Pioneer Venus Orbiter (PVO) Retarding Potential Analyzer (ORPA) Data Bundle PVO Retarding Potential Analyzer (ORPA) High-Resolution Ion Data Collection Description PDS3_DATA_SET_ID = PVO-V-ORPA-5-ELE/ION/PHOTO/UADS-V1.0 START_TIME = 1978-12-05T15:01:43.176 STOP_TIME = 1992-10-07T19:58:02.490 PDS3_DATA_SET_RELEASE_DATE = 1997-09-01 PRODUCER_FULL_NAME = DR. WILLIAM C. KNUDSEN Collection Overview: ==================== The ORPA processed data consist of 4 file types: high resolution thermal electrons, high resolution superthermal electrons, high resolution ions, and a key parameters file at 12 second sampling. High resolution data are provided (for the entire orbit / only the portion of the orbit near periapsis) The sample rate of the high resolution data is variable and dependent on the telemetry rate and other operational considerations. All of these data are derived from the reformatted EDR data (RDR) which contains the raw I-V curve values. The moments of the distributions have been computed by a least squares fitting algorithm. Data from the entire mission (Dec 5, 1978 - Oct 7, 1992) are included in the data collections, where possible. The PV RPA is described in considerable detail by Knudsen et al. [1979-1980]. The principles of measurement are also described therein together with some of the factors affecting the accuracy of the derived quantities. Additional information on the theory of measurement by an RPA is presented by Knudsen [1966]. Sampling: ========= The ORPA instrument sweeps through the ion, electron, and photoelectron modes in an EIIIP sequence covering 5 spacecraft spin periods spending one spin period in each mode. A single retarding scan can be completed approximately 40 times in a spin period (0.3 sec). There are various algorithms by which the instrument can decide which scan to place in the telemetry frame. Please read the instrument description for more details. Data Processing: ================ High resolution data were processing by using an automated least squares fitting procedure. Values derived from these fits are provided in the archive. Some of the quantities contained in this submittal of RPA data to the PDS are erroneous because of bad least-squares fits to the I-V curves. These bad fits were not detected by the data reduction algorithms and have not been removed by a trained observer viewing the I-V curves and making an educated judgment. A trained observer, looking at an I-V plot, can rather quickly recognize data that will produce erroneous fit results but it is difficult to write an algorithm that can recognize all the possible situations and make the necessary adjustments. High Resolution Ions: ===================== The algorithm that scans the data in an ion I-V curve and computes the initial estimates of the ion quantities must also make a decision as to what ion mass is represented by a peak in DI [Knudsen et al., 1979; 1980]. The voltage at which the DI peak occurs for a given mass may be substantially smaller or larger than the nominal value because the Venus ionosphere is moving relative the planet with a velocity that can approach that of the spacecraft. Consequently, some peaks in DI have been assigned the wrong mass. The result is not only an erroneous concentration for that mass but also an erroneous ion velocity and total ion density. It is possible to recognize the incorrect assignments when comparing several I-V curves which are adjacent to each other in time, but the analysis algorithms are not this sophisticated. A few errors in ion quantities are present in the PDS files resulting from this difficulty. The uncertainties in the ion fitting process are included in an ancillary file. Missing values: =============== RPA quantities may be unavailable for assigning to a specific time tag for several reasons as follows: The spacecraft data format in use at the time may not have contained any words for the RPA. The RPA may have been turned off for power conservation reasons. The spacecraft telemetry bit rate and/or data format may have been such that an RPA I-V curve was recorded only at long time intervals. RPA data for an interval of time, including the time tag, has not been reduced. (RPA data at the time of this submission have been reduced for only a small time interval about periapsis: plus and minus approximately 15 minutes for the first 800 orbits, plus and minus approximately 30 minutes for orbits 800-1300, plus and minus 60 minutes for orbits 1300-2890.) Ancillary Files: ================ The ion fitting process involves both mass and velocity discrimination In many cases, one or the other parameter can not be well determined. As an ancillary component of the high resolution ion data files, we have included an ion uncertainties file, found in the data-ion-uncertainty collection. Some of the reasons for the uncertainties in