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V-BOSS: Venus Bridge Orbiter and Surface System

Preliminary Report

Compass Team

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Team

Customer VEXAG

Study Lead Steve Oleson

Science, PIs Noam Izenberg, Marty Gilmore, Kandis Lea

Jessup, Robert Herrick, Jeff Balcerski, Geoff

Landis

High Temp elements Gary Hunter, Phil Neudeck, Glenn Beheim,

John Wrbanek

System integration/PEL J Michael Newman

Mission Steven McCarty

Guidance, navigation, and control Brent Faller, Michael Martini

Mechanical systems John Gyekenyesi

Thermal Systems Tony Colozza

Power Brandon Klefman, James Fincannon

Configuration and data handling Tony Colozza

Propulsion James Fittje

Communications Bob Jones

Configuration Tom Packard

COST / Risk Elizabeth Turnbull

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Purpose/FOMs• The Venus Bridge seeks to develop a two element mission (long duration lander and

orbiter relay) which fits in a $200M cost cap.

• The Compass Team tasked with the Lander/Orbiter Option

• Science priorities are derived from decadal survey goals.

• Launch Year: 2025, Lifetime –120 earth days on surface (~ 1 day/night cycle)

• FOMS: Cost, Decadal goals, Long duration coupled science (many days)

• Fault tolerance: Zero Fault, Class D– Telemetry covered for Mission Critical Events

• Trades done on broad array of Mission Options

• Point design developed to show concrete example what level of science for a Venus Bridge Mission with orbiter/lander science can be done in the 200 M Cost Cap

• This presentation will provide an overview of the Study Approach, Science Drivers and Return, Point Design including V-BOSS Orbital-Surface System, and background on trades/costs

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Study Approach

• Gather Science traceability, options, priorities

• Define notional ’allotments’ for elements based on the $200M cost cap

– Assuming a single, secondary launch the ‘wraps’ and cost margin define what can be done for the sum or flight systems

– Estimates from past lander, EDL, Orbiter designs used to ‘scope’ out the reasonable allotments to each system

• Flight systems design order below with design guided by Science Priorities

– Lander

– EDL

– Orbiter

• Baseline science $ allotments guides made based on past design cost splits

• Trades in Point Design to maximize science goals in cost cap

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V-BOSS (Venus Orbiter-Surface System)Approach

• Mission Theme: Coupled Orbiter-Lander concept to uniquely investigate mineralogy and surface-atmosphere interactions over extended duration

• Science Overview: 3 Mission Components

– Orbiter: Determine surface mineralogy

– Descent Observations: Atmospheric composition and IR radiance profile

– Long-Lived Lander: Surface-atmosphere interactions/dynamics, investigate surface mineralogy, equilibrium conditions, reaction rates, kinetics (possible baseline interior dynamics), downwelling radiance

• All three components complement each other and provide new science based on the Mission Theme

• Other Themes could have been chosen

• Based on:

– New Advances in Small Sat Technology

– Long-Lived In-situ Explorer (LLISSE) model: Simple system approach using high temperature electronics and microsystems

– Assumption of ride-along on Lunar Mission

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Venus Bridge Orbiter and Surface Study: Executive Summary

• Design Reference Mission for a $200M cost capped Venus Lander/Orbiter

• Mission:

– Delivery: Secondary launch towards moon, Orbiter carries Lander, two LGA, Powered EGA, deploy lander/EDL 30 days before Orbiter Capture (in earth view) into 10 earth day inclined Venus orbit, lander follows and enters in sight of orbiter and lands 55°S at night

– Lander Science: Lander gathers IR, Temp, Pressure and Chemical data during descent and for an entire Venus night/day, Wind data gathered once on surface: 2 minutes of data gathered and transmitted every 12 hours to orbiter using 100 MHz link at 36 bps

– Orbiter takes IR image co-incident with lander IR data and returns uplinked and IR image data to earth once a day at 200 bps

• Lander: ~ 7 kg, ~ 20 cm cube with drag flap, high temp electronics and battery, UHF communications through ½ wavelength loop antenna

• Entry/Descent/Landing System: ~ 10 kg, Heritage 0.5m Aeroshell, passive separation systems, lander provides telemetry

• Orbiter: Orbiter: ~ 100 kg dry Smallsat with ~ 70 kg monopropellant to provide ~ 1000 m/s burns at earth and to capture at Venus, ~ 200 W solar arrays, UHF uplink from lander, X-band data return to earth

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V-BOSS in ESPA ring

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Lander in Aeroshell

Orbiter in Final Configuration Lander on Surface

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Lunar flyby (~ 3 days

Launch and Cruise CONOPs

Secondary Launch to Moon (either co-manifest with lunar payload or as an upper stage restart)

Lunar flyby (~ 5 days)

