The document outlines a proposed mission, called Program INCEP, to investigate the composition and structure of comet 209P/LINEAR using a 6U cubesat. The mission objectives include performing a flyby of the comet with optical and infrared imaging and spectroscopy to analyze the comet's composition and estimate its mass. The cubesat design includes an ion thruster, cameras, spectrometers, an X-band radio for communications, and deployable solar panels. Trajectory analysis shows the cubesat can perform a flyby with the required instruments using its propulsion budget.

1. Tanish Himani
Mark Mote
Matthew Owczarski
Swapnil Pujari
Advisors:
Dr. Brian Gunter
Byron Davis
Michael Herman

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Motivation
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209P/LINEAR Specifications
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Position of 209P/LINEAR on July 7th 2019
• The Jupiter Family Comet 209P/LINEAR was discovered in by the Lincoln Near Earth
Asteroid research project in May 2004
• In May 2014 the comet made a close pass of 8.3 million km
• Monitoring of the comet revealed the lowest perihelion dust production of any
comet on record, indicating that the comet is currently transitioning to an extinct
phase
• In July of 2019 the comet once again crosses the ecliptic at a distance of ~1AU
presenting the opportunity for a flyby at a relatively low Δv
Dimensions of Nucleus
2.4 x 3 km
(third dimension unknown)
Rotation Rate est. 11, 22 hrs
Inclination 21.243 deg
Period 5.09 yr
Eccentricity 0.67258
Perihelion Distance 0.9695 AU

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Mission Objectives
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Mission Statement
Program INCEP will investigate the composition and structure of comet 209P/Linear through the use of optical imaging
and infrared spectroscopy. The data will be analyzed in order to develop a better understanding of how presolar
processes helped to shape bodies in the early solar system.
MO Mission Objectives
MO-1 The cubesat shall perform a flyby maneuver with comet 209P/LINEAR.
MO-2 The cubesat shall acquire optical and spectroscopic imaging on the comet during flyby.
MO-3
The gravitational disturbances on the cubesat’s orbit shall be calculated to estimate the mass of comet
209P/Linear
MO-4
The cubesat shall utilize onboard processing and telecommunications hardware to relay this data to a
ground station on Earth
MDC Mission Success Criteria Source Minimum Full
MSC-1
The cubesat shall have a flyby distance of 500 km with the comet
209P/LINEAR
MO-1 
MSC-1.1
The cubesat shall have a flyby distance of 250 km with the comet
209P/LINEAR
MO-1 
MSC-2
The spectrometer payload shall be pointed to within 0.15 degrees of
the comet during flyby
MO-2 
MSC-3
The spectrometer payload shall obtain detect chemical species on the
surface of the nucleus of 209P/LINEAR
MO-2 
MSC-3.1
Within the specified spectroscopy range, data collected must be
absorption and emission spectra of H20 ice at 1800 and 1380 nm
wavelengths
MO-2

MSC-4
The camera payload must capture one image every minute during the
total flyby period.
MO-2 
MSC-5 No more than a 10% data loss shall occur in the received signal MO-4 

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Mission Overview
X-band transmission.
7

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Program Schedule
Phase 1: Concept Development (10%
Margin)
Preliminary Studies on NASA Science
Goals
Determine Science Goal of Project
Create Mission Statement
Determine Mission Requirements
Phase 2: Preliminary Design (20%
Margin)
Develop Budget and Management Plan
Perform Architecture Trade Studies
Develop System Level Requirements
Phase 3: Final Design (15% Margin)
Choose Final System Architecture
Choose Final Sub-System Architectures
Purchase S/C Bus Components and
Payload
Phase 4: System Assembly,
Integration & Testing (25% Margin)
Software Development
Software and Hardware Integration
Integration Testing
Phase 5: Launch (50% Margin)
Prepare for Launch Opportunity
Integration Into Launch Vehicle and
Launch
Phase 6: Operations and Sustainment
(5%)
Perform Health Checks
Perform delta-V maneuver (Propulsion
Mode)
Enter Science Mode
Transmit Science Data to Ground
Station
Phase 7: Closeout (50%)
Storage and Analysis of All Data
Project Phase
Year 1 Year 2
Q4
Year 3 Year 4 Year 5
Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3

