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.

Slides:



Advertisements
Similar presentations
Concept Overview for 2 mt Case “2 mt case”: integrated payloads of no more than 2 mt can be landed on the surface of Mars; extension of current Mars EDL.
Advertisements

Larry Phillips MAY 13th-17th, 2002 Micro Arcsecond Xray Imaging Mission: Pathfinder (MAXIM-PF) Launch Vehicle Information Final Version.
POLICY Space Export Controls Update Since Delivering the 1248 Report to Congress - April 2012 −Congress added language into the FY13 National Defense Authorization.
Aug.19, 1999 George T. Roach Integration Mission Design Center NASA- GSFC Code 543 Greenbelt, MD FAX
Payload Design Criteria for the Space Test Program Standard Interface Vehicle (STP-SIV) Mr. Mike Marlow STP-SIV Program Manager Payload Design Criteria.
Delta II –7920 Fitup Study Model TMA-56 f10 optics In-Line configuration Delta II Launch Vehicle 7920 H 10L Composite Fairing.
PLATO Phase A/B1 Status TOU Meeting Catania 28 Feb 2011 PLAnetary Transits and Oscillation of stars.
The Field of View of a Thin Lens Interferometer Baseline=2B F F=range from array center to detector  ’’  Nulled here. B B 2Bsin  Bsin  2 Channels.
AAE450 Spring 2009 Mass Savings and Finite Element Analysis (FEA) Preparation for Orbital Transfer Vehicle (OTV) 100 gram Case Tim Rebold STRC [Tim Rebold]
1 Atlas Truss Adapter & Launch Vehicle Details (all I can find in the Atlas Mission Planner’s Guide and Standard Interface Spec) David Robinson/543 7/18/08.
Spacecraft Design and Sizing Dr Andrew Ketsdever MAE 5595 Lesson 14.
Gateway to Space AJ - 1 Mechanical System Design & the StarLight Project Andy Jarski Mechanical Systems Engineer Ball Aerospace & Technologies.
Constellation Orion Visible Light Constellation Orion Infrared Light.
Final Version Bob G. Beaman May 13-17, 2002 Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Electrical Power System (EPS)
Level 1 - LRO Requirements ESMD-RLEP-0010
Final Version Wes Ousley Dan Nguyen May 13-17, 2002 Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Thermal.
1 Project Name Solar Sail Project Proposal February 7, 2007 Megan Williams (Team Lead) Eric Blake Jon Braam Raymond Haremza Michael Hiti Kory Jenkins Daniel.
Student Satellite Project University of Arizona Team Goals Design, Fabricate, and Analyze a Structure that will Support the Payload –Space Allocation of.
1 NASA’s Goddard Space Flight Center 2005/4/14 LRO/CRaTER Technical Interchange Meeting LRO Mechanical Systems Giulio Rosanova / /
1 祝飛鴻 衛星結構設計 5/31/ What are key constraints for the spacecraft structure design? 2.How the structure design is affected by other subsystems?
Bob G. Beaman June 28, 2001 Electrical Power System SuperNova / Acceleration Probe (SNAP)
NASA’s Goddard Space Flight Center LRO Integration and Test Joanne Baker GSFC Code 568 August 16-17, 2005.
Tielong Zhang On behalf of the CGS Team in the Institute of Geology and Geophysics, Chinese Academy of Science Spacecraft System and Payload China Geomagnetism.
Final Version Micro-Arcsecond X-ray Imaging Mission Pathfinder (MAXIM-PF) Eric Stoneking Paul Mason May 17, 2002 ACS.
Final Version John Martin May 13-17, 2002 Opening Comments Micro Arcsecond X-ray Imaging Mission, Pathfinder (MAXIM-PF)
© Lavochkin Association, 2013 Ganymede Lander mission overview.
Space-Qualified Hardware for the CALIPSO Lidar
Mechanical SuperNova/Acceleration Probe SNAP Study Dave Peters George Roach June 28, a man who's willing to make a decision in the first place can.
Final Version Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Mission Operations Tim Rykowski Jeffrey Hosler May 13-17, 2002.
