Presentation is loading. Please wait.

Presentation is loading. Please wait.

Venus Mobile Explorer: Balloon Concept Venus Mobile Explorer: Balloon Concept Tibor Balint NASA JPL Richard Brill San Jose State University, NASA Ames.

Published byMarilynn Gardner Modified over 9 years ago

Similar presentations

Presentation on theme: "Venus Mobile Explorer: Balloon Concept Venus Mobile Explorer: Balloon Concept Tibor Balint NASA JPL Richard Brill San Jose State University, NASA Ames."— Presentation transcript:

1 Venus Mobile Explorer: Balloon Concept Venus Mobile Explorer: Balloon Concept Tibor Balint NASA JPL Richard Brill San Jose State University, NASA Ames Ed Chester CTAE Brandy Holmes University of Idaho Qamar A. Shams N ASA Langley Greg Thanavaro Boston University, Georgia Institute of Technology IPPW 6 Short Course 6-22-08

2 Mission Profile Descent Deployment from 70 - 50 km, recovers to cruise altitude, 60 - 65 km Balloon Specs Super-pressure balloon, Helium Teflon coated, acid resistant Shape (TBD by trades, spherical vs. egg-shaped) Supports payload gondola Payload/Instruments Imaging: IR (high res) + multispectral imager Chemical composition: Nepholometer + GCMS Meteorology: meteorology package (T, p, wind) Doppler: Ultra stable oscillator Sensors: Accelerometers + Gyros Drop Sondes: p, T, possible descent imager Lightning: Infrasonic microphone + electric field detector 2Venus Mobile Explorer: Balloon Concept

3 Communications Telecom trades TBD Notionally: X-band Low rate to Earth via DSN (unidirectional HGA) + High rate relay via orbiter (omnidirectional MGA/LGA) Power Gondola: Stirling Engine (21 kg, 140 W) + Secondary Batteries Drop Sondes: Primary Batteries Operationally: High power modes: (e.g. telecom) draw power from RPS + batteries Low power modes: recharge batteries from RPS Concern: ASRG heat waste rejection during cruise to Venus and entry He ASRG Batteries Drop Sondes (x2-4) Sci. Payload 3Venus Mobile Explorer: Balloon Concept

4 Power Breakdown of Balloon Concept 4Venus Mobile Explorer: Balloon Concept Power Power Avail., Watt Stirling Engine140 Secondary BatteriesTBD Science Payload Power Req., Watt Imaging IR10 Multispectral15 Chemical Composition Nephelometer40 GCMS30 Meteorology package4 Doppler Ultrastable oscillator10 Sensors Accelerometers & Gyros1.7 Drop Sondes (primary battery powered)0 Lightning Infrasonic Microphone1 Electric Field Detector1 Communications Omnidirectional, Medium/Low Gain X-band Antenna30 Directional, High Gain Antenna60 202.7

Download ppt "Venus Mobile Explorer: Balloon Concept Venus Mobile Explorer: Balloon Concept Tibor Balint NASA JPL Richard Brill San Jose State University, NASA Ames."

Similar presentations

1 CAN WE TURN A PHONE IN TO A SATELLITE? Android Open 2011San Francisco,10th Oct. 2011.

1 CAN WE TURN A PHONE IN TO A SATELLITE? Android Open 2011San Francisco,10th Oct
Science Motivation Comparative planetology of the outer planets is key to understanding the origin & evolution of the solar system S. Atreya (2006) –Deep,

Science Motivation Comparative planetology of the outer planets is key to understanding the origin & evolution of the solar system S. Atreya (2006) –Deep,
LightSail.

LightSail.
NASA, CGMS-41, July 2013 Coordination Group for Meteorological Satellites - CGMS An Optimization Analysis of the GCOM-C1 and Sentinel-3A Missions for Improved.

NASA, CGMS-41, July 2013 Coordination Group for Meteorological Satellites - CGMS An Optimization Analysis of the GCOM-C1 and Sentinel-3A Missions for Improved.
Stephen Hu Deployment Vehicle Selection Helicopter Design Hours Worked: 102 1 Team Member Stephen Hu.

Stephen Hu Deployment Vehicle Selection Helicopter Design Hours Worked: Team Member Stephen Hu.
International Planetary Probe Workshop 10

International Planetary Probe Workshop 10
Mars Pathfinder Mission Breakthrough on the Surface of Mars.

