Extremely Low Earth Orbit (ELEO-Sat) Taylor University

AFOSR University Nanosat-8 Program (UNP)

System Concept Review (SCR) 03/12/2013

1 (Thanks to AFSOR and UNP for supporting our Taylor University ELEO program and student learning.)

(Two members absent)

Principle Investigator/University: Dr. Hank Voss, hnvoss@taylor.edu, 765 618 3813 Taylor University, Upland, IN

Co-Investigator: Professor Jeff Dailey, jfdailey@taylor.edu, 260 241 0409

Student Team Leaders: Student Team Leader and SSD: Dan McClure Mechanical Lead: Paul Kuehl System Processors: David Lew Thermal, Attitude, RPI analyzer: Adam Kilmer Communication and Power: Paul Kuehl and Raquel Graves Public Outreach and K-12: Kate Yoshino

Mission Description: ELEO-SAT BUS Key Attributes:

Aerodynamic, high Ballistic Coefficient, Unit Mech. Structure

Pioneer CubeSat Globalstar Sat-sat data link (simplex/duplex)

New carbon fiber 2.5 m boom with bidirectional feed motor

Motor controlled (Pointing) 1m unfolding GaAs solar array

Attitude:GPS, aerodynamic, momentum wheel, 3-A magtorque

Orbit Interest: Release in orbit below 400km, Inc.>50deg,

ELEO-SAT Payload Key Attributes Five solid state energetic particle spectrometers (30keV-2MeV) VLF radio receiver with remote boom amplifiers (200-20kHz) Dual x-z axis DC AC Electric Field sensors (0-10Hz) Tip Plasma Probe with sweep voltage e- and ion density and T Retarding Potential Accelerator Analyzer (RPA): mass/velocity 3-axis Magnetometer (40mG to 2 Gauss)

Extremely Low Earth Orbit (ELEO-SAT) University NanoSat Program (NS-8), Taylor University, Upland, IN

March 2013

120-350 km extremely low in situ Ionosphere measurement for discovery and improving models (new Space Weather data)

Globalstar Comm. for global ELEO-Sat link (no ground station) Aerodynamic Satellite and new ELEO Plasma Instruments Mission Objectives: Improve ionospheric models/data below 300km (Space Weather) Investigate VLF coupling and energetic e- in the Radiation Belt Low-cost nanosat for 120-350km with inter-spacecraft comm. Develop new instrumentation for operation in low ionosphere Education with new electrical and mechanical technologies Related Programs: Complements AF programs like DSX, VPM, UNP, NS-7 Tech., other Technologies for Validation: Actel analog FPGA, Carbon fiber 2.5m boom with wires, Aerodynamic flow RPA Analyzer & Charging

VLF Waves

Plasma, Fields , & Waves

Particles EF Booms

120-400 km orbit

mailto:hnvoss@taylor.edumailto:jfdailey@taylor.edu

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Organization (Dan)

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Presentation Slides - Mission Overview - Military Relevance - System Block Diagrams - 5 System Eng. Questions - Student Projects, WBS

- Mech./Boom, SSD, EF/VLF, Plasma, RPA, Thermal, Attitude, Processors, Power, Comm., GSE, K-12

- Prioritization Plan - Schedule - Personnel Budget - Resource Budget - Internal Review Plan

Added Documentation Presentation Slides Mission Overview Document Block Diagrams Prioritization Plan Schedule Personnel Budget Resource Budget Documentation Plan Internal Review Plan Document Tree Contact List Quad Chart 5 System Engineering Questions

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Mission Overview

The proposed Extremely-Low-Earth-Orbit (ELEO) satellite is a powerful student aerodynamic nanosatellite to probe Space Weather and to demonstrate new technology. It will provide an unprecedented observation platform in the relatively unexplored upper atmosphere and ionosphere (120-300 km region)

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Orbital Decay

5 10 20 30 40 50 60 70

Time days80

100

150

200

250

300

Altitude km

ELEO Orbital Altitude vs Time

300 200 100 100 200 300

300

200

100

100

200

300

Approximate 2-3 month flight time

Using multiple nanosats and/or micro-thrusters a continuous ELEO mapping presence is possible

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ELEO Exploration

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Aerodynamic, x-y Booms, Solar

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Science Objectives Approach AFOSR Interest Key AF Doc. Ref.

