LlSA Pathfinder PROPULSION MODULE MECHANICAL INTERFACE CONTROL DOCUMENT. UK EXPORT CONTROL RATING : 9E001 Rated By : K. Tomkins.

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1 ~. ~~~ EADS+ ASTRIUM LlSA Pathfinder Page 1 of 24 PROPULSION MODULE MECHANICAL INTERFACE CONTROL DOCUMENT CI CODE: UK EXPORT CONTROL RATING : 9E001 Rated By : K. Tomkins Prepared by:... ~~~ ~ ~... ~~~~ Date: ,..... C?3.. n K. Tomkins Checked by: N. Dunbar Authorised by: h ~.. ~... ~ e M. Back/- ' '%&Lr w No UK expo cence required -These documents will require an exp licence if expork from the EU 0 EADS Astrium Limited 2005 EADS Astrium Ltd owns the copyright of this document which is supplied in confidence and which shall not be used for any purpose other than that for which it is supplied and shall not in whole or in part be reproduced, copied, or communicated to any person without written permission from the owner. EADS Astrium LimM, Registered in England and Wales No Registered office: Gunnels Wood Road. Stevenage. Hertfordshire, SGI ZAS, England Prowlsion Mcdule - MlCD.doc

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3 Page 3 of 24 CONTENTS 1. SCOPE DOCUMENTS Applicable Documents Reference Documents OVERVIEW System Requirements CATIA Models Static Test Configuration PRM CONFIGURATION PROPULSION MODEL CATIA MODEL EQUIPMENT STATUS INTERFACE & CONFIGURATION DRAWINGS Propulsion Module Interface Drawings Science Spacecraft Configuration Drawings THRUSTER LOCATIONS EQUIPMENT BOLT DEFINITION APPENDICES Appendix 1 - Axes Systems Appendix 2 Propulsion Module Interface Requirement Drawings Appendix 3 Science Spacecraft Configuration Drawings...20 Propulsion Module - MICD.doc

4 Page 4 of 24 TABLES Table 3-1 : SRS Configuration Requirements Verification...7 Table 3-2 : LISA Pathfinder Subcontractors...8 Table 5-1 : Propulsion Module CATIA Model Evolution...10 Table 6-1 : Propulsion Module Equipment Dimensions...11 Table 7-1 : Propulsion Module Interface Requirement Drawings...12 Table 7-2 : Science Spacecraft Configuration Drawings...12 Table 8-1 : Thruster Locations & Orientations...13 Table 9-1 : Propulsion Module Equipment Bolt Definition...14 Table 10-1 : PRM Axes Systems...16 FIGURES Figure 4-1 : Propulsion Module Configuration...9 Propulsion Module - MICD.doc

5 Page 5 of SCOPE This document defines and controls the mechanical interfaces for the LISA Pathfinder Propulsion Module. Propulsion Module - MICD.doc

6 Page 6 of DOCUMENTS 2.1 Applicable Documents The Applicable Documents are listed below, and are referenced in the text with the acronym AD-x. AD-1 Propulsion Module Requirement Specification S2.ASU.RS Reference Documents The Reference Documents are listed below, and are referenced in the text with the acronym RD-x. RD-1 Spacecraft Requirement Specification (SRS) RD-2 Acronyms, Abbreviations & Terminology S2.ASU.RS.2001 S2.ASU.LI.1006 Propulsion Module - MICD.doc

