Chris Flood
Matt Marcus
Kiran Patel
Tim Russell

• 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

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

• 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

• 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

• 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

• 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

• 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

• 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

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

• 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
Speed of light
Frequency
Wavelength
Diameter of Transmitting Antenna
Area of Transmitting Antenna
Efficiency of Transmitting Antenna
Transmitter Gain
Transmitter Power
EIRP slant range
Power flux density
Diameter of Receiving Antenna
Area of Receiving Antenna
Efficiency of Receiving Antenna
Receiver Gain
Carrier Power Received
Receiver System Noise Temp
Boltzmann Constant
Noise Spectral Density
Figure of Merit Gr/Ts
Free Space Loss
Total System Loss
Receiver C/No Available
Bit Error Rate
C/No Required
Data Rate
Eb/No Received
Eb/No Required
Link Margin m/sec
Hz m m m^2
W
W m
W/m^2 m m^2
W degK
J/degK
J/degK
Hz
Hz bits/sec
D
F d(r )
A(r ) h(r )
G(r )
C
T(s) k
N(o) f c l d(t)
A(t) h(t)
G(t)
P
EIRP
Gr/Ts
L(fs)
L(ts)
C/No(rcv)
BER
C/No(req)
R(b)
Eb/No(rcv)
Eb/No(req)
3.00E+08
1.20E+10
0.0250
0.50
0.20
0.55
2.17E+03
15.00
3.26E+04
4.06E+08
1.58E-14
18.00
254.47
0.55
2.81E+06
2.21E-12
300.00
1.38E-23
4.14E-21
9.38E+03
4.15E+22
2.75
1.93E+08
1.00E-05
9.40E+07
1.00E+07
19.35
9.40
2.05839
86.08
-138.02
12.55
24.06
-2.60
64.49
-116.56
24.77
-228.60
-203.83
dB
84.77
100.79
-16.02
-3.01
-7.07
-2.60
33.37
11.76
45.13
39.72
226.19
4.40
82.87
-50.00
79.73
70.00
12.87
9.73
3.14

Link Budget: S-Band Directly to Earth
Speed of light
Frequency
Wavelength m/sec
Hz m
Diameter of Transmitting
Antenna m
Area of Transmitting Antenna m^2
Efficiency of Transmitting Antenna
Transmitter Gain
Transmitter Power
EIRP slant range
W
W m
Power flux density W/m^2
Diameter of Receiving Antennam
Area of Receiving Antenna m^2
Efficiency of Receiving Antenna
Receiver Gain
Carrier Power Received W
Receiver System Noise Temp degK
Boltzmann Constant
Noise Spectral Density
Figure of Merit Gr/Ts
Free Space Loss
Total System Loss
Receiver C/No Available
Bit Error Rate
C/No Required
Data Rate
Eb/No Received
Eb/No Required
Link Margin
J/degK
J/degK
Hz
Hz bits/sec l f c d(t)
A(t) h(t)
G(t)
P
EIRP
D
F d(r )
A(r ) h(r )
G(r )
C
T(s) k
N(o)
Gr/Ts
L(fs)
L(ts)
C/No(rcv)
BER
C/No(req)
R(b)
Eb/No(rcv)
Eb/No(req)
3.00E+08
2.50E+09
0.1200
0.50
0.20
0.55
9.42E+01
5.00
4.71E+02
4.05E+08
2.29E-16
18.00
254.47
0.55
1.22E+05
3.20E-14
300.00
1.38E-23
4.14E-21
4.07E+02
1.80E+21
2.75
2.81E+06
1.00E-05
1.88E+06
2.00E+05
14.03
9.40
1.49268
dB
84.77
93.98
-9.21
-3.01
-7.07
-2.60
19.74
6.99
26.73
86.07
-156.41
12.55
24.06
-2.60
50.87
-134.95
24.77
-228.60
-203.83
26.10
212.55
4.40
64.48
-50.00
62.74
53.01
11.47
9.73
1.74

