Orbital Transfer Vehicle (OTV) Power Systems

Slides:

Advertisements

Similar presentations

Lunar Lander Power Systems

Advertisements

AAE450 Spring 2009 Final Presentation Draft Slides Description: Some draft slides and ideas 3/26/09 Kris Ezra Attitude 1.

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 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12,

AAE450 Spring 2009 Project X pedition Final slides outline for Orbital Transfer Vehicle Propulsion Week 11 Presentation Thursday, March 26, 2009 Brad Appel.

AAE450 Spring 2009 Tony Cofer Power Group TLI Phase 03/05/09 Power Limitations for Arbitrary Payload Tony Cofer] [Power] page 1.

AAE450 Spring 2009 Translunar Orbit Transfer Vehicle (OTV): Propulsion System Setup for 100g & 10 kg Case Launch Vehicle Selection for Arbitrary Case Thermal.

AAE450 Spring Gram Mission Integration and Model Korey LeMond STRC/THM/INTEG GL [Korey LeMond] [STRC/THM/INTEG/CAD GL, OTV Phase] 1.

Project X pedition Spacecraft Senior Design – Spring 2009

AAE450 Spring 2009 Mass Savings and Finite Element Analysis (FEA) Preparation for Orbital Transfer Vehicle (OTV) 100 gram Case Tim Rebold STRC [Tim Rebold]

AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.

AAE450 Spring Lunar Descent Attitude Control Analysis Christine Troy Assistant Project Manager Webmaster Lunar Descent Attitude Control Analysis.

AAE450 Spring 2009 X 0 Power System Solar - Battery Solar arrays Tony Cofer- Power System.

AAE450 Senior Spacecraft Design Catherine Frey Week 4: February 8 th, 2007 Propulsion Group, Transfer Vehicle Group Transfer Vehicle Combustion Chamber.

Durham University Solar-Powered Car

Cooling System Architecture Design for FCS Hybrid Electric Vehicle

CR1000s are only one part of a data acquisition system. To get good data, suitable sensors and a reliable data retrieval method are required. A failure.

Lesson 25: Solar Panels and Economics of Solar Power

IPS Rev 1.0 Ken Lutz University of California, Berkeley

There are four symbols that every competent EE must be able to manipulate with Consummate Skill: e j  $ Energy = $ Power = “Cash Flow” =

1 Electrical Power System By Aziatun Burhan. 2 Overview Design goal requirements throughout mission operation: Energy source generates enough electrical.

Hybrid Wind & Solar Generation Project

Power Sources Utility: 60 Hz - 120/240 V - 1,2,3 Phase Fixed Voltage Batteries Fuel Cells Photo Voltaic Thermionic Generators AC generators (“Alternators”)

1 DESIGN OPTIMIZATION OF A SOLAR RACE-CAR WITH ENERGY MANAGEMENT APPROACH O.Ustun, M.Yilmaz, C.Gokce, U.Karakaya, R.N.Tuncay İstanbul Technical University.

AAE450 Spring 2009 Kelly Leffel 3/0509 Structures and Thermal Lunar Descent Phase Lander Integration Lander Thermal Control Kelly Leffel Structures and.

Power Quality Assessment on Wind Energy systems Presented By vivek kumar(pe610)

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.

AAE450 Spring 2009 Preliminary Trans-Lunar Analysis [Levi Brown] [Mission Ops] January 29,

AAE450 Spring 2009 Lunar Lander Power Systems Thursday March 12 th Adham Fakhry Power Group Lunar Lander Descent Night Thermal.

AAE450 Spring 2009 Final Slides Lunar Lander Structure April 9, 2009 Lunar Descent Phase Group [Ryan Nelson] [STRC] 1.

AAE450 Spring 2009 Brian Erson Attitude Control Systems Trans Lunar Phase Alternative Design Comparison [Brian Erson] [Attitude] 1.

AAE450 Senior Spacecraft Design Project Aquarius Rogge - 1 Courtney Rogge Week 6: February 22 nd, 2007 Power Group Nuclear Power Capabilities TV Nuclear.

AAE450 Senior Spacecraft Design Ryan Scott Week 1: January 18 th, 2007 Power Group Leader Solar Panels / Transfer Vehicle / Capsule.

AAE450 Spring 2009 Lunar Night and Lander Power System Adham Fakhry February 26th, 2009 Power Group Lunar Descent Phase Passive Thermal Control for Lunar.

Power Systems Design Principles of Space Systems Design U N I V E R S I T Y O F MARYLAND Power Systems Design Definitions of energy and power Power generation.