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Trajectory

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Trajectory

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Trajectory

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INCEP Breakdown
Propulsion
Structure
EPS
C&DH
Payload
EPS
Telecom
Payload
ADCS
Telecom
Propulsion
Thermal &
Radiation

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Component List
Subsystem Component Name Quantity
Structures ISIS 6-Unit CubeSat structure 1
EPS
Clyde Space 3G FLEX EPS 1
CS 30 Whr Battery 1
CS Deployable Double Sided 6U Panels 4
CS 6U Body FixedSolar Panels 1
Thermal & Shielding MLI Blankets 1
Propulsion
Busek 3cm RF Ion Thruster 1
Electric Propellant 1
Liquid Propellant 1
MPS-120 1
ADCS BCT-XACT Module 1
Telecom
IRIS X-Band Transponder 1
AntDevCo X-Band Patch Antennas 1
C&DH Tyvak Intrepid System Board Computer 1
Payload
Argus 1000 SK Spectrometer 1
NanoCam C1U Camera (50 mm lens) 1
Radiation Shielding Lead radiation shielding 1

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Propulsion
Propulsion
Type
Component Name Application Delta V (km/s) Margin
Total Delta V
(km/s)
Electric
Propulsion
Busek 3cm RF Ion
Thruster BIT-3
Transit
2.02998 25% 2.537475
Station Keeping
Liquid
Propulsion
Aerojet MPS-120
CHAMPS
Science Maneuvers 0.017 15% 0.01955
Emergency Thrust 0.034 15% 0.0391
Desaturation of
reaction wheels
0.017 15% 0.01955
Total Delta V
Required - Electric
(km/s)
2.537475
Total Delta V
Required - Liquid
(km/s)
0.0782
Total Mass of
Propellant (kg)
1.509315746
Burn time (days) 319.7606526
Burn Time Margin
(%)
3.102832556

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Science Instruments
Mission
Statement
Science Goals
Science
Requirements
Measurement
Requirements
Instrument
Functional
Requirements
"...develop a
better
understanding of
how presolar
processes helped
to shape bodies in
the early solar
system"
Understand
cometary lifecycle
through the study of
a “dying” comet
Precise determination
of rotation rate
Ability to acquire
images at at least twice
the minimum estimated
rotation rate of
209P/LINEAR
Minimum image
acquisition rate of 0.18
observations per hour
Characterization of
surface topology
through identification
of craters, gas jets, and
other natural
morphological features
Ability to acquire high
resolution images of the
comets surface
Minimum Spatial
Resolution better than
20 m/pixel at chosen
flyby distance
Improve
understanding of
volatile
composition of
Jupiter family
comets
Determination of ice
grain presence in the
near nucleus coma.
Ability to detect spectral
identification bands of
water ice
Spectrographic
detection of 1800 and
1380 nm wavelengths
Determination of ice
presence on surface
Spectrographic
resolution of less than
13.8 nm

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Science Instruments
Argus 1000 SK (Infrared Spectrometer)
• Operation Band: 1000-2400 nm
– Capable of detection of H20, C2, N2+, NH3, CH4…
• Spectral Resolution: 6 nm
• Mass: 0.23 kg
• Dimensions: 45 x 50 x 80 mm
NanoCam C1U 50mm (Camera System)
• Operation Band: 400-1000 nm
• Image acquisition rate: 37.9 /hr
• Spatial Resolution: 14.1 m/pixel
• 50 mm lens
• 225 km flyby distance
• Mass: 0.17 kg
• Dimensions: 45 x 50 x 80 mm

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ADCS and Telecommunications
IRIS Transponder
(NASA JPL):
– X-Band (Rx/Tx)
– BPSK Modulation
AntDevCo X-Band
Patch Antenna
– 16 dB Gain
– DSN Compatible
BCT XACT
• Slew rate: >=10 deg/sec
– Maximum required angular
rate: 4.2 deg/s
DSN

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Power
Clyde Space FLEX EPS
Clyde Space 30 Whr Battery
Clyde Space 6U Double
Deployed 2-Sided Solar Panels
- 18 cells per side
- 90 cells for 5 panels (single
side)
EPS
Clyde Space 3G FLEX EPS 1
CS 30 Whr Battery 1
CS Deployable Double Sided
6U Panels
4
CS 6U Body FixedSolar
Panels
1
Power Generated (Worst-case):
- 5° Angle -> 86 W
- 45° Angle -> 61 W

