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Daniele Bedini (BEDINI & PARTNERS)

Andrea Messidoro (AEROSEKUR)

Giorgio Boscheri (THALES ALENIA SPACE ITALIA)

ISLSWG Workshop

“BIOREGENERATIVE LIFE SUPPORT”

Turin, 18/19 May 2015

SPACE EXPLORATION:

GREENHOUSES

ARCHITECTURES

TECHNOLOGIES

& CONTENTS

by BEDINI/BOSCHERI/MESSIDORO

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Presentation Contents

GreenMOSS Study Introduction:

Team and objectives

The Global Exploration Roadmap context

The MELISSA Context

Lunar Greenhouse architecture concepts and selection criteria

Lunar Greenhouse architecture baseline description

Primary and secondary structure preliminary sizing strategy

Architecture-related work limits and suggestions for future work

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

GreenMOSS – Lunar Greenhouse

Study (2013-2014)

TEAM

Preliminary Study of a Lunar

surface greenhouse

in the MELISSA framework SUPPORT

Two major trade-offs:

Artificial vs natural illumination

Mono vs Multicrop

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

GreenMOSS in the Global

Exploration Roadmap

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Contribute to MELiSSA project GreenMOSS contributes to the need to get preliminary figures

(worst case scenario) for the MELiSSA project

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Volume reduction challenge inherited

from previous greenhouse studies

HOW TO ADDRESS THE CHALLENGE:

• New configurations/architectures

• Deployable primary and secondary structures

ESA OGEGU

TASI LUNAR FARM UA-CEAC LGH prototype

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Primary structure preliminary sizing

steps

European

Launcher

Crop only on

single floor

(multiple levels)

Above Lunar

surface

Crop module

architecture

definition

Definition of

modules

configuration

Greenhouse

final

configuration

Structure

preliminary

sizing

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Architecture selection strategy

• A big set of possible primary structure configurations was identified

• Based on architectural feasibility considerations, a reduced set of promising

solutions was identified

• The limited set was further analysed for a more advanced trade-off, from a system level

point of view, to identify the baseline solution for the primary structure

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Advanced Technologies

Identification + Requirements

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

PS main concepts for further analysis

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SICSA LunarHab Concept [1980]

SICSA MarsLab Concept [2004]

LGH Arizona University [on-going]

NASA/ILC Lunar Habitat

[1996]

TASI/Aero Sekur STEPS2 [on-going]

NASA/ILC Dover/TASI TransHab

[2000]

NASA/Bigelow Genesis I, II and BEAM [on-going]

ESA/TASI/ Aero Sekur

IMOD [2006]

3 – INFLATABLE CYLINDER

W. INT. RIGID CORE 2 – INFLATABLE CYLINDER W.

INT. STRUCTURE

1 – INFLATABLE DOME

– ONE MEMBRANE

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

17/04/2015 Ref.:

PS baseline concept brief description

• Cylindrical shape module with 2 half-

toroid ends (IMOD-like)

• Vertical orientation at launch and

horizontal orientation at lunar surface

installation

• Both axial (x) and radial (y-z)

expansions

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Each crop module is equipped with

multiple-level crop growth units,

providing up to 135 m2 of crop

surface, within a 515 m3 usable

volume

usable volume

PS baseline concept brief description

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

17/04/2015

Internal Barrier Radiation

Protection

Flexible skin detail

Product tree

Structure Assembly Mass

[kg]

Flexible Skin 2866

Metallic End Assembly 1300

Core Frame 280

Total 4446

Single module preliminary mass budget

PS baseline concept brief description

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

17/04/2015

Flexible skin detail

Internal Barrier Radiation

Protection

Layer name Thickness [mm] Material Position

Radiation Protection TBD TBD 1

Internal Barrier 0,5 Kevlar 2

Air Containment Bladder 0,7 Polyurethane (PU) 3

Structural Restraint 4,2 Kevlar 4

MMOD Shielding 300 Nomex 5

MLI 0,3 VDA and Mylar 6

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Up to about 500 m2 of crop surface

required

Crop modules connected to

common purely inflatable aisle

Including quality

control and storage

units

135m2 x 4

Additional module required for:

Crop quality control and Storage

Interface with the lunar base/

MELiSSA loop

PS baseline concept brief description

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

PS baseline concept summary

• Selected crop module architecture

• Cylindrical shape module with 2 half-toroid ends (IMOD-like)

• Vertical orientation at launch and horizontal orientation at lunar surface installation

• Both axial and radial expansions

Main uncertainties for the PS preliminary design:

• More detailed analysis of deployment phase

(incl. installed HW) needed

• Review of load paths after consolidation of the

internal configuration

• Radiation protection layer to be re-assessed after

design consolidation

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

PS & SS mechanical analyses

Loading Conditions

1. Stowed Configuration

• Launch loads

• Orbital maneuvers loads (insertions and cruising)

• Landing loads

At this stage only recommendations and guidelines were given.

2. Deployed Configuration

• Internal pressure load

• Other sub-systems masses and interaction loads

• Human operations loads

At this stage a preliminary mechanical assessment was performed:

• Analytical calculation for Internal Pressure Loads (Structural Restraint)

• FEM Analysis for other sub-systems masses and interaction loads (including SS)

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Structural Restraint configuration

PBO Zylon ribbon Kevlar ribbon

Restraint (courtesy of STEPS2)

Restraint CAD

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Restraint analytical calculation

model

• Excel-based analytical

calculation tool,

WPC3_INFLATABLE,

developed for the research

program STEPS2 regarding

inflatable space habitable

structures with the scope of

increase the TRL up to 5.

• Based on the Mariotte or

Young-Laplace equation for

thin-walled cylinders.

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

SS mechanical analysis

Scope

• Report the results of the structural analysis of the reference design of

secondary structure

• define if the proposed design is a feasible base for this structure

• define some design modifications to improve this solution

Required results

• Calculation of the deformations of the structure under the applied

loads

• Calculation of the von-Mises stress

• Calculation of MoS as per ECSS-E-30-05

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to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

SS mechanical analysis – load

distribution

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Main limits to foster further

discussion - 1/2

Direct impact on architectural solution selection and analysis

• No standard analysis models are available for:

• INFLATABLE STRUCTURES and FLEXIBLE COMPONENTS

• Radiation shielding concept need for greenhouse module is still not defined

(with the potential to strongly impact budgets)

• Installation operations shall be more accurately defined (significant impact on

possible architectures)

• Module unloading from lander (including rotation)

• Module positioning

• Module deployment and docking/mating

• Module inflation

• Module outfitting

• Planetary outpost installation additional support equipment (rovers, robotic

arms etc...) are not defined yet (significant impact on possible architectures)

• Logistics is not defined yet (significant impact on mission)

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

Main limits to foster further

discussion - 2/2

Direct impact on system sizing

• Mass Balance available data limited reliability for many GreenMOSS crops

strongly impact required growth surface

• Static plant growth rates (from NASA BVAD) are not for the same

cultivars

• MELiSSA physiological crop growth model not yet available for all crops

• Lack of consolidated data for low TRL key technologies may strongly impact

configuration and budgets:

• Solar collector/concentrator

• Robotic aid hardware (e.g. sowing, harvesting, transplanting)

• High-flow thermal control equipment

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This document is not to be reproduced, modified, adapted, published, translated in any material form in whole or in part nor disclosed

to any third party without the prior written permission of Thales Alenia Space Italia ISLSWG WS, Turin, May 18-19 2015

By Bedini, Messidoro, Boscheri

TEAM SUPPORT

QUESTIONS?