7 Page 7 of OVERVIEW 3.1 System Requirements The following sub-sections assess each of the requirements defined in the SRS, RD-1, which are applicable to the configuration aspects of the LISA Pathfinder Launch Composite. SRS REF NUMBER SRS-197 SRS-67 SRS-859 SRS-1157 REQUIREMENT DESCRIPTION The PRM main function shall be to contain a separate Chemical Propulsion System (CPS) that shall be commanded from the SCM. The CPS shall include: a) A Main Engine (ME) that shall allow orbital manoeuvring capacity of the composite. b) An Reaction Control Thrusters subsystem (RCT) that shall allow attitude manoeuvring capacity of the composite. The Launch Composite Principal Reference Frame, O_lc_mF is defined as: - Origin to be at the separation plane between Propulsion Module and launch vehicle, on the centreline of the cylinder; - Z-axis pointing up towards the Science Spacecraft; - X-axis parallel to the LTP centre-line with positive towards Test Mass 1; - Y-axis forms an orthogonal set. The Launch Composite Alignment Frame, O_lc_aF is defined as: - Origin TBD; - Z-axis pointing up towards the Science Spacecraft; - X-axis parallel to the LTP centre-line with positive towards Test Mass 1; - Y-axis forms an orthogonal set. The PRM reference frame shall be the same as the Composite reference frame as defined in SRS-67. VERIFICATION Appendix 2 Propulsion Module Interface Requirement Drawings Appendix 1 - Axes Systems Appendix 1 - Axes Systems Appendix 1 - Axes Systems Table 3-1 : SRS Configuration Requirements Verification Propulsion Module - MICD.doc

8 Page 8 of CATIA Models The configuration is controlled through CATIA models, these models being exchanged between the Prime Team (EADS Astrium Ltd) and the relevant Subcontractors shown in Table 3-2:- ELEMENT Propulsion Module SUBCONTRACTOR TBD Table 3-2 : LISA Pathfinder Subcontractors The LISA Pathfinder CATIA model represents the Flight Model (FM) configuration. The Structure Model (StM) configuration will be the same as the FM but for this the units represented by mass dummies. The LISA Pathfinder FM CATIA model comprises two separate major entities corresponding to the Science Spacecraft and Propulsion Module respectively. Each of these entities comprises numerous small models representing, for example, a spacecraft panel or unit. Each of these smaller models is combined using the Assembly Manager Tool (ASM) to enable viewing of the full satellite configuration. Constructing the model in this way ensures an efficient use of the computing system and also allows updates to individual models. Each issue of the FM CATIA model is a collection of smaller models at their various relevant issues. For Launch Composite configurations, elements are extracted from both the Science Spacecraft and Propulsion Module models as necessary. 3.3 Static Test Configuration The Static Test configuration comprises the basic flight structures for both the Propulsion Module and Science Spacecraft, assembled together using a flight representation clampband and separation system, and a representative set of mass dummies for all major equipments (on SCM only). This Static Test configuration is used for:- - the primary structure static test, - the Launch Composite/Launcher separation test, - and the Propulsion Module/Science Spacecraft separation test. Propulsion Module - MICD.doc

9 Page 9 of PRM CONFIGURATION The basic configuration of LISA Pathfinder Propulsion Module is shown Figure 4-1. The Propulsion Module Physical Reference Frame is defined in section 10.1, Appendix 1 - Axes Systems. Figure 4-1 : Propulsion Module Configuration Propulsion Module - MICD.doc

10 Page 10 of PROPULSION MODEL CATIA MODEL The CATIA model of the FM Propulsion Model exists as:- To be provided by supplier. The history of this model is as summarised in Table 5-1. ISSUE HISTORY 1 Table 5-1 : Propulsion Module CATIA Model Evolution Propulsion Module - MICD.doc

11 Page 11 of EQUIPMENT STATUS Table 6-1 provides a list of the customer furnished equipments accommodated on the Propulsion Module for which supplier MICDs are not available and provides the enveloping assumptions used for the configuration of the satellite. EQUIPMENT SCM to LV Umbilical Harness TBD DIMENSIONS Length Width/Diam Height x y z (mm) (mm) (mm) Unspecified Electronics Unit TBD Separation System TBD Table 6-1 : Propulsion Module Equipment Dimensions Propulsion Module - MICD.doc