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Mass Budget and TRL
Subsystem Component Name Quantity Mass (g) Contingency Total Mass (g) TRL
Structures ISIS 6-Unit CubeSat structure 1 1100 10% 1210 7
EPS
Clyde Space 3G FLEX EPS 1 150 10% 165 9
CS 30 Whr Battery 1 260 10% 286 9
CS Deployable Double Sided 6U Panels 4 290 20% 1392 9
CS 6U Body FixedSolar Panels 1 290 10% 319 9
Thermal & Shielding MLI Blankets 1 100 20% 120 9
Propulsion
Busek 3cm RF Ion Thruster 1 1550 15% 1782.5 5
Electric Propellant 1 1184 20% 1420.8 7
Liquid Propellant 1 300 10% 330 7
MPS-120 1 1300 10% 1430 6
ADCS BCT-XACT Module 1 850 10% 935 6
Telecom
IRIS X-Band Transponder 1 400 10% 440 6
AntDevCo X-Band Patch Antennas 1 300 10% 330 7
C&DH Tyvak Intrepid System Board Computer 1 55 10% 60.5 8
Payload
Argus 1000 SK Spectrometer
1 230 10% 253 9
NanoCam C1U Camera (50 mm lens) 1 170 20% 204 6
Radiation Shielding
Lead radiation shielding
1 1400 5% 1470 9
Total Dry Mass 10727
Total Wet Mass 12147.8
Total Allowed Mass 14000
Margin 13%

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Power Budget
Subsystem
Component
Name
Quantity Continegency (%)
Safe Mode
Duty Cycle
Maneuverin
g Duty Cycle
Science
Duty Cycle
Transmission
Duty Cycle
Safe Mode
Power Draw
(mW)
Maneuvering
Power Draw
(mW)
Science
Power Draw
(mW)
Transmissio
n Power
Draw (mW)
EPS
Clyde Space
3G FLEX EPS
100.00% 5.00% 1 1 1 1 157.5 157.5 157.5 157.5
CS 30 Whr
Battery
100.00% 5.00% 1 1 1 1 52.5 52.5 52.5 52.5
Propulsion
BUSEK 3m
RF Ion
Thruster
100.00% 15.00% 0 1 0 0 0 69000 0 0
MPS-120 100.00% 15.00% 0 0.1 0.25 0.1 0 287.5 718.75 287.5
ADCS
BCT-XACT
Module
100.00% 10.00% 0.4 1 1 0.7 1245.2 3113 3113 2179.1
Telecom
IRIS X-Band
Transponde
r (RX)
100.00% 10.00% 0.2 1 1 1 1408 7040 7040 7040
IRIS X-Band
Transponde
r (TX)
100.00% 10.00% 0.05 0.1 1 1 349.25 698.5 6985 6985
AntDevCo
X-Band
Patch
Antennas
100.00% 10.00% 0.05 0.1 0.5 1 1375 2750 13750 27500
C&DH
Tyvak
Computer
100.00% 10.00% 1 1 1 1 550 550 550 550
Payload
Argus 1000
Infrared
Spectromet
er
100.00% 15.00% 0 0 1 0 0 0 2525.4 0
NanoCam
C1U
100.00% 15.00% 0 0 1 0 0 0 741.75 0
Total (W) 5.13745 83.649 35.6339 44.7516
Margin 1586.22% 3.56% 72.56% 37.40%

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Link and Data Volume Budget
Data Volume Analysis Units Downlink Uplink
Data Rate kbps 13.26 259.87
Data TX Requirement Mbyte 97.60 5.00
Transmission Time
sec 58863.58 153.92
hrs 16.35 0.04

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Thermal Calculations
Component Energy (W)
Solar Input 1360 (1/m2
)
Solar Input (30% Area
Incident)
109.2819927
Solar Input (40% Area
Incident)
145.6579535
INCEP during propulsion 83.649
INCEP during safe mode 5.13745
INCEP during trans
mode
44.7516
Qin,total (prop) 170.1309927
Qin,total (safe) 114.4194427
Qin,total (trans) 154.0335927
Mode Temperature (C)
Propulsion 20.28514967
Safe -7.419603697
Transmission 13.0832871

