Avionics Group Project Chris Flood Matt Marcus Kiran Patel Tim Russell

Problem Statement Calculate communications link budgets for a variety of links Compile sensors list for mission Develop list of possible ENAE484 projects for next semester and rank top 3 project ideas

Sensors List Proximity Sensors Linear Motion Angular Rotation Hull Temperature Cabin Temperature O2 / CO2 / CO / Humidity Sensors Cabin Pressure Solar Panel Energy Output Fuel Gauge

Proximity Sensors High criticality sensors, will have redundant sensors in case of failure during mission Must function for proper navigation Sampling rate - 1Hz Scanning Laser Rangefinder – 10 total sensors 4 spaced 90 degrees apart all the way around the craft 4 sensors redundant to these on vehicle hull 2 placed on bottom of craft for docking and landing

Translational and Angular Motion Continuous high sampling rate Extremely critical system for navigation and control Have redundant sensor in case of failure Sampling Rate - 10 Hz – Important to have up to date information for spacecraft motion and control Use stock 2 IMUs – Measure x, y, z, roll, pitch, yaw – ENERGY REQUIREMENTS

Cabin Temperature / Pressure Sensors Highly critical sensors for life support applications Not necessary for spacecraft function Sampling Rate - 1Hz Absolute Pressure Sensor for pressure Thermistors for Cabin Temperature Determine cabin pressure throughout mission Keep cabin pressure within habitable limits Keep cabin temperatures within habitable limits

O2 Sensors For O2 tanks, important for tracking propellant pressures – absolute pressure for tanks Sampling Rate – 1Hz Detect O2 levels within cabin at any point in time Determine limits for safe operation, remain out of critical flammability limits O2 pressure sensors for O2 tanks Determine pressure, amount of usable O2 remaining in tanks at any given time during mission

CO2/CO Sensors Not critical for mission, only determines CO2/CO in cabin, mission continues with or without Sampling Rate – 1 Hz Determine levels of CO2/CO within crew cabin Remain within safe limits for astronaut habitability Determine amount of CO2/CO scrubbing necessary at any point in time during mission ENERGY REQUIREMENTS

Solar Power Energy Output Use voltmeters to determine voltage generated from solar cells Sampling rate: 10Hz Determine power output of solar panels over time Ensure adequate storage and generation of energy Disable non vital systems during power lows

Fuel Gauge Keep track of pressures and amounts of propellants remaining for mission Ensures proper rationing of propellants for use throughout mission duration Sampling rate: 10Hz Very high criticality for propulsion system

DBTE Ideas : Human Factors for an Inflatable Habitat (Top 3) Optimal interior layout / sizing Launch configuration for uninflated structure What can we test? – Configuration and placement of hardware – Create various different layouts for habitat and have participants rate ease of task completion each configuration

DBTE Ideas : Window configuration (Top 3) Determine adequate sightlines for landing What can we test? – Test different window configurations / layouts – Design a variety of window configurations and find optimal window angle and layout for maximum visibility

DBTE Ideas : Window configuration (Top 3) Why do we care? – Previous Space habitats (e.g. ISS) have not been inflatable – Gather data on efficient layout and design of inflatable habitat

DBTE Ideas : Window configuration (Top 3) Why do we care? – Landing is riskiest part of mission, human executed task, ensure proper visibility

DBTE Ideas : Sleeping Arrangements (Top 3) Create adequately comfortable sleeping conditions for astronauts What can we test? – Bed types and arrangements within crew cabin – Test sleep quality through various sleeping configurations via stamina and functionality test after sleeping Why do we care? – Sleep is critical for astronaut health and for proper functioning during mission

Additional DBTE Ideas Water cycle taste test Airlock evaluation Situational awareness of robotics operator Ladder design Visibility when docking Suit port entry exit

Communication Link Budgets We will use White Sands receiving antenna (WS-1) on Earth – 18m diameter antenna L-2 relay satellite modeled as TDRS Capsule high gain antenna will be outfitted for Ku, Ka, and S band transmitters – 0.5m diameter parabolic dish – 60.5 W max power consumption

Link Budget: Ku Band Directly to Earth dB Speed of lightm/secc3.00E FrequencyHzf1.20E Wavelengthml Diameter of Transmitting Antennamd(t) Area of Transmitting Antennam^2A(t) Efficiency of Transmitting Antennah(t) Transmitter GainG(t)2.17E Transmitter PowerWP EIRPW 3.26E slant rangemD4.06E Power flux densityW/m^2F1.58E Diameter of Receiving Antennamd(r ) Area of Receiving Antennam^2A(r ) Efficiency of Receiving Antennah(r ) Receiver GainG(r )2.81E Carrier Power ReceivedWC2.21E Receiver System Noise TempdegKT(s) Boltzmann ConstantJ/degKk1.38E Noise Spectral DensityJ/degKN(o)4.14E Figure of Merit Gr/TsGr/Ts9.38E Free Space LossL(fs)4.15E Total System LossL(ts) Receiver C/No AvailableHzC/No(rcv)1.93E Bit Error RateBER1.00E C/No RequiredHzC/No(req)9.40E Data Ratebits/secR(b)1.00E Eb/No ReceivedEb/No(rcv) Eb/No RequiredEb/No(req) Link Margin

