Instrument Information |
|
IDENTIFIER | urn:nasa:pds:context:instrument:ds1.ids::1.0 |
NAME |
ION PROPULSION SYSTEM DIAGNOSTIC SUBSYSTEM |
TYPE |
PLASMA WAVE SPECTROMETER |
DESCRIPTION |
Instrument Overview =================== A suite of 12 diagnostic sensors was integrated into the Ion Propulsion System (IPS) Diagnostic Subsystem (IDS). Two of the instruments were the plasma wave antenna and search coil. Time domain and spectrometer data were obtained from both sensors. Scientific Objectives ===================== The NASA Solar Electric Propulsion (SEP) Technology Applications Readiness (NSTAR) ion thruster operating aboard Deep Space 1 generates an environment that includes electrostatic, magnetic and electromagnetic fields, charged particles, and neutral particles. The thruster environmental components, in combination with the natural space environment and the space vehicle, produce the 'induced environment.' The induced environment has the potential of impacting the performance of spacecraft subsystems or science sensors. The objective for the Ion Propulsion System (IPS) Diagnostics Subsystem (IDS) flown on DS1 was to characterize these environments within significant resource constraints. Since the measured effects of the IPS on the spacecraft environment proved to be benign, the IDS was reprogrammed during flight to collect solar induced wave data and signals caused by dust impact events during the encounter. Detectors ========= Search Coil Magnetometers - Two single-axis search coil magnetometers were mounted on the boom. One search coil is a new technology miniaturized sensor developed in the JPL MicroDevices Laboratory that uses a field rebalance technique for measurement. The second search coil was a build-to-print of the Orbiting Geophysical Observatory (OGO-6) single-axis sensor manufactured by Space Instruments, Inc., Irvine, California. The second search coil sensor was apparently damaged at the launch site by large AC fields and was inoperable during the DS1 mission. Flight measurements were performed with a measurement bandwidth over 10 Hz to 50 kHz. The full-scale range at 200 Hz is 100 nT with a resolution of 1 pT. The AC magnetic fields were characterized as a discrete power spectrum with four measurement intervals per decade. The transient waveform for 'events' was also captured with a sampling rate of 20 kHz for 500-msec windows. The transient recorder was commanded at prescribed intervals. Plasma Wave Antenna - A simply deployed dipole plasma wave antenna (PWA) with adjustable-gain preamplifier was mounted onto the boom. The PWA is a pair of low-mass Ni-Ti shape-memory alloy (SMA) metallic strips with a tip-to-tip separation of 2 m. The PWA deployment occurs upon exposure of the stowed SMA coiled ribbon to the Sun. Within 2 hours, the PWA antenna slowly extends to its deployed position. The PWA is connected to a low-noise preamplifier that was built by TRW, Redondo Beach, California. Flight measurements were performed in a low-frequency domain of 10 Hz to 100 kHz and a high-frequency domain of 100 kHz to 30 MHz. The low-frequency domain is characterized by a voltage-swept band pass filter with a minimum of four measurements per decade with an amplitude range of 100 micro-V/m to 1000 mV/m. The high-frequency domain is characterized with a minimum of four measurements per decade with the same amplitude range as the low-frequency domain. Transient waveform measurements were performed at a 20-kHz sampling rate with a 500-msec circular buffer. Electronics =========== IDS Architecture - IDS consists of two interconnected hardware units: a Diagnostics Sensors Electronics Unit (DSEU) and a Remote Sensors Unit. The IDS is an integrated package with one +28VDC and dual MIL-STD-1553 serial communications interface to the DS1 spacecraft. The DSEU has 2 data sampling systems, a contamination monitor, and