urn:nasa:pds:mess-rs-raw:calib:mess_rs_mdm 1.0 1.13.0.0 Product_Observational Simpson, R. A.; Reid, M. 2022 Table of momentum dump data during the MESSENGER mission 2022-05-20 1.0 Initial version for PDS4 2006-01-10T15:00:05.829Z 2015-04-18T21:22:59.375Z Calibration Calibrated Data characterizing each MESSENGER momentum dump MErcury Surface, Space ENvironment, GEochemistry, and Ranging Mission Mission urn:nasa:pds:context:investigation:mission.messenger data_to_investigation MESSENGER Spacecraft urn:nasa:pds:context:instrument_host:spacecraft.mess is_instrument_host MESSENGER flight systems Equipment Commands to and feedback from spacecraft systems urn:nasa:pds:messenger:document-rs:sis-mdm data_to_document MESS-V/H-RSS-1-EDR-RAWDATA-V1.0:MESS_RS_MDM data_to_derived_source_product PDS Geosciences Node The value of external_source_product_identifier is constructed from the PDS3 DATA_SET_ID, an ASCII colon character, and the PDS3 PRODUCT_ID. mess_rs_mdm.csv 2015-06-04T00:00:00 34932 71e1ef49824ea285e59306125a52daf4 MESSENGER Momentum Dump Maneuver File 0 PDS DSV 1 The Momentum Dump Maneuver (MDM) file contains information on each momentum dump maneuver and each orbit correction maneuver (OCM) All of these events were commanded angular momentum dumps (CMD); MESSENGER did not perform any autonomous momentum dumps. The primary purpose of this file was to supply information to the Navigation and Radio Science teams for use in their trajectory reconstruction analyses. This was an accumulating file with one row for each angular momentum dump. After each maneuver, a new MDM file with a new row was created; only the final version of the file is included in this archive. Each row includes the time of the maneuver and estimates of the initial and final angular momentum for each axis, the total change in velocity caused by the maneuver, and the change in mass. Two coordinate systems were used by the MESSENGER team: the spacecraft body coordinates used by the Guidance and Control (GC) engineers and the adaptor-ring (AR) coordinates used by the development engineers. The two systems differed only in the location of the origin: subtract 0.89662 meters from the Z coordinate to convert the s/c body coordinates to the adaptor-ring coordinates. This file provides the spacecraft center of mass in both coordinate systems. 198 Carriage-Return Line-Feed Comma 23 0 193 Command ID 1 ASCII_String 9 %9s An identifier for the momentum dump maneuver, enclosed in double quotes. Commanded Maneuver Dumps have the form CMDnnn or CMD nnn where nnn is a sequence number between 1 and 180. Orbit Correction Maneuvers have the form OCMnnx or OCM nnx where nn is a sequence number between 1 and 18 and x is an optional letter suffix. IBF Angular Momentum X 2 ASCII_Real 6 kg*m**2/s X component of the angular momentum in the initial body frame. IBF Angular Momentum Y 3 ASCII_Real 6 kg*m**2/s Y component of the angular momentum in the initial body frame. IBF Angular Momentum Z 4 ASCII_Real 6 kg*m**2/s Z component of the angular momentum in the initial body frame. FBF Angular Momentum X 5 ASCII_Real 6 kg*m**2/s X component of the angular momentum in the final body frame. FBF Angular Momentum Y 6 ASCII_Real 6 kg*m**2/s Y component of the angular momentum in the final body frame. FBF Angular Momentum Z 7 ASCII_Real 6 kg*m**2/s Z component of the angular momentum in the final body frame. Total Angular Momentum Change 8 ASCII_Real 5 kg*m**2/s Magnitude of the angular momentum change. First Thruster Firing Time 9 ASCII_Date_Time_DOY 22 %22s Time in UTC of the first thruster firing. Last Thruster Firing Time 10 ASCII_Date_Time_DOY 22 %22s Time in UTC of the last thruster firing. Thruster On Time 11 ASCII_Real 7 second The number of seconds that thrusters fired. Residual Delta-V X 12 ASCII_Real 8 mm/s The residual delta-V x-component in EME2000 coordinates. Residual Delta-V Y 13 ASCII_Real 8 mm/s The residual delta-V y-component in EME2000 coordinates. Residual Delta-V Z 14 ASCII_Real 8 mm/s The residual delta-V z-component in EME2000 coordinates. Mass Consumption 15 ASCII_Real 7 g The mass of fuel consumed during the maneuver. 999.99 Unused 16 ASCII_Real 3 An unused legacy field; set to 0.0. Spacecraft Mass 17 ASCII_Real 7 kg Spacecraft mass after the maneuver. 999.99 GC CM X 18 ASCII_Real 7 m Spacecraft center of mass after the maneuver; GC frame, x-component. 999.99 GC CM Y 19 ASCII_Real 6 m Spacecraft center of mass after the maneuver; GC frame, y-component. 999.99 GC CM Z 20 ASCII_Real 9 m Spacecraft center of mass after the maneuver; GC frame, z-component. 999.99 AR CM X 21 ASCII_Real 7 m Spacecraft center of mass after the maneuver; AR frame, x-component. 999.99 AR CM Y 22 ASCII_Real 6 m Spacecraft center of mass after the maneuver; AR frame, y-component. 999.99 AR CM Z 23 ASCII_Real 6 m Spacecraft center of mass after the maneuver; AR frame, z-component. 999.99