the fits are described in the data-ion-uncertainty collection description document. Data: ===== The high resolution data files contain 17 ephemeris data columns necessary for the interpretation of the data. We will describe the ephemeris data columns and then place the phrase ephemeris(17) in the column name field of the file description. Ions (ASCII Table) ____________________________________________________________________ name type description ____________________________________________________________________ UTC Date Time YMD UTC at the time of the sweep IORBT Integer Orbit number TPER Integer Periapsis time (UT) KDAY Integer Periapsis day of year SWEEP Integer Unique sweep number TIMI String Unique time of sweep ALTI Real Altitude of sweep SZAI Real Solar Zenith Angle of sweep TOTI Real Total ion density H+ Real Hydrogen ion density HE+ Real Helium ion density O+ Real Oxygen ion density M29+ Real Sum density of CO+, NO+, N2+ ions O2+ Real O2+ ion density CO2+ Real Carbon dioxide ion density VELI Real Ion bulk velocity component in direction of RPA out TI Real Ion temperature PHII Real Spacecraft ground potential CSQ Real Chi square, goodness of curve fit FRSI Real Saturation ion current BCKI Real Background ion current EPH1 Real Roll spin angle (NRSC - RAMROLL)** EPH2 Real Spin period EPH3 Real Attitude of spin axis X (NRSC - ATTX)** EPH4 Real Attitude of spin axis Y (NRSC - ATTY)** EPH5 Real Attitude of spin axis Z (NRSC - ATTZ)** EPH6 Real Distance from Venus to center of spacecraft, Real X component (ICC_ECLP - XP1SFF)* EPH7 Real Distance from Venus to center of spacecraft, Real Y component (ICC_ECLP - YP1SFF)* EPH8 Real Distance from Venus to center of spacecraft, Real Z component (ICC_ECLP - ZP1SFF)* EPH9 Real Spacecraft velocity X component (ICC_ECLP - DXP1SF)* EPH10 Real Spacecraft velocity Y component (ICC_ECLP - DYP1SF)* EPH11 Real Spacecraft velocity Z component (ICC_ECLP - DZP1SF)* EPH12 Real Distance from Sun to center of spacecraft, Real X component (ICC_ECLP - XPHSFF)* EPH13 Real Distance from Sun to center of spacecraft, Real Y component (ICC_ECLP - YPHSFF)* EPH14 Real Distance from Sun to center of spacecraft, Real Z component (ICC_ECLP - ZPHSFF)* EPH15 Real Venus center velocity, X component (ICC_ECLP)* EPH16 Real Venus center velocity, Y component (ICC_ECLP)* EPH17 Real Venus center velocity, Z component (ICC_ECLP)* * Inertial Cartesian Coordinate System - Ecliptic ** Non-rotation spin coordinate system RPA Measured Quantities ======================= The PV RPA is described together with some of the principles of measurement in some detail by Knudsen et al. [1979,1980]. Many of the factors affecting accuracy are also described therein. We present in this section the quantities recorded on the PDS EDR data files following the four time tag quantities, their nominal uncertainty and measurement noise level, and additional limitations of the quantities. Table 1 lists the symbol, quantity, measurement range with units in which the quantities are quoted, noise level of measurement, and uncertainty of the measurement for the quantities reported by the RPA. We have included in the list of quantities the vector components of the ion bulk velocity even though we do not supply values in this Oct 1988 submission to PDS. TABLE 1 SYMBOL QUANTITY RANGE NOISE LEVEL UNCERTAINTY UTC UNIVERSAL TIME OF MEASUREMENT 0 - 8.7x10**7ms - 0.1s TOTI TOTAL ION DENSITY 10 - 1x10**7cm 10 cm-3 10% H+ HYDROGEN ION DENSITY 300 - 10**7cm-3 300 cm-3 10% O+ OXYGEN ION DENSITY 300 - 10**7cm-3 300 cm-3 10% M29+ SUM DENSITY OF CO+,N2+,NO+,O2+ 300 - 10**7cm-3 300 cm-3 10% CO2+ CARBON DIOXIDE ION 300 - 10**7cm-3 300 cm-3 10% TI ION TEMPERATURE 150 - 10,000 K - 10% VX ION BULK VELOCITY, X COMPONENT 0 - 7 km/s 0.4 km/s 0.4 km/s VY ION BULK VELOCITY, Y COMPONENT 0 - 7 km/s 0.4 km/s 0.4 km/s VZ ION BULK VELOCITY, Z COMPONENT 0 - 7 km/s 0.4 km/s 0.4 km/s F1I SATURATION ION CURRENT 0 - 1.3x10-4 A 1x10-12 A 1% BKGI ION BACKGROUND CURRENT 0 - 1.3x10-4 A 1x1O-12 A 1% VPI SPACECRAFT GROUND POTENTIAL -5 - +3 V - 0.1V TOTE ELECTRON DENSITY 102 - 107 cm 3 - - TE ELECTRON TEMPERATURE 300 - 20,000 K - 10% F1E SATURATION ELECTRON CURRENT 0 - 1.3x10-4 A 1x10-12 A 1% BKGE ELECTRON BACKGROUND CURRENT 0 - 1.3x10-4 A 1x10-12 A 1% VPTE SPACECRAFT GROUND POTENTIAL -5 - +3V - 0.1V N1 FIRST SUPRATHERMAL 0 - 107 cm-3 1 cm-3 20% ELECTRON DENSITY T1 FIRST SUPRATHERMAL 0 - 100 eV 0.2 eV 20% ELECTRON TEMPERATURE N2 SECOND SUPRATHERMAL 0 - 105 cm-3 1cm -3 20% ELECTRON DENSITY T2 SECOND SUPRATHERMAL 0 - 100 eV 0.2 eV 20% ELECTRON TEMPERATURE F1P SATURATION SUPRATHERMAL 0 - 1.3x10-4A 1x10-12A 1% ELECTRON CURRENT BKGP BACKGROUND SUPRATHERMAL 0 - 1.3x10-4A 1x10-12A 1% ELECTRON CURRENT VPPE SUPRATHERMAL ELECTRON 0 - +20V - 0.1 - 5V SPACECRAFT POTENTIAL UTC: UTC is the universal time in milliseconds assigned to the physical