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Cost Estimate
Item Quantity Cost per unit Contingency Total cost after margin
CubeSat Components
(contingency accounted for)
1 $1,499,400.66 -- $1,499,400.66
DSN data transmission after
flyby (using DSN 70m
stations)
1 $82,958.40 15% $95,402.16
DSN station-keeping (weekly
updates at 1 hour each,
using 34m HSB station)
48 $845.60 15% $46,677.12
One Principal Investigator
(Assistant Professor) - one
year
4 $10,000.00 25% $50,000.00
Two Project Managers (Grad
Students) - one year
4 $40,000.00 25% $200,000.00
Spacecraft Integration,
Assembly, and Testing
1 $185,925.68 30% $241,703.39
Online telescope rental (180
hours per year)
4 $4,500.00 20% $21,600.00
Total Mission
Cost
$2,154,783.33

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Cost Estimate
70%
5%
2%
2%
9%
11%
1%
INCEP Cost Breakdown
CubeSat Components
DSN Data Transmission
DSN Station-Keeping
Principal Investigator
Project Managers
Integration, Assembly, and
Testing
Telescope Rental

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Risk Management
RN Risk Mitigation
1 Trajectory Deviation
High precision navigation determination
High precision comet tracking
Secondary Thruster
2 Camera System Failure Approach images taken
3 Radiation Damage
Radiation Shielding
Component Placement
4 Cometary Debris Damage Flyby Location
5 Propulsion Unit Failure (TRL5) N/A
6 Reaction Wheel Failure Liquid Thruster
5
4
3 6 3,4
2 1 2 5
1
1 2 3 4 5
Impact
Likelihood
5
4 6 3,4
3 1 2
2 5
1
1 2 3 4 5
Likelihood
Impact

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Summary
• INCEP plans to study 209P/LINEAR to better
understand how pre-solar processes helped to
shape bodies in the early solar system
• High scientific value
• Cost is far under budget of similar missions and
NASA request for proposal
• High margins for all phases and components of
the mission

25. Questions?

26. Backup Slides

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Link Budget
Comet Telecom Link Budget Symbol: Units: Cubesat -> Earth (Downlink) Earth -> Cubesat (Uplink)
Item: f GHz Telemetry and Data: Telemetry and Data:
Frequency f Hz 8.45 7.15
Frequency P Watts 8450000000 7150000000
Transmitter Power (RF Output Transmit
Power)
P dBW 10 20000
Transmitter Power (RF Output Transmit
Power)
Ll dB 10 43.01029996
Transmitter Line Loss Gt dBi 0 0
Transmitter Antenna Gain EIRP dBW 16.5 67
Equivalent Isotropic Radiated Power S m 26.5 110.0103
Propagation Path Length c m/s 99607000000 99607000000
Speed of Light Ls dB 300000000 300000000
Free Space Path Loss La dB -270.9446962 -269.4936829
Propagation and Polarization Loss Lpr dB -1 -2
Receive Antenna Pointing Loss Gr dBi -0.2 -2
Receive Antenna Gain Ts K 74.4 16
System Noise Temperature Ts dBK 20.6 250
System Noise Temperature R bps 13.1386722 23.97940009
Data Rate 13264.56928 259867.3358
Symbols per Byte Eb/No dB 2 2
Eb/No C/No dB-Hz 6 6
Carrier-to-Noise Density Ratio Req Eb/No dB 44.21663157 57.13721698
Required Eb/No dB 2 2
Implementation Loss (estimate) dB -1 -1
Margin dB 3 3

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Work Breakdown Schedule

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Descope Options
Option Impact
Mass Saved
(kg)
Cost Saved
($K)
Volume
Saved (U)
Power Saved
(W)
Switch
Battery from
30 W-hr to
10 W-hr
Minimal 0.1 0.5 0 0.01
Removal of
Camera
Payload
Moderate 0.204 13.57 0.9 0.66
Removal of
MPS-120
(Liquid
Propulsion)
Major 1.76 150 1 4