Structures and Mechanisms Subsystems AERSP 401A. Introduction to Structural Estimation Primary Structure: load-bearing structure of the spacecraft Secondary.
DINO PDR 23 October 2015 DINO Systems Team Jeff Parker Anthony Lowrey.
AAE450 Spring 2009 Finite Element Analysis (FEA) for Orbital Transfer Vehicle (OTV) Tim Rebold STRC [Tim Rebold] [STRC] [1]
AAE450 Spring 2009 Support structure for Orbital Transfer Vehicle (OTV) Tim Rebold STRC [Tim Rebold] [STRC] [1]
LAUNCH VEHICLE DOWNSELECT A Wide Variety of Launch Systems Are Available Today Initial Downselect Constraint Based Upon UMRM Requirements Primary Payload.
Final Version Gabe Karpati May 17, 2002 Micro-Arcsecond X-ray Imaging Mission, Pathfinder (MAXIM-PF) System Overview.
MAXIM Periscope ISAL Study Highlights ISAL Study beginning 14 April 2003.
Henry Heetderks Space Sciences Laboratory, UCB
NASA/Air Force Cost Model presented by Keith Smith Science Applications International Corporation 2002 SCEA National Conference June
Final Version Dick Bolt Code 302 May 13-17, 2002 Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Mission Success.
March 2004 At A Glance autoProducts is an automated flight dynamics product generation system. It provides a mission flight operations team with the capability.
Structural Practices Principles of Space Systems Design U N I V E R S I T Y O F MARYLAND Structural Design Practices Payload interfaces to launch vehicles.
SE&I Pre-Proposal Meeting GSFC - JPL Systems Engineering Management Colleen McGraw.
N A S A G O D D A R D S P A C E F L I G H T C E N T E R I n t e g r a t e d D e s i g n C a p a b i l i t y / I n s t r u m e n t S y n t h e s i s & A.
1 衛星結構設計 祝飛鴻 5/25/  What are the main functions of structure subsystem?  Provide support all other subsystems and attach the spacecraft to launch.
1 System Architecture Mark Herring (Stephen Merkowitz Presenting)
Competition Sensitive Gabe Karpati June 28, 2001 SuperNova / Acceleration Probe (SNAP) System Overview.
Final Version Kequan Luu May 13-17, 2002 Micro-Arcsecond Imaging Mission, Pathfinder (MAXIM-PF) Flight Software.
N A S A G O D D A R D S P A C E F L I G H T C E N T E R I n t e g r a t e d D e s i g n C a p a b i l i t y / I n s t r u m e n t S y n t h e s i s & A.
John Martin April 5, 2001 SuperNova/ Acceleration Probe (SNAP) Introduction.
Final Version Gary Davis Robert Estes Scott Glubke Propulsion May 13-17, 2002 Micro Arcsecond X-ray Imaging Mission, Pathfinder (MAXIM-PF)
Wes Ousley June 28, 2001 SuperNova/ Acceleration Probe (SNAP) Thermal.
WFIRST Large-cell structure concept design Preview Work in progress 3/4/2016Robin Lafever1.
EXTP Accomodation Study Hong Bin, Zhang Long Institute of Spacecraft System Engineering. CAST Oct 27th, 2015.
THEMIS MRRSystems - 1 GSFC, Jan 5, 2007 Systems Engineering.
AAE 450 – Spacecraft Design 1 Solar Power & Docking Options Eric Gustafson 1/18/2005 Power group & docking sub-committee Solar power and autonomous docking.
X-ray Interferometer Mirror Module ISAL Study Pre-work Overview.
Ares V an Enabling Capability for Future Space Science Missions H. Philip Stahl, Ph.D. NASA MSFC.
Status of EPS Battery configuration finalized Solar panel layout –finalized Solar panel Substrate is ready for bonding EM – fabricated and Completed the.
Spacecraft Technology Structure
USNA Standard CubeSat Bus USNA-P1 CubeSat (USNA-14)
Technical Resource Allocations
ISAS Solar Physics Yohkoh (1991- ) Hionotori ( )
Systems Engineering Management
Henry Heetderks Space Sciences Laboratory, UCB
Micro-Arcsecond X-ray Imaging Mission Pathfinder (MAXIM-PF)
Orbital Transfer Vehicle (OTV) Power Systems
Week 4 Presentation Thursday, Feb 5, 2009
THERMAL CONTROL SYSTEM
CHEOPS - CHaracterizing ExOPlanet Satellite
<Your Team # > Your Team Name Here
Presentation transcript:

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 hands of a pathological criminal” Albert Einstein

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 2  Design Mission Unique spacecraft bus  HUB spacecraft consists of one Core S/C and 6 Petal S/C. These petal S/C will eventually become free flyer S/C.  Core S/C and Petal S/C are structurally the same.  A Detector spacecraft will attached to the HUB spacecraft then separate on orbit.  Accommodate a orbit Transfer Module (propulsion).  For payload accommodation use:  Use standard, highly successful mechanical designs with heritage, I.e. fixtures, bracket and fittings where possibly.  Minimize complex procedures.  Baseline Delta IV –5m x 14.3m launch vehicle shroud Overview

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 3 Launch Configuration Delta IV Heavy 5m X 19.1m fairing Delta IV 5m X 14.3m fairing P/L Sta Sta C.G. Sta Sta Sta Propulsion/Hub SpaceCraft Hub SpaceCraft/Detector SpaceCraft Propulsion/Hub SpaceCraft Delta IV 5m X 14.3m fairing

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 4 Mission Sequence Launch Transfer Stage Science Phase #1 Low Resolution 200 km Science Phase #2 High Resolution 1 km 20,000 km

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 5 Component Layout Hub Core & Petal Hub Core Hub Petal (6) LOS Laser Detector S/C Payload Adapter Fitting Optical Module (9) Optical Module (11) Comm Antenna (S/C to S/C 0.3 m)

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 6 Component Layout Detector Solar Array (4.5 m 2 ) Comm Antenna (Ground/SpaceCraft 0.5 m) Comm Antenna (S/C to S/C 0.3 m) Comm Antenna (Ground/SpaceCraft 0.5 m) LOS laser receiver CCD Camera CCD Electronics Thermal Shade (2.3 m 2 )

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 7 Structure Mass  Structure Mass  Hub Core – 57 kg  Hub Petal – 56 kg  Detector Payload Adapter Fitting – 12 kg  Detector – 85 kg

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 8  No spacecraft clearance issues  Ample clearance inside the launch vehicle fairing for all spacecraft appendages  Ample volume for spacecraft subsystems inside the bus  Mechanical interfaces:  Mission axial C.G. height within limits for launch vehicle PAF  Mission lateral C.G. are within limits for launch vehicle PAF  Mission stiffness for launch vehicle is TBD at this phase of the study  The concept of latching / unlatching the Freeflyer spacecraft has not been looked into for this phase of the study. However the concept has been used successfully many times in the past. One example is the MultiMission Spacecraft concept used for several satellites including, Solar Maximum, UARS, and EUVE. It has also been adapted for use on some Hubble components.  The actual spacecraft subsystems are not shown due to the time element. The spacecraft density is low enough to accommodate these volumes. Issues and Concerns

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 9 MECHANICAL BACK-UP SLIDES

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 10 Launch Vehicle Capabilities

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 11 Spacecraft Bus Densities

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 12 OPTIC HUB to FREE FLYER Latching Concept (example) This picture shows the latching / unlatching of Multi-Mission Modular Spacecraft. This basic concept could be used for the LAI-MAXIN “OPTIC HUB” to “FREE FLYER” configuration Free Flyer (s) Spacecraft Optic Hub Spacecraft

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 13 DELTA IV PAF C.G kg 2500 mm

Final Version MAXIM-PF 17 May 2002 Goddard Space Flight Centers Mechanical Page 14 Detector Mass Properties and Area’s 3.3^2m 1.9^2m 5.6^2m YZX