Mars Cube One - Amazon Web Services€¦ · MarCO (Mars Cube One) Tyvak NLAS 6U Dispenser Adapter...

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FOUO FOUO 1 MarCO Mars Cube One

Transcript of Mars Cube One - Amazon Web Services€¦ · MarCO (Mars Cube One) Tyvak NLAS 6U Dispenser Adapter...

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FOUO

FOUO

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MarCO Mars Cube One

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Mars

Earth

March 2016

Sept 28, 2016Entry, Descent, and Landing

TCM 1

TCM 2

TCM 3

TCM 4

TCM 5

6.5 Month Cruise

MarCO Mars Cube One

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MarCO-A

MarCO-B

X-Band 8 kbps

To Earth

UHF RelayDSN 70m Reception

X-Band 8 kbps

To Earth

Sept 28, 2016InSight Entry, Descent, and Landing

Mission Objective: • Provide an 8kbps real-time

relay for InSight’s Entry, Descent and Landing at Mars

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Mechanical Configuration: Deployed

Solar Array Feed Sun Sensor

Cold Gas System

Radio Stack

SSPA & LNA Assembly Cabling, camera hooks etc.

Battery Assembly

ReflectArray

C&DH, EPS, ADCS stack

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Mechanical Configuration: Deployed

UHF Loop Antenna

Thrusters

Radiator

Tx/ Rx MGA (co-boresighted with HGA)

Tx/ Rx LGA (bottom, not shown)

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LV Accommodation on Aft Bulkhead Carrier (ABC)

Paylads Integrated on ABC

On 400-series Atlas, the ABC is in a separate volume from the primary fairing volume, with no vent paths between the volumes within the launch vehicle.

Each MarCO spacecraft will be contained within an enclosed NLAS dispenser during launch operations, and separate after InSight separation.

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Integration Flow

Installed in Tyvak NLAS (San Luis Obispo)

MarCO (Mars Cube One)

Tyvak NLAS 6U Dispenser Adapter Plates

Atlas / Centaur Aft Bulkhead Aft Bulkhead Carrier (ABC) Plate

Tyvak NLAS & MarCO Adapter Plate Mated to ABC Plate on Centaur Aft Bulkhead (SLC-3, VAFB)

ABC Plate W/ Adapter Plate Installed to Aft Bulkhead

NLAS/MarCO System Mated to MarCO Adapter Plate (VAFB)

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MarCO Deployment Timeline

180° Snap Roll

MarCO #2 Separation

Resume CCAM & LV EOM Ops

Liftoff

Fairing Separation

InSight Separation

Partial CCAM (w/ 4° Turn)

Centaur Main Engine Start

MarCO #1 Separation

Deployment of MarCO Satellites takes place after InSight departs, after partial CCAM maneuver, and after establishment of new trajectory

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Contamination Control & Planetary Protection

•  CC/PP Overview ›  MarCO is expected to be Category III (Mars Flyby) and will comply with NPR8020.12D

–  Received initial response from PPO to categorization request letter, with a request for additional information

–  MarCO will supply documentation in accordance to NPR8020.12D. Delivery dates are negotiated separately with the PPO, as there are no formal KDPs

–  Plan developed in coordination with InSight PP lead and NASA PPO, delivered 6/8/2015

›  MarCO must mitigate potential impact on InSight’s PP/CC approach

–  ATLO contamination risk minimized; MarCO is physically separated from InSight on launch vehicle aft bulkhead carrier

›  Generally, MarCO flight systems have no organic contamination control requirements

–  Spacecraft maintained at “generally clean” level during ATLO –  Special consideration will be taken for propulsion system (e.g. filtered propellant) and

star tracker optics (e.g. RBF covers) as needed

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Planetary Protection Implementation

•  Baseline Plan is Impact Avoidance ›  MarCO intends to comply with the impact avoidance requirements for launch vehicle

elements, (10e-4 for 50 years) as opposed to the more typical (less stringent) requirements levied on orbiters or flyby spacecraft

–  Rationale: Typical spacecraft impact avoidance is predicated on 100k cleanroom (unlike MarCO)

–  PPO indicates that if MarCO can demonstrate impact avoidance requirements for launch vehicle elements, no cleanliness or assay requirements will be levied

›  Must bias all TCMs to maintain this probability threshold, including in the event of spacecraft failures (no credit is taken for presumed spacecraft reliability).

–  Analysis indicates TCM bias maintains probability threshold

•  Contingency Plan is Burn-Up & Break-Up analysis ›  In case that the above impact avoidance constraints cannot be met, MarCO intends to

demonstrate via burn-up and break-up analysis that no more than 10e5 viable spores (per NPR 8020.12D) get delivered to the surface of Mars in the event of an impact of either spacecraft

›  This approach would entail biological assays and possibly additional cleaning and/or cleanroom procedures to establish/verify initial cleanliness

›  This approach is not preferred due to potential risks and cost growth. Current trajectory analysis indicates this backup is not required.