Lunar phasing

Second Lunar flyby (~ 117days)

Powered Earth Flyby ~270 m/s(~ 120days)

Cruise to Venus ~ 130 days

Separate Lander @ 7rpm ~29 days before entry

Orbiter Inserts into 240 hr orbit in view of earth (~ 800 m/s)

Orbiter Receives telemetry and science data from lander thru descent (~ 2 hrs after capture burn)

Lander ‘wakes up’ ~ ½ hr before entering venus atmosphere

Orbiter deploys UHF antenna

80 km

70km

60km

50 km

40 km

30 km

20 km

10 km

0 km

-93°C

-43°C

-23°C

67°C

142°C

210°C

390°C

410°C

455°CSurface

Drag flaps are deployed

and heat shield released 25

minutes 20 s after entry

Venus Atmospheric Descent

Subsonic Speeds

are reached 20 s

after entry

Landing probe is released

37 minutes 20 s after entry

Landing probe reaches the

surface 85 minutes 8 s after entry

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V-BOSS (Venus Bridge Orbital Surface System)Science Return Examples

• Couple Venus Orbiter/Descent/Landed Science• Orbiter: Observe Lander site region during descent

and over extended periods

• Probe on Decent: Provide an IR profile upward/downward profile

• Landed Probe: IR bolometers correlated with 2 wavelengths of Orbiter spectrometer

• Orbiter Observations• Multispectral IR characterization of significant

percentage of surface

• Constrain surface mineralogy and provide planet wide comparative assessments

• Provide data to compare orbital measurements and real-time surface properties

Orbiter Configuration

Mission Overview

Lander Antenna

IR Mapper

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• Descent Profile Measurements• 3 hour characterization of the descent from

aeroshell departure to surface

• Determine atmospheric composition at lowest scale height

• Provide IR (looking up and down) and Visual radiance profile over the transition to the surface

• Long Duration Surface Measurements • Constrain atmospheric variability at surface

boundary

• Measure surface mineralogical reactions

• Observe meteorological and radiance properties over 1 Venus solar day (day/night)

Lander During Descent

Wind Sensor

UpwardBolometers

Lander on SurfaceDownwardBolometer

Reaction Chemistry

Metrological array

V-BOSS (Venus Bridge Orbital Surface System)Science Return Examples

UpwardBolometers

Metrological array

DownwardBolometers

80 km

70km

60km

50 km

40 km

30 km

20 km

10 km

0 km

-93°C

-43°C

-23°C

67°C

142°C

210°C

390°C

410°C

455°CSurface

Chemistry,

pressure and

Temperature

measured during

descent

One

downlooking and

two uplooking

bolometers

measure the

atmosphere

simultaneously

with the orbiter’s

IR imager

Venus Atmospheric Descent

Subsonic Speeds

are reached 20 s

after entry

Landing probe is released

37 minutes 20 s after entry

Landing probe reaches

the surface 85 minutes

8 s after entry

Lander provides UHF telemetry to

Orbiter just before and during EDL

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One ~1500 hr day

Landed Operations

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One ~1500 hr Night

Gas/Pressure/Temp/Wind Speed Direction 2 minutes of samples every 12 hrs

2 min UHF, 36 bps Uplink to Orbiter 3 times a day

Daytime operations at same level as daytime except without IR bolometers

Orbiter in highly elliptic, 240hr orbit

Gas/Pressure/Temp/Wind Speed Direction 2 minutes of samples every 12 hrs

IR Bolometers probe the atmosphere 2 minutes of samples every 12 hrs

Orbiter IR imager images Venus twice an orbit at the same time as the lander

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Landing Site Trades

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3

Low Risk

Med Risk

0°,40°N

327°,63°N

Excludes:

Selected Site

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Science TraceabilityDecadal Goals VEXAG Goals Mission Goals Instrument Measurement

Orbiter

How have the myriad chemical and physical processes that shaped the solar system operated, interacted, and evolved over time?

Understand what the chemistry and mineralogy of the crust tell us about processes that shaped the surface of Venus over time.

Constrain surface mineralogy MIREM: Multispectral IR Emissivity Mapper Radiance at sensor for 4 channels in the infrared windows (1 channel

outside window for control)

Probe (Descent)

What governed the accretion, supply of water, chemistry, and internal differentiation of the inner planets and the evolution of their atmospheres, and what roles did bombardment by large projectiles play?

Understand atmospheric evolution; Characterize the Venus Greenhouse

Determine atmospheric composition at lowest scale

height

V-Chem (on Descent): Atmospheric Chemical sensor suite: fO2, CO, SOx, H2O, OCS, HCl, HF,

NO, Pressure, Temp

Metrological array

Can understanding the roles of physics, chemistry, geology, and dynamics in driving planetary atmospheres and climates lead to a better understanding of climate change on Earth?

