AAE450 Spring 2009 Electronic Hardware Systems Communications Trans-Lunar Phase Joshua Elmshaeuser Communications 1.

Slides:



Advertisements
Similar presentations
Agate Ltd Case Study-Requirments Analysis
Advertisements

AAE450 Spring 2009 Reliability Analysis Solomon Westerman, PM Week 5, 2/12/09 [Solomon Westerman] [PM] 1.
Lunar Lander Power Systems
8’th ILEWG Conference, Beijing, July 23-27, 2006 MSSL/UCL UK. Lunar Exploration with Penetrators A.Smith, R.Gowen, A.Coates – MSSL/UCL I.Crawford – Birkbeck/UCL.
AAE450 Spring 2009 UHF Lander-Rover COM Systems Toy Ball Shell Structure Communications Group Trans Lunar Phase Group Toy Ball Analysis Lander CATIA Design.
AAE450 Spring 2009 Final Presentation Draft Slides Description: Some draft slides and ideas 3/26/09 Kris Ezra Attitude 1.
AAE450 Spring 2009 Tim Rebold 01/22/09 Structures and Thermal Thermal Control Systems [Tim Rebold] [STRC]
AAE450 Spring 2009 Hopper Trajectory February 26, 2009 [Alex Whiteman] [Mission Ops] [Lunar Descent] Page 1.
AAE450 Spring 2009 Attitude Determination in Low Earth Orbit Description: Research Attitude Determination Systems Filter Pertinent Reference Material from.
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.
AAE450 Spring 2009 Slide 1 of 7 Orbital Transfer Vehicle (OTV) Thermal Control Ian Meginnis February 26, 2009 Group Leader - Power Systems Phase Leader.
AAE450 Spring 2009 Slide 1 of 8 Orbital Transfer Vehicle (OTV) Masses and Costs Ian Meginnis March 12, 2009 Group Leader - Power Systems Phase Leader -
AAE450 Spring 2009 Kelly Leffel 3/26/09 Structures and Thermal Lunar Descent Phase Lander Integration Lander Thermal Control (Day) Kelly Leffel Structures.
AAE450 Spring 2009 Lander Phase: Hybrid Propulsion System Propulsion System Sizing and Inert Mass Analysis Hopper and Rover Designs for 10kg Payload Hopper.
AAE450 Spring 2009 More Attitude Control Thruster Options Brittany Waletzko Translunar/OTV Phase Week 7 Brittany Waletzko - ATT.
AAE450 Spring 2009 Week 4 Presentations [Solomon Westerman][PM]
AAE450 Spring 2009 Lunar Descent Final Numbers Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 03/12/09 [Josh Lukasak] [Attitude] (1)
AAE450 Spring 2009 Translunar Orbit Transfer Vehicle (OTV): Propulsion System Setup for 100g & 10 kg Case Launch Vehicle Selection for Arbitrary Case Thermal.
Project X pedition Spacecraft Senior Design – Spring 2009
AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.
AAE450 Spring 2009 Hopper Design Alternative Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 02/26/09 [Josh Lukasak] [Attitude] (1)
AAE450 Spring 2009 X 0 Power System Solar - Battery Solar arrays Tony Cofer- Power System.
AAE450 Spring 2009 Patch Antenna Pivot Michael Christopher -Communications Group -TLI Phase Group 1 OF 5Michael Christopher - COM.
AAE450 Spring Gram Lander CATIA Design Communications Group Trans Lunar Phase Group Toy Ball Analysis Lander CATIA Design Joshua Elmshaeuser Communications.
AAE 450 Spring 2008 Justin M. Rhodes Avionics – Telecommunications Webmaster Telecommunications and Wiring.
A spring with a mass of 6 kg has damping constant 33 and spring constant 234. Find the damping constant that would produce critical damping
Electricity Consumers: LED Lighting
Space Engineering Institute (SEI) Space Based Solar Power Space Engineering Research Center Texas Engineering Experiment Station, Texas A&M University.
AAE 450 Spring 2008 Nicole Bryan Avionics Final Presentation Slides 1.
COMM Subgroup Tomo Sugano (Primarily served as COMM personnel) Tasks –Started out by helping Relative Orbit team with differential delta-V requirement.
Development of special generators of low-temperature plasma for ecological and biomedical applications. Research and Educational Center on Basic Problems.
AAE450 Spring 2009 Kelly Leffel 3/0509 Structures and Thermal Lunar Descent Phase Lander Integration Lander Thermal Control Kelly Leffel Structures and.
AAE450 Spring 2009 BAE Single Board Computer Ground Based Systems Communications Group Trans Lunar Phase Group Joshua Elmshaeuser Communications 1.
1 Titel van de presentatie Communications Communications architecture Frequency bands Ground-space link Intersatellite link Antenna configuration Tracking.
1 How to design or select an antenna? Communications Crosslink scientific/housekeeping data (emitter & receiver sat) G/S link scientific data (emitter.
Telecommunications Technology Concepts of Technology.
AAE450 Spring 2009 Communications Ground Stations Communication Equipment Alternative Landing Method March 26, 2009 [Trent Muller] [COM]
AAE450 Spring 2009 Rover Power Toy Ball Power (Budget and Resizing) Jeff Knowlton [Jeff Knowlton] [Power] 1.
Titan Saturn System Mission Workshop - Paris, Mar 17-19, 2008 MSSL/UCL UK Penetrators for Enceladus Titan Saturn System Mission Workshop - Paris, Mar 17-19,
AAE450 Spring 2009 Support structure for Orbital Transfer Vehicle (OTV) Tim Rebold STRC [Tim Rebold] [STRC] [1]
AAE450 Spring 2009 Slide 1 of 7 Final Presentation Slides Ian Meginnis April 9, 2009 Group Leader - Power Systems Phase Leader - Translunar Injection OTV.
AAE450 Spring 2009 Slide 1 of 8 Final Presentation Back-up Slides Orbital Transfer Vehicle (OTV) Power and Thermal Control Ian Meginnis Ian Meginnis Power.
 In computing, an input device is a peripheral (piece of computer hardware equipment) used to provide data and control signals to an information processing.
ESA’s GSTB Programme GSTB-V1 is a ground system to test Galileo’s key algorithms using GPS data GSTB-V2 consists of a pair of satellites: –GSTB-V2/A (SSTL)
AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Comparison [Brian Erson] [Attitude] 1.
AAE 450 Spring 2008 Nicole Bryan 2/14/2008 Avionics, MAT Team MAT Results Ref: Danielle Yaple, MAT Code-writers 1.
AAE450 Spring 2009 Thermal Transport Subsystems Toy Ball System,100g Payload John Dixon COM GL, Loco PL [John Dixon] [COM GL] 1.
Final Slides By: Kara Akgulian Mission Ops Locomotion Phase 1.
AAE450 Spring 2009 Lander Phase: Hybrid Propulsion System Propellant Tank Sizing and Pressure Analysis Thermodynamic analysis on Hydrogen peroxide Tanks.
AAE450 Spring 2009 Lander CATIA Design Communications Group Trans Lunar Phase Group Space Ball Analysis Lander CATIA Design Joshua Elmshaeuser Communications.
MASCOT, ROSETTA,… Examples of CNES activity in Proximity Links.
AAE450 Spring 2009 Kelly Leffel 2/5/09 Structures and Thermal Lunar Descent Phase Kelly Leffel Structures and Thermal 1.
AAE450 Spring 2009 Lunar Night and Lander Power System Adham Fakhry February 26th, 2009 Power Group Lunar Descent Phase Passive Thermal Control for Lunar.
AAE450 Senior Spacecraft Design Mark Cunningham Week 6: February 22 nd, 2007 Communications Team, Comm. SATs CAD, TV/ET/MT Groups Communication Satellites.
AAE 450 – Spacecraft Design 1 Attitude Determination Methods Brienne Bogenberger January 18, 2004 Dynamics & Control Group Lead, Attitude Determination.
Fundamental Digital Electronics
AAE450 Spring 2009 Kelly Leffel Structures and Thermal [Kelly Leffel] [Structures and Thermal]
AAE450 Spring 2009 Power Systems for Lander Adham Fakhry [Adham Fakhry] [Power]
AAE 450 Spring 2008 Stephanie Morris 2/21/08 Propulsion Standard Deviations.
AAE450 Spring 2009 Attitude Determination in Low Earth Orbit Description: Determine Attitude Accuracy Upper and Lower Bound Recommend Addition of Sun Sensor.
POWER AMPLIFIERS E 5:4 LAB.GRUPPEN NAME MODEL 제조사 General
Structures and Thermal Locomotion Phase
With its new amplifier IC chip, indoor directional TV antenna
Rover Communication Subsystems
Nicole Bryan Avionics Final Presentation Slides
Onboard Electrical Equipment
Orbital Transfer Vehicle (OTV) Power Systems
By: Josh Lukasak Attitude Group Lead Lunar Descent Phase Manager
David Childers March 6, 2008 Structures Cost Center of Mass
Now Buy Best External Door Hardware from Doorhardware
Presentation transcript:

AAE450 Spring 2009 Electronic Hardware Systems Communications Trans-Lunar Phase Joshua Elmshaeuser Communications 1

AAE450 Spring 2009 Digital Camera & Antenna Amplifier  Thermo Scientific CID8825D (730 x 512) –Operating Temperature: 0 °C to +40 °C –Radiation Tolerant up to: 3.06 MRad –Mass: 3.12 kg –Power: 18 Watts  SSTL S-Band High Power Amplifiers (Lander use) –Operating Temperature: -20 °C to +50 °C –Radiation Tolerant up to: 5 kRad –Mass: 1250 g –Dimensions: 57 x 135 x 190 mm –Power: 33 Watts Joshua Elmshaeuser Communications 2

AAE450 Spring 2009 Antennas  SSTL S-Band Patch Antenna (Rover) –Operating Temperature: -20 °C to +50 °C –Radiation Tolerant up to: 50 kRad –Mass: 80 g –Dimensions: 82 x 82 x 20 mm  SSTL S-Band Quadrifilar Helix Antenna (Lander) –Operating Temperature: -20 °C to +50 °C –Radiation Tolerant up to: 5 kRad –Mass: 500 g –Dimensions: 100 x 100 x 500 mm Joshua Elmshaeuser Communications 3

AAE450 Spring 2009 Details on Radiation Hardening  Contacted representative from SAVE inc. –Research in radiation to devices –Testing device would cost $50k –Could self test for less ~ $25k –Said that off the shelf devices are hardier than most would think Joshua Elmshaeuser Communications 4

AAE450 Spring 2009 Details on Antennas and Amplifier  Company – Surrey Satellite Technology LTD (SSTL) –Based out of the UK –Awaiting reply on cost and Power consumption estimates –Currently have several systems operating in space – [Name] [Group] 5