quantities recorded in this record. UTC will typically, but not always, lie within plus or minus 6 seconds of the time of day assigned to the time tag of this record. UTC should be accurate to within plus or minus 0.1 second. TOTI: TOTI is the total ion density of the plasma in cm-3 and is derived from the FORTRAN expression TOTI=FlI/(VN*e*Area) where F1I is the first ion current measured with zero retarding potential, VN is the component of ion bulk velocity parallel to the RPA axis derived from the lst-squares analysis when an analysis was possible, e is the electronic charge, and AREA is the effective area of the RPA collector (= 0.81 cm2). When a lst- squares analysis is not possible, VN is the component of the spacecraft velocity in ecliptic coordinates parallel to the RPA axis. H+: H+ is the hydrogen ion density. When the RPA is operating in one of its peaks mode, H+ will be detected and recorded only when its density is greater than approximately 10% of the sum of more massive ion densities. H+ can be the second most abundant ion and still not be recorded when the RPA is operating in its two peaks mode. The uncertainty of the H+ density also depends on its density relative to that of more massive ions. For an H+ density comparable to that of more massive ions, the accuracy should be of the order of 10%. The detection noise level for H+ is estimated at 300 cm-3. Additional discussion of the RPA ion peak detection capability and limitation is given by Miller et al. [1984]. O+: O+ is the oxygen ion density. It will be detected in the presence of more massive ions only when its density is greater than approximately 10% of the sum of more massive ions. The RPA does not resolve C+, N+, or 0+. We have assumed in our least-squares fitting that (CC+] + CN+])/CO+] is constant at 0.07, a value derived from PV ion mass spectrometer results. M29+: M29+ is the symbol assigned to the sum density of ions with mass near 32 atomic mass units, CO+, NO+, N2+, O2+. The RPA does not resolve these masses. In performing a least squares analysis, I have permitted the algorithm to adjust the density of a mass 32 ion and a fictitious mass 29 ion in fitting the measured DI peak corresponding to this mass range [Miller et al., 1984]. Measurements by the PV IMS have revealed that the density of NO+ can approach been that although the median density of each of the two masses varies with altitude in the expected way, on successive sweeps the least squares analysis can assign all the density to mass 29 for one sweep and to mass 32 in the next. For the PDS files, I have added the densities of the mass 29 and 32 ions and entered them under the symbol M29+. RPA results as well as IMS results show that the predominant ion mass in the group is 32 in most regions of the ionosphere. In future submissions, the sum density of this mass group will be submitted under the symbol m32+. C02+: C02+ is the density of the carbon dioxide ion. TI: TI is the ion temperature and is assumed to be the same for all ion masses. It is one of the adjustable variables in the least-squares analysis of ion sweeps. VX: VX is the x component of ion bulk velocity. The vector ion bulk velocity is derived from three component velocities parallel to the RPA axis measured in three successive spin periods of the PV spacecraft [Knudsen et al., 1980]. In deriving the vector, it is necessary to assume that the ion bulk velocity is uniform over the region of space traversed by the spacecraft in two spin revolutions of the spacecraft, a distance of about 250 km. The coordinate system in which VX, VY, and VZ are given will be specified when data are submitted. VY: VY is the y component of the bulk ion velocity. VZ: VZ is the Z component of the ion bulk velocity. F1I: F1I is the saturation (first) current measured in an ion I-V sweep. The retarding potential is programmed to be slightly negative of plasma potential during this measurement. F1I is measured relative to the ion current measured with the retarding potential equal to 37V positive [Knudsen et al. 1979]. BKGI: BKGI is the current to the RPA collector measured just before the beginning of an ion sweep with the retarding potential set at approximately +37V relative to plasma potential. VPI: VPI is the value of the spacecraft potential relative to plasma potential that is assumed to exist at the time of the ion sweep. The value is derived by interpolating between values of the spacecraft potential measured in the thermal electron mode. TOTE: TOTE is the total electron density derived from the thermal electron mode saturation current F1E. The formula used for this present PDS submission, in FORTRAN language, is: TOTE = 6.15E9*MAX(0, -3.5E-9 -F1E)~0.847 We consider this measure of the total electron density to be approximate and valid only while the PV spacecraft is within the ionosphere. TE: TE is