Link Budget: Ka-Band to L-2 Relay
Speed of light
Frequency
Wavelength m/sec
Hz m
Diameter of Transmitting
Antenna m
Area of Transmitting Antenna m^2
Efficiency of Transmitting Antenna
Transmitter Gain
Transmitter Power
EIRP slant range
W
W m
Power flux density W/m^2
Diameter of Receiving Antennam
Area of Receiving Antenna m^2
Efficiency of Receiving Antenna
Receiver Gain
Carrier Power Received W
Receiver System Noise Temp degK
J/degK
J/degK
Boltzmann Constant
Noise Spectral Density
Figure of Merit Gr/Ts
Free Space Loss
Total System Loss
Receiver C/No Available
Bit Error Rate
C/No Required
Data Rate
Eb/No Received
Eb/No Required
Link Margin
Hz
Hz bits/sec c f l d(t)
A(t) h
(t)
G(t)
P
EIRP
D
F d(r )
A(r ) h
(r )
G(r )
C
T(s) k
N(o)
Gr/Ts
L(fs)
L(ts)
C/No(rcv)
BER
C/No(req)
R(b)
Eb/No(rcv)
Eb/No(req)
3.00E+08
3.20E+10
0.0094
0.50
0.20
0.55
1.54E+04
15.00
2.32E+05
6.50E+07
4.36E-12
4.90
18.86
0.55
1.48E+06
4.52E-11
100.00
1.38E-23
1.38E-21
1.48E+04
7.59E+21
2.75
1.19E+10
1.00E-05
9.40E+09
1.00E+09
11.90
9.40
1.26645
dB
84.77
105.05
-20.28
-3.01
-7.07
-2.60
41.89
11.76
53.65
78.13
-113.60
6.90
12.75
-2.60
61.71
-103.44
20.00
-228.60
-208.60
41.71
218.80
4.40
100.76
-50.00
99.73
90.00
10.76
9.73
1.03

Link Budget: Ku-Band L-2 Relay to
Earth
Speed of light
Frequency
Wavelength
Diameter of Transmitting Antenna
Area of Transmitting Antenna
Efficiency of Transmitting Antenna
Transmitter Gain
Transmitter Power
EIRP slant range
Power flux density
Diameter of Receiving Antenna
Area of Receiving Antenna
Efficiency of Receiving Antenna
Receiver Gain
Carrier Power Received
Receiver System Noise Temp
Boltzmann Constant
Noise Spectral Density
Figure of Merit Gr/Ts
Free Space Loss
Total System Loss
Receiver C/No Available
Bit Error Rate
C/No Required
Data Rate
Eb/No Received
Eb/No Required
Link Margin m/sec
Hz m m m^2
W
W m
W/m^2 m m^2
W degK
J/degK
J/degK
Hz
Hz bits/sec f c l d(t)
A(t) h
(t)
G(t)
P
EIRP
D
F d(r )
A(r ) h
(r )
G(r )
C
T(s) k
N(o)
Gr/Ts
L(fs)
L(ts)
C/No(rcv)
BER
C/No(req)
R(b)
Eb/No(rcv)
Eb/No(req)
3.00E+08
1.20E+10
0.0250
4.90
18.86
0.55
2.09E+05
15.00
3.13E+06
4.06E+08
1.51E-12
18.00
254.47
0.55
2.81E+06
2.12E-10
100.00
1.38E-23
1.38E-21
2.81E+04
4.15E+22
2.75
5.57E+10
1.00E-05
2.35E+10
2.50E+09
22.30
9.40
2.37225
dB
84.77
100.79
-16.02
6.90
12.75
-2.60
53.19
11.76
64.95
86.08
-118.20
12.55
24.06
-2.60
64.49
-96.74
20.00
-228.60
-208.60
44.49
226.19
4.40
107.46
-50.00
103.71
93.98
13.48
9.73
3.75

Link Budget: UHF Omni to EVA suits
Speed of light
Frequency
Wavelength
Diameter of Transmitting Antenna
Area of Transmitting Antenna
Efficiency of Transmitting Antenna
Transmitter Gain
Transmitter Power
EIRP slant range
Power flux density
Diameter of Receiving Antenna
Area of Receiving Antenna
Efficiency of Receiving Antenna
Receiver Gain
Carrier Power Received
Receiver System Noise Temp
Boltzmann Constant
Noise Spectral Density
Figure of Merit Gr/Ts
Free Space Loss
Total System Loss
Receiver C/No Available
Bit Error Rate
C/No Required
Data Rate
Eb/No Received
Eb/No Required
Link Margin m/sec
Hz m m m^2
W
W m
W/m^2 m m^2
W degK
J/degK
J/degK
Hz
Hz bits/sec f c l d(t)
A(t)
C
T(s) k
N(o)
Gr/Ts
L(fs)
L(ts) h(t)
G(t)
P
EIRP
D
F d(r )
A(r ) h(r )
G(r )
C/No(rcv)
BER
C/No(req)
R(b)
Eb/No(rcv)
Eb/No(req)
3.00E+08
9.00E+08
0.3333
0.11
0.01
0.63
6.25E-01
0.50
3.13E-01
2.00E+04
6.22E-11
0.11
0.01
0.63
6.25E-01
3.44E-13
300.00
1.38E-23
4.14E-21
2.08E-03
5.68E+11
2.75
3.01E+07
1.00E-05
1.41E+07
1.50E+06
20.09
9.40
2.13710
dB
84.77
89.54
-4.77
-9.74
-20.53
-2.04
-2.04
-3.01
-5.05
43.01
-102.06
-9.74
-20.53
-2.04
-2.04
-124.64
24.77
-228.60
-203.83
-26.81
117.55
4.40
74.79
-50.00
71.49
61.76
13.03
9.73
3.30

• 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