Understand what the chemistry and mineralogy of the crust tell us about processes that shaped the surface of

Venus over time.

Radiance (IR Bolometers) V-Rad (On descent) Radiance (IR Bolometers) (on lander) 2 looking up and 1 looking down

Bolometer with IR Filters

Probe (Landed)

How have the myriad chemical and physical processes that shaped the solar system operated, interacted, and evolved over time?

Characterize how the interior, surface, and atmosphere interact

Constrain surface-atmosphere interactions

V-Chem: Long duration Atmospheric Chemical sensor suite: fO2, CO, SOx, H2O, OCS, HCl, HF,

NO, Pressure, Temp

Metrological array

Characterize current processes in the atmosphere

Measure wind speed and direction over several months

V-Wind: Long-duration wind sensor Metrological array

Understand what the chemistry and mineralogy of the crust tell us about processes that shaped the surface of Venus over time.

Radiance (IR) V-Rad: Radiance (IR Bolometers) (on lander) 2 looking up and 1 looking down

Bolometer with IR Filters

Did Mars or Venus host ancient aqueous environments conducive to early life, and is there evidence that life emerged?

Understand what the chemistry and mineralogy of the crust tell us about processes that shaped the surface of Venus over time.

Measure surface mineralogy reactions

V-Lab: Reaction chemistry samples Measure electrochem (IV,CV)

Microplatforms with geological samples

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Trades within this Theme

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Approaches for Other Themes

VEXAG Goals Mission Goals InstrumentOrbiter

Understand atmospheric evolution; Characterize the Venus Greenhouse Identify UV absorber UV imaging spectrometer

Descent Probe

Characterize current processes in the atmosphere Quantify radiant flux at low altitudes Up/downwelling radiometer (VIS-IR)

Measure wind speed and direction AccelerometerLower atmosphere composition Self-lit UV spectrometer

Particle Characterization Nephelometer Lander

Assess the current structure and dynamics of the interior. Measure heat flow Heat flow sensor

Measure seismicity over several months Long-duration seismometer

Measure surface conductivity Conductivity probe/spike

Understand chemical and physical processes that influence rock weathering

Local geologic context for interpreting lander data Panchromatic camera (enclosed)

Thickness, compressiblility of soil measure soil compressibility (resistance)

Characterize current processes in the atmosphere

Visible radiance Narrow band solar cell

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Alternate Theme

Science goal for alternate point design:Coordinated study of the components of the atmospheric circulation and dynamics in order to resolve questions associated with the mechanisms that drive Venus’ atmospheric superrotation. To accomplish this goal requires coordinated remote and in-situ observations on the time scale of a solar day on Venus.

Approach

Lander: LLISSE (with capability to monitor radiant energy at surface)

Lander: Self-lit simple UV spectrometer that can identify atmospheric composition in

near surface environment level

Orbiter: UV imaging and spectroscopy suite

Orbiter: NIR imaging and spectroscopy suite

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Mission Point Estimate (FY18$M)

FY18$M

Phase A 4

Phase B/C/D Costs 158

1 Program Management 10

2 Systems Engineering 13

3 Safety & Mission Assurance 5

4 Science 6

5 Payload 10

5.1 Lander Payload 4

5.2 Orbiter Payload 6

6 Flight System 86

6.1 Lander 19

6.2 Entry, Descent, and Landing 9

6.3 Orbiter 59

7 Mission Operations 13

9 Ground System 6

10 Systems Integration & Testing 8

Phases A-D Mission Cost 162

Reserves (25%) 40

Total Cost with Reserves 202

Mission Cost Summary

• Excludes:

– Phase E

– Launch Costs

– Education

– TRL<6 funded elsewhere

(LLISSE Baseline development on-going)

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Summary

• Mission Theme: Coupled Orbiter-Lander concept to uniquely investigate mineralogy and surface-atmosphere interactions over extended duration

• Significant and Revolutionary Science Viable

– Orbiter: Determine surface mineralogy

– Descent Observations: Atmospheric composition and IR radiance profile

– Long-Lived Lander: Surface-atmosphere interactions/dynamics, investigate surface mineralogy, equilibrium conditions, reaction rates, kinetics (possible baseline interior dynamics), downwelling radiance

• Launch Year: 2025, Lifetime –120 earth days on surface (~ 1 day/night cycle)

• Method Identified to Allow Mission to Venus via Launch Towards the Moon

• Long-Lived In-situ Explorer (LLISSE) model: Simple system approach using high temperature electronics and microsystems

• Cost: $202M with 25% growth (assumes launch, phase E, TRL<6 funded elsewhere)

PRELIMINARY CONCLUSION: VENUS BRIDGE CONCEPT VIABLE