Mars Pathfinder Mission Breakthrough on the Surface of Mars.
Venus Atmosphere Platform Options Reconsidered Presentation for IPPW-9, Toulouse, June 19, 2012 Graham E. Dorrington School of Aerospace, Mechanical and.

Venus Atmosphere Platform Options Reconsidered Presentation for IPPW-9, Toulouse, June 19, 2012 Graham E. Dorrington School of Aerospace, Mechanical and.
K. Ramus 1, B. Holmes 1, A. Camery 1, D. Eld 1, R. Riggs 1, R. Gunn 1, D.H. Atkinson 1, M. Murbach 2, and the Univ. Idaho.

K. Ramus 1, B. Holmes 1, A. Camery 1, D. Eld 1, R. Riggs 1, R. Gunn 1, D.H. Atkinson 1, M. Murbach 2, and the Univ. Idaho.
TECHNOLOGIES FOR A LONG DURATION LANDER ON THE SURFACE OF VENUS Douglas S. Mehoke, Ralph D. Lorenz, Stuart W. Hill The Johns Hopkins University Applied.

TECHNOLOGIES FOR A LONG DURATION LANDER ON THE SURFACE OF VENUS Douglas S. Mehoke, Ralph D. Lorenz, Stuart W. Hill The Johns Hopkins University Applied.
Space & Planetary Robotics Group Aerobots for Planetary Exploration Dave Barnes Head of Space Robotics Department of Computer Science Aberystwyth University.

Space & Planetary Robotics Group Aerobots for Planetary Exploration Dave Barnes Head of Space Robotics Department of Computer Science Aberystwyth University.
(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Mars CubeSat.

(c) 2014 California Institute of Technology. Government sponsorship acknowledged. Pre-Decisional: For planning and discussion purposes only. Mars CubeSat.
High altitude airborne developments have presented huge advantages in the US military’s arsenal through: environmental monitoring precision navigation.

High altitude airborne developments have presented huge advantages in the US military’s arsenal through: environmental monitoring precision navigation.
Copyright 2011 | Company Proprietary Parachute Development for Venus Missions Christopher Kelley – Airborne Systems Robert Sinclair – Airborne Systems.

Copyright 2011 | Company Proprietary Parachute Development for Venus Missions Christopher Kelley – Airborne Systems Robert Sinclair – Airborne Systems.
Surface and Atmosphere Geochemical Explorer (SAGE) Anita Sengupta, Jet Propulsion Laboratory, California Institute of Technology Rob Maddock, Juan Cruz,

Surface and Atmosphere Geochemical Explorer (SAGE) Anita Sengupta, Jet Propulsion Laboratory, California Institute of Technology Rob Maddock, Juan Cruz,
The Lander is at a 25 km Lunar altitude and an orbital period of approximately 110 minutes. After separation occurs the Lander is completely self sufficient.

The Lander is at a 25 km Lunar altitude and an orbital period of approximately 110 minutes. After separation occurs the Lander is completely self sufficient.
Project X pedition Spacecraft Senior Design – Spring 2009

Project X pedition Spacecraft Senior Design – Spring 2009
0 250- 250 500 Temperature ( C) Pressure ( bars) 1000 100 10 1.0 0.1 0.01 Jupiter Probes Venus Surface Exploration CNSR Europa Surface and Subsurface Titan.

Temperature ( C) Pressure ( bars) Jupiter Probes Venus Surface Exploration CNSR Europa Surface and Subsurface Titan.
Idaho High Altitude Scientific Ballooning Program - Idaho RISE A program of the NASA Idaho Space Grant Consortium Course introduced: ENGR204 Sp2006 Enrollment:

Idaho High Altitude Scientific Ballooning Program - Idaho RISE A program of the NASA Idaho Space Grant Consortium Course introduced: ENGR204 Sp2006 Enrollment:
OXFORD RAS Venus meeting- 12 November 2010 Colin Wilson Co-P.I. – Univ. of Oxford & Eric Chassefière P.I. – Univ. Paris Sud European Venus Explorer An.

OXFORD RAS Venus meeting- 12 November 2010 Colin Wilson Co-P.I. – Univ. of Oxford & Eric Chassefière P.I. – Univ. Paris Sud European Venus Explorer An.

Similar presentations

Ads by Google