team2_incep_presentation

Interplanetary Comet Exploration Probe (INCEP)

A flyby mission of the comet 209P/LINEAR

Tanish HimaniMark Mote

Matthew OwczarskiSwapnil Pujari

Advisors:Dr. Brian Gunter

Byron DavisMichael Herman

Motivation/Background

Overview

Flight System/Components

Technical Resource Budgets

Summary

Motivation

2


Overview



Summary

209P/LINEAR Specifications

3Position 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 degPeriod 5.09 yr

Eccentricity 0.67258

Perihelion Distance 0.9695 AU


Overview



Summary

Mission Objectives

4

Mission StatementProgram 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 ObjectivesMO-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-3.1Within 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


Overview



Summary

5

Mission Overview

X-band transmission.

7


Overview



Summary

6

Program SchedulePhase 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 PhaseYear 1 Year 2

Q4Year 3 Year 4 Year 5

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3


Overview



Summary

7

Trajectory


Overview



Summary

8

Trajectory


Overview



Summary

9

Trajectory


Overview



Summary

10

INCEP Breakdown

Propulsion

StructureEPS

C&DH

Payload

EPS

Telecom

Payload

ADCSTelecom

Propulsion

Thermal & Radiation


Overview



Summary

11

Component ListSubsystem Component Name QuantityStructures ISIS 6-Unit CubeSat structure 1

EPS

Clyde Space 3G FLEX EPS 1CS 30 Whr Battery 1

CS Deployable Double Sided 6U Panels 4CS 6U Body FixedSolar Panels 1

Thermal & Shielding MLI Blankets 1

Propulsion

Busek 3cm RF Ion Thruster 1Electric Propellant 1Liquid Propellant 1

MPS-120 1ADCS BCT-XACT Module 1

TelecomIRIS X-Band Transponder 1

AntDevCo X-Band Patch Antennas 1C&DH Tyvak Intrepid System Board Computer 1

PayloadArgus 1000 SK Spectrometer 1

NanoCam C1U Camera (50 mm lens) 1

Radiation Shielding Lead radiation shielding 1


Overview



Summary

12

PropulsionPropulsion

Type Component Name Application Delta V (km/s) Margin Total Delta V (km/s)

Electric Propulsion

Busek 3cm RF Ion Thruster BIT-3

Transit2.02998 25% 2.537475

Station Keeping

Liquid Propulsion

Aerojet MPS-120 CHAMPS

Science Maneuvers 0.017 15% 0.01955

Emergency Thrust 0.034 15% 0.0391Desaturation 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) 319.7606526Burn Time Margin

(%) 3.102832556


Overview



Summary

13

Science Instruments

Mission Statement Science Goals Science

RequirementsMeasurement 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


Overview



Summary

14

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


Overview



Summary

15

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


Overview



Summary

16

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 1CS 30 Whr Battery 1CS Deployable Double Sided 6U Panels 4

CS 6U Body FixedSolar Panels 1

Power Generated (Worst-case):- 5° Angle -> 86 W- 45° Angle -> 61 W


Overview



Summary

17

Mass Budget and TRLSubsystem Component Name Quantity Mass (g) Contingency Total Mass (g) TRLStructures ISIS 6-Unit CubeSat structure 1 1100 10% 1210 7

EPS

Clyde Space 3G FLEX EPS 1 150 10% 165 9CS 30 Whr Battery 1 260 10% 286 9CS Deployable Double Sided 6U Panels 4 290 20% 1392 9CS 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 5Electric Propellant 1 1184 20% 1420.8 7Liquid Propellant 1 300 10% 330 7MPS-120 1 1300 10% 1430 6

ADCS BCT-XACT Module 1 850 10% 935 6

TelecomIRIS X-Band Transponder 1 400 10% 440 6AntDevCo X-Band Patch Antennas 1 300 10% 330 7

C&DH Tyvak Intrepid System Board Computer 1 55 10% 60.5 8

PayloadArgus 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 10727Total Wet Mass 12147.8

Total Allowed Mass 14000Margin 13%


Overview



Summary

18

Power BudgetSubsystem Component

Name Quantity Continegency (%) Safe Mode Duty Cycle

Maneuvering Duty Cycle

Science Duty Cycle

Transmission Duty Cycle

Safe Mode Power Draw

(mW)

Maneuvering Power Draw

(mW)

Science Power Draw

(mW)

Transmission 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

Thruster100.00% 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

Antennas100.00% 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

Spectrometer

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%


Overview



Summary

19

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 Timesec 58863.58 153.92

hrs 16.35 0.04


Overview



Summary

20

Thermal CalculationsComponent 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


Overview



Summary

21

Cost EstimateItem 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

year4 $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


Overview



Summary

22

Cost Estimate

70%

4%

2%

2%

9%

11%1%

INCEP Cost Breakdown

CubeSat ComponentsDSN Data TransmissionDSN Station-KeepingPrincipal InvestigatorProject ManagersIntegration, Assembly, and TestingTelescope Rental


Overview



Summary

23

Risk Management

RN Risk Mitigation

1 Trajectory Deviation

High precision navigation determination

High precision comet tracking

Secondary Thruster2 Camera System Failure Approach images taken

3 Radiation Damage Radiation ShieldingComponent 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


Overview



Summary

24

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

Questions?

Backup Slides


Overview



Summary

27

Link BudgetComet 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 7.15Frequency 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 0Transmitter Antenna Gain EIRP dBW 16.5 67

Equivalent Isotropic Radiated Power S m 26.5 110.0103Propagation Path Length c m/s 99607000000 99607000000

Speed of Light Ls dB 300000000 300000000Free Space Path Loss La dB -270.9446962 -269.4936829

Propagation and Polarization Loss Lpr dB -1 -2Receive Antenna Pointing Loss Gr dBi -0.2 -2

Receive Antenna Gain Ts K 74.4 16System Noise Temperature Ts dBK 20.6 250System Noise Temperature R bps 13.1386722 23.97940009

Data Rate 13264.56928 259867.3358Symbols per Byte Eb/No dB 2 2

Eb/No C/No dB-Hz 6 6Carrier-to-Noise Density Ratio Req Eb/No dB 44.21663157 57.13721698

Required Eb/No dB 2 2Implementation Loss (estimate) dB -1 -1

Margin dB 3 3


Overview



Summary

28

Work Breakdown Schedule


Overview



Summary

29

Descope Options

Option ImpactMass Saved

(kg)Cost Saved

($K)Volume

Saved (U)Power Saved

(W)Switch

Battery from 30 W-hr to

10 W-hrMinimal 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

team2_incep_presentation

Documents