a fields monitor (processor). The data provided was processed using a Fields Measurement Processor (FMP). The FMP consists of 3 boards: processor, spectrometer, and magnetometer. The magnetometer is not discussed here. The spectrometer board amplifies both the search coil and plasma wave signals for time domain sampling and provides two identical low frequency, voltage controlled tuned band passed filters. These two filters yield the search coil and plasma wave data. For the plasma wave sensor, the spectrometer has a bank of selectable high frequency band pass filters. Operational Modes ================= The IDS contains two separate processor elements: the DSEU microprocessor and the fields measurement processor (FMP)[HENRYETAL2000]. The DSEU microprocessor supports the communications interface with DS1, controls serial communications with the FMP, and digitizes and controls the sensors within the RSU. The IDS operates as a remote terminal on the DS1 MIL-STD-1553 serial bus. Telemetry from the RSU sensors is collected on 2- second intervals and placed in selected 1553 subaddresses for transmission to DS1. Configuration messages are transmitted to the DSEU to select active sensors within the RSU and FMP and to establish sweep ranges and gains for these sensors. Configuration messages to the FMP are passed through the DSEU to the FMP directly. The DSEU polls the FMP for data at half-second intervals. In the typical FMP scan mode operation, a block of sensor data is transmitted at 16-second intervals. Occasionally, the FMP will transmit 0.5-second waveforms sampled at 20 kHz from the plasma wave and search sensors and 120 s 20 Hz from the flux- gate magnetometers. These 'burst' events can be commanded or initiated via internal triggering within the FMP. Location ======== IDS was located adjacent to the ion engine on the DS1 spacecraft. Measured Parameters =================== The IDS Plasma Wave Spectrometer characterized the electrostatic wave and electromagnetic noise environments produced by the IPS and other DS1 subsystems. A large volume of both spectral and time-domain data were obtained throughout the DS1 mission, especially during IPS operations. There is not a direct correlation of noise amplitude with IPS operating power. The IPS noise levels are bounded as follows: o IPS E-field continuous noise: < 1 V/m, < 15 MHz. o IPS E-field transient: < 2 V/m for < 1 ms. o IPS B-field continuous noise: < 10 micro-T, < 10 kHz. o IPS B-field transient: < 200 micro-T for < 2 ms. Limits for the major DS1 subsystem noise sources, namely the hydrazine reaction control subsystem (RCS) thrusters and engine gimbal actuators (EGAs), are bounded by: o RCS thruster E-field transient: < 5 V/m for < 10 ms. o RCS thruster B-field transient: < 200 micro-T for < 40 ms. o EGA B-field continuous noise: < 10 micro-T, at 100 Hz. o EGA B-field transient: < 100 micro-T for < 1 s. References ========== Henry, M.D., D.E. Brinza, A.T. Mactutis, K.P. McCarty, J.D. Rademacher, T.R. vanZandt,R. Johnson, G. Musmann, and F. Kunke, NSTAR Diagnostics Package Architecture and Deep Space 1 Spacecraft Event Detection, IEEE 2000 Aerospace Conference Paper, 11.0502, 2000. |
MODEL IDENTIFIER | |
NAIF INSTRUMENT IDENTIFIER |
not applicable |
SERIAL NUMBER |
not applicable |
REFERENCES |
Brinza, D.E., M.D. Henry, A.T. Mactutis, K.P. McCarty, J.D. Rademacher,
T.R. vanZandt, P. Narvaez, J.J. Wang, B.T. Tsurutani, I. Katz, V.A. Davis,
S. Moses, G. Musmann, F. Kuhnke, I. Richter, C. Othmer, and K.-H.
Glassmeier, An Overview of Results from the Ion Diagnostics Sensors Flown
on DS1, AIAA-2001-0966, 2001. Henry, M.D., D.E. Brinza, A.T. Mactutis, K.P. McCarty, J.D. Rademacher, T.R. vanZandt, R. Johnson, G. Musmann, and F. Kunke, NSTAR Diagnostics Package Architecture and Deep Space 1 Spacecraft Event Detection, IEEE 2000 Aerospace Conference Paper, 11.0502, 2000. |