Link Budget: S-Band Directly to Earth dB Speed of lightm/secc3.00E FrequencyHzf2.50E Wavelengthml Diameter of Transmitting Antennamd(t) Area of Transmitting Antennam^2A(t) Efficiency of Transmitting Antennah(t) Transmitter GainG(t)9.42E Transmitter PowerWP EIRPW 4.71E slant rangemD4.05E Power flux densityW/m^2F2.29E Diameter of Receiving Antennamd(r ) Area of Receiving Antennam^2A(r ) Efficiency of Receiving Antennah(r ) Receiver GainG(r )1.22E Carrier Power ReceivedWC3.20E Receiver System Noise TempdegKT(s) Boltzmann ConstantJ/degKk1.38E Noise Spectral DensityJ/degKN(o)4.14E Figure of Merit Gr/TsGr/Ts4.07E Free Space LossL(fs)1.80E Total System LossL(ts) Receiver C/No AvailableHzC/No(rcv)2.81E Bit Error RateBER1.00E C/No RequiredHzC/No(req)1.88E Data Ratebits/secR(b)2.00E Eb/No ReceivedEb/No(rcv) Eb/No RequiredEb/No(req) Link Margin

Link Budget: Ka-Band to L-2 Relay dB Speed of lightm/secc3.00E FrequencyHzf3.20E Wavelengthm Diameter of Transmitting Antennamd(t) Area of Transmitting Antennam^2A(t) Efficiency of Transmitting Antenna  (t) Transmitter GainG(t)1.54E Transmitter PowerWP EIRPW 2.32E slant rangemD6.50E Power flux densityW/m^2  4.36E Diameter of Receiving Antennamd(r ) Area of Receiving Antennam^2A(r ) Efficiency of Receiving Antenna  (r ) Receiver GainG(r )1.48E Carrier Power ReceivedWC4.52E Receiver System Noise TempdegKT(s) Boltzmann ConstantJ/degKk1.38E Noise Spectral DensityJ/degKN(o)1.38E Figure of Merit Gr/TsGr/Ts1.48E Free Space LossL(fs)7.59E Total System LossL(ts) Receiver C/No AvailableHzC/No(rcv)1.19E Bit Error RateBER1.00E C/No RequiredHzC/No(req)9.40E Data Ratebits/secR(b)1.00E Eb/No ReceivedEb/No(rcv) Eb/No RequiredEb/No(req) Link Margin

Link Budget: Ku-Band L-2 Relay to Earth dB Speed of lightm/secc3.00E FrequencyHzf1.20E Wavelengthm Diameter of Transmitting Antennamd(t) Area of Transmitting Antennam^2A(t) Efficiency of Transmitting Antenna  (t) Transmitter GainG(t)2.09E Transmitter PowerWP EIRPW 3.13E slant rangemD4.06E Power flux densityW/m^2  1.51E Diameter of Receiving Antennamd(r ) Area of Receiving Antennam^2A(r ) Efficiency of Receiving Antenna  (r ) Receiver GainG(r )2.81E Carrier Power ReceivedWC2.12E Receiver System Noise TempdegKT(s) Boltzmann ConstantJ/degKk1.38E Noise Spectral DensityJ/degKN(o)1.38E Figure of Merit Gr/TsGr/Ts2.81E Free Space LossL(fs)4.15E Total System LossL(ts) Receiver C/No AvailableHzC/No(rcv)5.57E Bit Error RateBER1.00E C/No RequiredHzC/No(req)2.35E Data Ratebits/secR(b)2.50E Eb/No ReceivedEb/No(rcv) Eb/No RequiredEb/No(req) Link Margin

Link Budget: UHF Omni to EVA suits dB Speed of lightm/secc3.00E FrequencyHzf9.00E Wavelengthml Diameter of Transmitting Antennamd(t) Area of Transmitting Antennam^2A(t) Efficiency of Transmitting Antennah(t) Transmitter GainG(t)6.25E Transmitter PowerWP EIRPW 3.13E slant rangemD2.00E Power flux densityW/m^2F6.22E Diameter of Receiving Antennamd(r ) Area of Receiving Antennam^2A(r ) Efficiency of Receiving Antennah(r ) Receiver GainG(r )6.25E Carrier Power ReceivedWC3.44E Receiver System Noise TempdegKT(s) Boltzmann ConstantJ/degKk1.38E Noise Spectral DensityJ/degKN(o)4.14E Figure of Merit Gr/TsGr/Ts2.08E Free Space LossL(fs)5.68E Total System LossL(ts) Receiver C/No AvailableHzC/No(rcv)3.01E Bit Error RateBER1.00E C/No RequiredHzC/No(req)1.41E Data Ratebits/secR(b)1.50E Eb/No ReceivedEb/No(rcv) Eb/No RequiredEb/No(req) Link Margin

UHF Omni to EVA suits Antenna diameter of 11cm easily fits on suits Transportable power of 0.5w is attainable Slant range of 20km will more then double max distance transverse by Apollo Data Rate of 1.5 Mbps will transmit suit video and all other communications