtesy of Drexel University

Wing A-Tail


Aerodynamic Data



General Data

A

A


Constraint Diagram

Landing Field Length

Cruise

Take-Off Field Length

Current PositionClimb Gradient

Propulsion Requirements

*>50062.3222.96~0.4863000TFFJ44-3*>50021.847.2~0.4862400TFFJ44-2C

TFTFTFTF

Type

150019001200700

Max Power

At S.L.(lb)

0.480.48

~0.486~0.486

SFC(/hr)

20.920.919.014.5

MaxDia.(in)

46.746.737.841.0

MaxLength

(in)

BypassRatio

Dry Weightw/o Avionics

(lb)

Model

3.4459FJ44-1C

*

Engine SelectionWilliams/ROLLS FJ44-1A

FAA and JAA CertifiedScaled Properties

SFC @TAMB=59F 0.486Takeoff Thrust 1200 lbBypass Ratio 3.28Weight (Dry) 270 lb

23.7 38.9

17.316.7

14.3

45.2

Both Figures Courtesy http://www.williams-int.com/product/1a.htm

Engine Installation

Inlet CharacteristicsSubsonic Airflow (M < 0.5)

No need for shock dissipating geometryFreestream velocity optimal

InletPerpendicular to freestream velocityRaised 1 above the fuselage

Ducting Standard Rectangular to Circular Gradient Increasing Inlet Area

PerformanceOptimal Mission Profile Characteristics

Time in Flight 33.8 hrs Total Distance Covered 8300 NM Time to 60,000 ft 84 min

Menelaus Comparison

0.9618.80.4

250+1200 lb

(1)Turbofan

34+

8 ,000+

60,000+3,000250

1,8001,200

241606228

Virginia Tech

Menelaus

13.72526.523.323.518Aspect Ratio301540134*315234Wing Area (ft2)

2,8743,100*1,1863,2502,650Empty Weight (lb)7,30014,500*6143,0003,000Fuel Weight (lb)2,3002,000264330750750Payload Weight (lb)12,47425,6002,2002,1307,0006,400TOGW (lb)

77116.271.555.38664Wingspan (ft)56.344.42523.63434Length (ft)

Scaled Composites

Proteus

Northrop Grumman

Global Hawk

Aurora Flight

Sciences Perseus B

General Atomics Altus II

General Atomics Altair

General Atomics

Predator B

61,00065,00065,00065,00040k-65k40k-65kAltitude (ft)

5,40016,6006,000 (est.)6,000 (est.)6,200 (est.)

6,000 (est.)Range (NM)

2442243224Endurance (hrs)

1.81.60.71.02.01.5Lift Coefficient41.547.411.316.322.227.3W/S (lb/ft2)

0.436270

700 hp

(1) Turboprop

0.329210

2,300 lb

(1)Turbofan

0.196258

100 hp

(1) Piston

0.130258

100hp

(1) Piston

0.277345

7,100 lb

(1) Turbofan

0.368T/W

4,586 lbHP/Thrust (hp/lb)272Cruise Speed (ktas)

(2) TurbofanEngine # and Type

* Information Not Available | Aircraft Images Copyright their Respective Producers

Systems

Payload

Collision Avoidance

Fuel

Landing Gear

Payload

Communications Dome

Engine

Fuel System

Landing Gear

Figure courtesy of NASA

Communication System

http://www.telediaspora.com

Due to the Beyond Visual Range Nature of Menelaus, Line of SightCommunication Devices are Impractical

Satellite Communications Equipment is the Optimal Solution

Collision Avoidance System

Collision Avoidance Similar to systems being tested on Proteus

Cost

$2,628,315 Total 5 Units$13,141,575Total 1 Unit

$822,976.86 Engineering Production Cost

$1,433,445.72 Manufacturing Materials Cost

$1,790,930.38 Flight Test Aircraft$8,390,142.00 Development Support Cost

$167,867.15 Manufacturing Hours$175,116.74 Tooling Hours

$3,459.12 Material Cost$361,097.13 Engineering Hours

CostCategory

Cost $361,097

$8,390,142

$167,867

$3,459

$175,117

$1,790,930

$822,977

$1,433,445.72

Engineering Hours Material Cost Tooling HoursManufacturing Hours Development Support Cost Flight Test AircraftManufacturing Materials Cost Engineering Production Cost

Measures of Effectiveness

8,000 NM>60,000 ftMenelaus

7,000 NM>60,000 ft

RFP

OKVcruiseOKClimb Time

CommentItem

OKModular Payload

ExceedsRangeCloseEndurance

OKAltitude

Wing A-Tail


Aerodynamic Data



General Data

A

A


team microsaps - virginia techmason/mason_f/mmapsfinalpres.pdf · team microsaps adam dubinskas...

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