Density Where Mass meets Volume. What to Know How do I convert units in Density Problems? ConversionExamples 1000 g = 1 kg a.1500 g = ______ kg b

AAE450 Spring 2009 Final Lander Volume and Mass 10kg, 100g, Arbitrary March 12, 2009 Lunar Descent Phase Group [Ryan Nelson] [STRC] 1.

AAE450 Spring 2009 Power Systems for Lander Adham Fakhry [Adham Fakhry] [Power]

Micro Arcsecond X-ray Imaging Mission Pathfinder (MAXIM-PF) Mechanical George Roach Dave Peters 17 May 2002 “Technological progress is like an axe in the.

AEON 4000 Including the SMPS 4000 rectifier and the AEON Gold Alarm & Monitoring Unit.

 The acronym KERS stands for Kinetic Energy Recovery System.  The device recovers the kinetic energy that is present in the waste heat created by the.

Power Philip Luers NASA/GSFC Code 561 August 16-17, 2005.

Cost Comparison of Higher Parking Orbit Scale up for Arbitrary Payload

Spacecraft Power Systems

Photovoltaic Systems Engineering Electronic Control Devices (ECDs)

Photovoltaic Systems Engineering

Photovoltaic Systems Engineering Session 15 Stand-Alone PV Systems

Department of Electrical Engineering

[Cory Alban] [Mission Ops] [Locomotion]

An alternative to storing electrical energy in batteries is storing energy in the form of hydrogen. Hydrogen cam be easily generated by electrolysis.

Week 6 Presentation Thursday, Feb 19, 2009

Attitude, Lunar Transfer Phase

Ian Meginnis January 29, 2009 Group Leader - Power Systems

Structures and Thermal Lunar Descent Phase

By: Josh Lukasak Attitude Group Lead Lunar Descent Phase Manager

Final Presentation Slides

Solomon Westerman Week3 1/29/09

[Kara Akgulian] [Mission Ops]

Photovoltaic Systems Engineering

Week 4 Presentation Thursday, Feb 5, 2009

Photovoltaic Systems Engineering Session 07 Photovoltaic Systems:

Final Slides Attitude Control System (ACS) – Lunar Transfer

Solar Energy Commercialization Utility Scale Solar Development

Critical Design Review

Ian Meginnis January 29, 2009 Group Leader - Power Systems

Presentation transcript:

Orbital Transfer Vehicle (OTV) Power Systems Ian Meginnis February 12, 2009 Group Leader - Power Systems Phase Leader - Translunar Injection Ian Meginnis Power Systems

OTV Solar Arrays Two, circular Ultraflex solar arrays from Able Engineering Based on 2kW power needs: Total Deployed Area = 6.67m2 Total Stowed Volume = 0.068m3 Total Mass = 13.3kg Total Cost = $2 million Structural Requirements Stowed Maximum Acceleration: 25g normal; 30g lateral Deployed Maximum Acceleration: 0.1g (all axes) Lunar lander batteries can support 2kW of OTV operations for up to 50mins during periods of darkness Ian Meginnis Power Systems

OTV Power Configuration PPU (Electric Propulsion) PCDU Battery (LL) 100V DC-DC Converters Individual OTV Components Solar Array <200V Solar Array Acronym Definitions: PCDU - Power Conditioning and Distribution Unit PPU - Power Processing Unit LL - Lunar Lander DC - Direct Current Note: Not to scale Ian Meginnis Power Systems

Backup Slide Calculation of Solar Array Dimensions Solar Array Mass: Total Power Consumption: 2kW Solar Array Power Density: 150W/kg 2000W / 150W/kg = 13.3kg Solar Array Storage Volume: Thickness: 0.102m Height: 0.326m Radius: 1.03m 0.102m x 0.326m x 1.03m = 0.0342m3 Solar Array Cost: Cost/Watt: $1000/W 2000W x $1000/W = $2 million Ian Meginnis Power Systems

Backup Slide (cont.) PCDU Specifications Terma Power Management and Distribution System Power Capacity: 2kW Voltage Output: 100V Mass: 14kg Volume: 0.0247m3 Ian Meginnis Power Systems

Backup Slide (cont.) DC-DC Converter Information 100 VDC Input Spacecraft Bus, Radiation Hardened Produced by Modular Devices Incorporated Available power output: 6.5W-80W Various output voltages available Separate DC-DC converter used for each device All converters integrated into single-box design Ian Meginnis Power Systems