S1 Make unique In situ Observations below

300 km (ELEO) in Ionosphere and

atmosphere. Improve Models

Aerodynamic ELEO-Sat,

deployable boom, ELEO Plasma

Instruments

Aero braking, Ionosphere, Models,

Communications, GPS phase, Plasma

Dynamics, TIDs, Gravity Waves,

Miller: Sec. 7

Moses: 1a, 6a

S2 Investigate LEP and VLF coupling in the

Radiation Belt and Lightning effects in

space

ELEO energetic particle

detector, VLF receiver, E-Field

and plasma probe

AF current DXS and VPM satellites,

Magnetosphere, Communication,

Radiation Belt

Miller: Sec. 7

Schoenberg: Ref

Moses: 1b

S3 Space Weather: Determine ELEO electron

density in lower Ionosphere and Energy

flow

Langmuir Probe, Electric Field

probe, Waves, Energetic

Particles

Ionosphere, Impulsive Parallel E fields,

Weather / Ionosphere coupling. Space

Weather SATS

Miller: Sec 7

Moses: 1a

Technology Objectives

T1 Develop a low-cost reliable ELEO

aerodynamic SAT for new data below

300km with inter-spacecraft

communication

Based on TSAT Iridium /Global

Star Comm. , deployable solar

array nose cone, Ballistic Coef.

Nanosatellite development, Formation

flying, Intelligence, Autonomous

control, Internet Iridium SAT

Operations

Moses: 2b,7a, 8c

D. Voss: Ref.

T2 Build plasma instrumentation for ELEO

velocities/densities, Thermal and Flow

Model

Include an advanced payload

on ELEO with good heritage

Nanosatellites, Research, Moses: 6a

T3 Deployable Antenna and Boom: Develop

carbon fiber variable 3 m boom: deploy

and retract.

Use Flight motor and gear

reduction used in UNP-3 TEST,

Spool from TUSAT

Deployable Antennas and Booms, Moses: 5a

T4 Advanced Space Electronics: Flight test

powerful mixed-mode FPGA - low

power/size

Actel FPGA fusion analog digital

few chip SAT.

Operational nano-satellite

constellations, low cost/size,

Moses: 4b,4d,4e, and

8c

Educational Objectives

E1 Stimulate many undergraduate students Over 30 students on project,

Education

New ideas!, New recruits, Creativity,

Space careers

D. Voss: Ref

E2 Stimulate secondary students and public.

STEM and K-12

>100 students, Newspaper and

TV coverage

Science interest, Informed public,

education

D. Voss: Ref 8

Table 2.1: ELEO-SAT Objectives, Approach, and Military Relevance Science Objectives trace to the Approach, the AFOSR Interest, and the AF documents. AF documents referenced are

Moses/2012 (NS-7 Technology areas of interest), Miller/2012 (BAA-AFOSR-2012-001 Space Science, Section 7), D. Voss/2012 (University-Nanosat-Program, UNP education), and Schoenberg (in support of AF-DXS missions and VPM BAA-RV-12-05).

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System Block Diagram (Dan)

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System Mechanical Block

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Specification Summary

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Instrument

Power Mass

Duty Cycle Range/Spec. Experience

(mW) (grams)

Plasma Probe 160 270 100% e- density, 0-107 cm-3 NASA, SEEP

E-field Probes 160 475 100% 1 mV- 1 V/m, 25 keV to 2 MeV TSAT, S81-1 SEEP

Magnetometer 145 160 100% 40 m-gauss to 2 gauss TSAT, TUSAT

GPS 500 50 1% 20Hz

Power 75 50 100%

Controls the power to instruments and

HARP

Management RF Modules

Primary Downlink 1.5W 30 10% 1616.25Mhz HARP, TSAT

Duplex Uplink 5.0W 60 2% 1616.25Mhz HARP

Comm. Board 50 50 100% Communications control

module HARP, TSAT

E-Plates & Frame 1500 6061T6 Aluminum TSAT

Total Power 9720

Battery Pack 144W 800

8.0v / 18A LI Poly with protection

HARP, TSAT

Circuit, UL approved

Solar Array 25W 350

Total Mass 4755

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5 Systems Engineering

Questions

1. Who is your customer? The new 120-300 km ELEO data and hardware proof-of-concept should be valuable to the AF,

ONR, NASA, NSF, and other stakeholders. Dr. Voss (in collaboration with others) has much experience in Ionosphere and Radiation Belt publications and needs (See Table 2.1).

ITT Aerospace (or Exelis, Fort Wayne, IN) helps to review our satellite system requirements and work. Plan pre-PDR design review for ELEO.

Other customers include investigators who access our planned Summary Archive ELEO Database.

2. What are your customers requirements? Make calibrated in-situ plasma measurements with standard sensitivities and resolutions

Standard Space Weather Instrumentation includes Energetic Particles, VLF waves, Plasma density and temperature, electric field vector, RPA, and 3-Axis flux-gate magnetometer.