the thermal electron temperature derived using equation (1) in Knudsen et al. [1980]. When the spacecraft is positive relative to plasma potential r a condition existing with the spacecraft in the sun and in a low density plasma the value of TE is representative of the secondary electrons trapped in the positive spacecraft potential well. F1E: F1E is the saturation electron current measured at the beginning of a thermal electron mode sweep. The front (retarding) grids are at a potential of +6.8 V relative to the spacecraft ground. BKGE: BKGE is the current measured by the RPA electrometer at the beginning of the thermal electron mode. The front (retarding) grids of the RPA are held at a potential of -4.6 V during the measurement. VPTE: VPTE is the spacecraft potential relative to the ambient plasma potential. It is derived from the thermal electron sweep data as described BY Knudsen et al. [1980]. When the spacecraft is in the solar wind and exposed to the sun, its potential is typically a few volts positive with respect to the solar wind plasma potential. VPTE loses its meaning in this situation. N1: N1 is the density of the low temperature Maxwellian electron distribution used to fit the suprathermal electron I-V curve [Knudsen et al., 1985]. T1: T1 is the temperature of the low temperature Maxwellian electron distribution. N2: N2 is the density of the high temperature Maxwellian electron distribution used to fit the suprathermal electron I-V curve [Knudsen et al., 1985] T2: T2 is the temperature of the high temperature Maxwellian electron distribution. F1P: F1P is the electron current measured by the RPA with zero retarding potential on the retarding grid. BKGP: BKGP is the electron current to the RPA with the retarding potential on the retarding grid equal to -58V. VPPE: VPPE is the spacecraft potential relative to the ambient plasma potential. When the spacecraft is in the solar wind and not in the Venus umbra, the spacecraft is positive, and the potential is inferred from the suprathermal electron I-V curve. When the spacecraft is within the ionosphere or in the Venus umbra, the potential is either estimated or taken from the potential measured in the thermal electron mode. Coordinate Systems: =================== Non-rotating spin coordinate system (NRSC): The roll angle of the roll reference object will be calculated in this coordinate system as well as the roll angles of the Fs, RIP, RAM, and NADIR signals. The non-rotating coordinate system (Wx, Wy, Wz) is centered at the spacecraft center of mass. The Wz-axis is parallel to the spacecraft spin axis. The Wx-Wy plane is perpendicular to the spacecraft spin axis. The Wx-Wz plane includes the Vernal Equinox of reference. Thus the Wx-axis is at the intersection of the plane perpendicular to the spacecraft spin axis and the plane containing the spin axis and the Vernal Equinox. Roll angles in this coordinate system are measured in the Wx-Wy plane from the roll reference direction. Inertial Cartesian Coordinate System - Ecliptic (ICC-ECLP) The Ecliptic Inertial Cartesian Coordinate System is defined for the reference epoch of 1950.0 The X-direction lies in the Ecliptic Plane and is positive away from the reference body towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference. The Y direction is measured outward from the center of the reference body, perpendicular to and east of the the X-axis, and lying in the ecliptic plane of reference. The Z direction is positive toward the north ecliptic pole of reference, from the center of the reference body." Confidence Level Overview: ========================== Some of the quantities contained in this submittal of RPA data to the PDS are erroneous because of bad least-squares fits to the I-V curves. These bad fits have not been detected by our current algorithms for reduction of the data and have not been removed by a trained observer viewing the I-V curves and making an educated judgment. References ========== Colin, L., Pioneer Venus Overview, IEEE Transactions on Geoscience and Remote Sensing, Vol GE-18, No. 1, pp. 5-10, 1980. R. O. Fimmel, L. Colin, and E. Burgess, 'Pioneering Venus: A Planet Unveiled', NASA SP-518, 1995. Knudsen W.C. , Evaluation and demonstation of the use of retarding potential analyzers for measuring several ionospheric quantities, J. Geophys. Res., vol. 71, pp. 4669-4678, 1966. Knudsen, W.C., J. Bakke, K. Spenner, and V. Novak, Retarding Potential Analyzer for the Pioneer Venus Orbiter, Space Sci. Inst., 4, 351, 1979. Knudsen, W.C., K. Spenner, J. Bakke, and V. Novak, Pioneer Venus Orbiter Planar Retarding Potential Analyzer Plasma Experiment, IEEE Trans. on Geosci. Remote Sens., 18, 1, 60, 1980. Nothwang, G.T., Pioneer Venus Spacecraft Design and Operation, IEEE Transactions on Geoscience and Remote Sensing, Vol GE-18, No. 1, pp. 5-10, January 1980.