12 Page 12 of INTERFACE & CONFIGURATION DRAWINGS 7.1 Propulsion Module Interface Drawings The Propulsion Module Interface Requirement Drawings are contained in section 10.2, Appendix 2 Propulsion Module Interface Requirement Drawings. The drawing status list shown in Table 7-1. TITLE DRAWING ISSUE Propulsion Module Interface Requirement Drawing DG Provisional PRM:Launch Vehicle Interface Drawing TBD TBD SCM:PRM Interface Drawing TBD TBD SCM to LV Umbilical Interface Drawing TBD TBD Unspecified Electronics Unit Interface Drawing TBD TBD Separation System Interface Drawing TBD TBD Table 7-1 : Propulsion Module Interface Requirement Drawings 7.2 Science Spacecraft Configuration Drawings The Science Spacecraft configuration drawings are contained in section 10.3, Appendix 3 Science Spacecraft Configuration Drawings. The drawing status list shown in Table 7-2. TITLE DRAWING ISSUE Closure & Shear Panels Equipped DG Provisional TBD TBD Table 7-2 : Science Spacecraft Configuration Drawings Propulsion Module - MICD.doc

13 Page 13 of THRUSTER LOCATIONS The location and direction cosines of all thrusters mounted on the Propulsion Module are defined in Table 8-1. All dimensions are relative to the LCM Physical Reference Frame, lc_mf (see Appendix 1 - Axes Systems). SYSTEM IDENTITY DIMENSIONS DIRECTION COSINE X_lc_mf Y_lc_mf Z_lc_mf cos x cos y cos z (mm) (mm) (mm) (-) (-) (-) Main Engine see Note 1 ME 0 0 TBD Thruster see Note 2 1A TBD TBD TBD TBD TBD TBD 1B TBD TBD TBD TBD TBD TBD 2A TBD TBD TBD TBD TBD TBD 2B TBD TBD TBD TBD TBD TBD 3A TBD TBD TBD TBD TBD TBD 3B TBD TBD TBD TBD TBD TBD 4A TBD TBD TBD TBD TBD TBD 4B TBD TBD TBD TBD TBD TBD Notes : 1 : nominal location and orientation taken at point of thrust application, the centre of the nozzle throat. Alignment accuracy to be better than ±0.1 and measured with a knowledge better than : nominal location and orientation taken at centre of nozzle exit plane. Alignment accuracy to be better than ±0.1 and measured with a knowledge better than 30. Table 8-1 : Thruster Locations & Orientations Propulsion Module - MICD.doc

14 Page 14 of EQUIPMENT BOLT DEFINITION The bolt sizes, numbers of holes and foot thickness for customer furnished equipments mounted on the Propulsion Module are defined in Table 9-1. EQUIPMENT NUMBER BOLT SIZE NUMBER FOOT OF UNITS OF HOLES THICKNESS SCM:LV Umbilical Harness TBD TBD TBD TBD TBD Electronic Unit TBD 1 TBD TBD TBD Separation System TBD 1 TBD TBD TBD Table 9-1 : Propulsion Module Equipment Bolt Definition Propulsion Module - MICD.doc

15 Page 15 of APPENDICES 10.1 Appendix 1 - Axes Systems Propulsion Module - MICD.doc

16 Page 16 of 24 Table 10-1 : PRM Axes Systems Propulsion Module - MICD.doc

17 Page 17 of Appendix 2 Propulsion Module Interface Requirement Drawings The drawing status is summarised in Table 7-1. Propulsion Module - MICD.doc

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20 Page 20 of Appendix 3 Science Spacecraft Configuration Drawings The drawing status is summarised in Table 7-2. Propulsion Module - MICD.doc

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24 Page 24 of 24 DOCUMENT CHANGE DETAILS ISSUE CHANGE AUTHORITY CLASS RELEVANT INFORMATION/INSTRUCTIONS A - - Initial issue for SCM Structure ITT Formal issue for EMITS release of SCM Structure ITT DISTRIBUTION LIST INTERNAL EXTERNAL S. Barraclough A. G. Jones LISA Pathfinder project, ESA P. Chapman M. Kemp LISA Pathfinder project, EADS Astrium GmbH, Friedrichshafen M. Davidson P. Kemp SCM Structure Supplier (TBD) N. Dunbar M. Sprague A. Elliott M. Stewart R. Fayard K. Tomkins K. Gould G. Viney R. Gray D. Wealthy D. Head Configuration Management Propulsion Module - MICD.doc