ELECTRICAL TEST PROCEDURE (ETP) FOR ECU SPACECRAFT EMULATOR GSE SN: 001. GP-B Procedure P0847 Rev -

Transcription

1 0847 Rev. W. W. Hansen Experimental hysics Laboratory STANFORD UNIVERSITY STANFORD, CALIFORNIA Gravity robe B Relativity Mission ELECTRICAL TEST ROCEDURE (ET) FOR ECU SACECRAFT EMULATOR GSE SN: 001 G-B rocedure 0847 Rev - repared by: Jennifer Bower Gyroscope Suspension System (GSS) Group Approved by: William Bencze RE, Gyroscope Suspension System (GSS) Group Approved by: Dorrene Ross G-B Quality Assurance

2 ECU GSE ET 0847 Table of Contents: 1.0 Revision History Scope: Reference Documents QA rovisions: Test ersonnel General Instructions Hardware Safety Requirements: Test Equipment Device Under Test: ower On: Spacecraft ower Emulation Verification HLD Driver Emulation Verification: Revision History Rev Level Comments/notes Revised By - First release of this test procedure 5/30/01 J Bower age 2 of 11

3 ECU GSE ET Scope: 2.1. This procedure details the functional tests required for ECU Spacecraft Emulator Ground Support Equipment (GSE) prior to use with ECU flight hardware Successful completion of this test certifies this device as functional and safe for use with ECU flight hardware. 3.0 Reference Documents 3.1. Electrostatic Discharge Control rogram for rotection of Electrical and Electronic arts, Assemblies, and Equipment, MIL-STD ECU to Spacecraft Interface Wiring Diagram, 8A QA rovisions: 4.1. Upon completion of this procedure, the ECU manager and the G-B QA manager shall certify her/his concurrence that the procedure was performed and accomplished in accordance with the prescribed instructions by signing and dating his approval at the end of this procedure. 5.0 Test ersonnel This test procedure is to be conducted only by the following personnel: 5.1. William Bencze 5.2. Scott Smader 5.3. Lo Van Ho 5.4. Jennifer Bower 5.5. Rick Bevan General Instructions 6.1. Redlines can be initiated by the test personnel listed in Section 5.0 and must be approved by QA Test operators shall read this procedure in its entirety and resolve any apparent ambiguities prior to beginning this test Any nonconformance or test anomaly should be reported by a Discrepancy Report. Refer to the Quality lan, 0108, for guidance. Do not alter or break test configuration if a test failure occurs; notify quality assurance Only the following persons have the authority to exit/terminate this test or perform a retest: test operators listed in Section 5.0 and G-B QA. age 3 of 11

4 ECU GSE ET Hardware Safety Requirements: 7.1. This assembly is ESD sensitive; special care shall be exercised per the Electrostatic Discharge Control rogram for rotection of Electrical and Electronic arts, Assemblies, and Equipment, MIL-STD Ensure that power is removed from cable assemblies before connecting or disconnecting cable connectors Connector savers are to be used on all flight connector interfaces unless otherwise specified Examine all mating connectors before attempting to mate them. Remove any foreign particles. Look for any damaged pins or sockets. Do not force the coupling action if excessive resistance is encountered. Ensure that keyways are aligned when mating connectors. age 4 of 11

5 ECU GSE ET Test Equipment The following support hardware, test equipment, or software will be used and the applicable information for the instruments shall be recorded below. Hand-written additions to this list may be made in the space provided. Equipment Description Make Model SN Cal Due 1. ECU Spacecraft Emulator ECU NA (this doc) 2. Multimeter Fluke 3. Oscilloscope Tektronix 4. ower Supply (in SC emulator) H 6653A in GSE Cable (2) in GSE Cable Device Under Test: Record the serial number of the Device Undergoing Test, or DUT. ECU Spacecraft emulator assembly SN: Test Operator: Name: Start of test: : Time: age 5 of 11

6 ECU GSE ET ower On: Note: All handling of this DUT shall be performed using ESD control methods, as outlined in MIL- STD Unit shall be inspected at an ESD certified station. Wrist straps and/or heel grounding straps shall be used. ower Distribution [1] SC Emulator [2] Back panel J12 1 J13 1 J12 J13 A-Side WR (D9) B-Side WR (D9) Rack-mount C [3] J27 1 J27 HLD (D44) H ower Supply [4] 115 VAC J1 ECU GSE-1 Figure 1: ECU Rack and Cables /F Notes Turn on unit via the circuit breaker on the ower Distribution box [1] Boot the C [3] Turn on power to H DC ower Supply [4] Run LabView ECU Test program from desktop Record version number of LabView ECU Control anel. Version: Turn on power to SC Emulator [2] In LabView, click ower Settings button to ON Verify 28V on H ower Supply [4] ress Undervolt Reset on SC Emulator [2] age 6 of 11

7 ECU GSE ET 0847 Spacecraft ower Emulation Verification Verify that the power panel on the LabView control panel is set for DC: 28.0 V, AC: 0.0 V Under ower Settings, use down arrow to decrease DC Voltage (master voltage) until SC Emulator Undervolt indicator lights. Record voltage Return the master voltage to 28V and press Undervolt Reset Click both ower Status control buttons to indicate ON. Verify each of the indicator lights on the SC Emulator are lit Click both ower Status control buttons to indicate OFF. Verify each of the indicator lights on the SC Emulator is not lit Using a multimeter, verify the table below for the J12 and J13 connectors. Use the following pin combinations for the voltage measurements: ositive: Negative: in 2 in 7 in 1 in 6 /F Notes Undervolt Voltage: ower Status Configurations J12 J13 /F ECU A-side 28V ECU B-side 28V in 2 in 1 in 2 in 1 OFF OFF ON OFF OFF ON All voltage tolerances: ± 0.20 V age 7 of 11

8 ECU GSE ET HLD Driver Emulation Verification: J27: connect scope negative terminal to pin 32 and positive terminal to the pins indicated in the table below Verify the voltage pulses in the table below for the given HLD transitions. /F Notes HLD Transition /F A-Side ower Converters (ON) A-Side ower Converters (OFF) B-Side ower Converters (ON) B-Side ower Converters (OFF) A-Side Heat ulse Enable (ON) A-Side Heat ulse Enable (OFF) B-Side Heat ulse Enable (ON) B-Side Heat ulse Enable (OFF) age 8 of 11

9 ECU GSE ET Verify the 6 HLDs tested above indicate OFF Verify the voltage pulses in the table below for the given HLD transitions. Two voltage pulses should occur for each HLD transition: one when the mouse is pressed, and one when it is released. /F Notes HLD Transition /F All ECU to A ower A-Side to B ower B-Side to B ower A-Side All Enable B-Side All Enable A-Side Dewar heat disable B-Side Dewar heat disable A-Side SIA heat disable B-Side SIA heat disable A-Side GMA power disable B-Side GMA power disable A-Side UV disable B-Side UV disable A-Side 1553 B-Side 1553 indicates 28 V pulse; blank indicates no pulse. age 9 of 11

10 ECU GSE ET 0847 I certify that this procedure was performed in whole and that the data recorded above is complete and accurate. Test Engineer This is to certify that the information obtained under this test procedure is as represented and the documentation is completed and correct. ECU Representative Quality Assurance age 10 of 11

11 ECU GSE ET 0847 ECU Spacecraft Emulator Tested on: Retest by: By: er 0847 Rev Stamp: ECU Spacecraft Emulator Tested on: Retest by: By: er 0847 Rev Stamp: ECU Spacecraft Emulator Tested on: Retest by: By: er 0847 Rev Stamp: age 11 of 11