10 05-28final tfn slide-deck

Apr 7, 2023 www.teamfrednet.org 1

Team FREDNET Mission Update


GLXP Requirement• Primary Prize

– Landing on Moon• Carry GLXP payload

– Broadcasting HD video– Roving 500 m

• Secondary Prizes– Water detection– Heritage sites– Surviving the Lunar night


Team FREDNET to the Moon• Open Source GLXP Team

– Everyone can participate– Students at all levels– Professionals at all levels

• Current effort include– Individuals from US, Europe, Australia and Asia– University teams– Industry partners

• People making a difference– Being a participant rather than a spectator


TFN Structure

• Mission Team– Overall mission design,

interfaces, integration

• Open Source Team– Subsystems, alternative

solutions, innovation

• Business Development– Strategic partnerships, fund

raising


TFN Mission Study

• Baseline mission concept– Falcon 1e– Launch from Kwajalein Atoll– Direct descent to Lunar surface

• Constraints– Cost/Reliability– Payload mass– Launch windows– Landing windows


TFN Mission Phases

• Ascent (Falcon 1e)– Upper stage burnout

• Payload tip-off (Separation)– Earth coast - checkout

• Trans-lunar injection (TLI stage)– Trans-lunar coast – mid-point corrections

• Direct descent landing (Lander)– Post landing check-out and operations


Landing/Operations

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Planned operations from -40 C to +40 C(narrow window for Lunar ops ~ 2 days)


Launch Windows

Fluctuations in Lunar Distance vs. Optimal Landing Window


Trajectory


Delta V Budget

Mission Phases Delta V (m/s)

Trans-Lunar Injection 3100Margin 5% 155TLI Total 3255Landing 2700Margin 5% 135ACS 10TCM 80Alignment error 100Landing Total 3025Mission Total 6280


Solid propellant concept (Weed)

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o Two separation stageso TLI separationo De-Orbit separation

o Two solid stages o ATK Star class

o Monopropellant Landero Hydrazineo Differentially throttled

(Star30BP)

(Star17A)

TLI separation plane

De-orbit separation plane

Landed Mass Layout



Landed Mass Breakdown

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Subsystem Baseline Mass (kg)Communications 5.0GNC 5.4Power 8.0C&DH 2.0Thermal (passive) 0.0 Structure 13.0TFN Payload (rover/camera) 3.5GLXP Payload 1.0Total 37.9Margin 7.1Margin % 19%Total+Margin 45.0

Vehicle Masses (Weed)


Item TLI (kg) De-orbit (kg) Lander (kg)Vehicle Total 37.00 14.50 20.90Total Payload 207.40 80.90 45.00Engine/Fuel 505.00 112.00 15.00

GLOW 749.40 207.40 80.90


Bi-propellant concept (Masten)

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o One separation stageo TLI separation

o Two bi-propellant engines o TLI is 3000 lb classo Lander is 200 lb class

o Landero De-orbit and descent

(Star30BP)

(Star17A)

TLI separation plane

De-orbit separation plane


TLI/Lander Mass Breakdown

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Lander Stage Total (kg)Ox Tank 4Fuel Tank 2Helium Tank 7Main Engine 7RCS Thruster 4Structure 8Plumbing 4Electrical 4

Vehicle Total 40Payload 30Oxidizer 97Fuel 13

Total GLOW 181

TLI Stage Total (kg)Ox Tank 12Fuel Tank 4Helium Tank 25Main Engine 15RCS Thruster 4Structure 5Plumbing 5Electrical 4

VehicleTotal 74Lander 181Oxidizer 440Fuel 61

Total GLOW 756


Conceptual Communications Budget• Vehicle Transmission (40 cm dish):

– Pointing accuracy ~ 3 deg• Low gain whip antenna prior to dish pointing

– During TLI• the transmit power is ~ 0.5 Watts RF

– After landing, • the transmit power is increased to ~ 1.0 Watts RF

• Ground Station Transmission (34 meter dish):– Pointing accuracy ~ 0.05 deg– Operating at 8.4 GHz


TFN On-going development• Open source contributions

– Lander design• Queens Univ. study• Univ. of Virginia

– Imaging technologies• Broward College

– Rovers• Three competing concepts• LEGO Moonbot educational software program

– Communications• Open source radio


Come join Team FREDNET

• A lunar mission goal– Pooling our collective intelligence– Demonstrating our potential– Making our efforts relevant

• Demonstrating real science and engineering

[email protected]


Thanks to the TFN Mission Team

• AGI for use of Satellite Toolkit• David Masten• Ryan Weed• Joshua Tristancho• Balachandar Ramamurthy• Alex Csete• Bill Mania


Additional Slides


Global Reach• Open source spawned by the internet

– Forums– Wikis– Skype– Youtube– Twitter

• Leveraging IT ubiquity for collaborationwww.teamfrednet.org


TFN Open Source Technologies

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picoroverWRV-1 Jaluro

Lunar Lander


TFN and XOIE

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Mission Analysis

Stage Mission Solid Margin Bi-Prop Margin

TLI 3255 3300 1.4%

De-Orbit

2835 2700 -4.8%

Landing 190 190 0.0%

Technology

10 05-28final tfn slide-deck