DESCRIPTION |
INSTRUMENT OVERVIEW
===================
The Dust Impact Detector System consists of six subsystems with the
primary aim of recording the impacts of all particles of significant
mass incident on the Giotto probe. Mounter on Giotto's dust shields,
the detectors determine the mass spectrum. The capacitor impact
system records the discharge of a parallel plate capacitor when
impacted by a particle whose mass exceeds the threshold value. The
sensor is bonded to the outer surface of the front shield. The MSM
and RSM subsystems of the DIDSY were designed and built at the
University of Kent at Canterbury but the acoustic design of the front
shield was the responsibility of the Rutherford Applied Physics
Laboratory. Three 200 kHz longitudinally resonant PZT 5A piezoelectric
microphone elements are attached to the rear of the spacecraft front
shield. Each crystal is contained in a hermetically sealed stainless
steel container. Impacts on the spacecraft rear kevlar shield are
sensed by a fourth (RSM) sensor identical to the front ones. The IPM
sensor consist of two impact ionization detectors each with a sensitive
area of 59.6 cm**2 and a piezoelectric detector supplied by the
University of Kent at Canterbury. The entire system was designed and
developed by the Max-Planck-Institute-Fuer-Kernphysik with the help
of the Technical University of Munich. The sensor is attached to the
front shield of the spacecraft.
SCIENCE OBJECTIVES
==================
DIDSY attempts to measure the mass efflux from a comet. In order
to determine the mass spectrum, a collection of instruments,
sensitive to different properties are used. Two broad groups measure
the particles directly (gas and dust) or the plasma generated by both.
In the former case, the discrete data represent a set measured values
for a single event. These can be collected to form the mass spectrum
of the particles. In the latter case, a 1 cm**2 gold-plated electrode
measures the plasma.
CALIBRATION DESCRIPTION
=======================
A program of laboratory measurements was carried out to determine
the performance of different shield designs. A revised design
incorporates a 35 degree sector of the annular shield which remains
'clean' (DID 4). It is then possible to get a relatively true signal.
There is also a large sector (325 degrees) that is treated as a
single surface and measured by detectors DID 2 and DID 3.
DETECTORS
=========
DETECTOR_ID : DID 7
DETECTOR_TYPE : PARALLEL PLATE CAPACITOR
DETECTOR_ID : DID 5
DETECTOR_TYPE : PIEZOELECTRIC
(A PZT 5A piezoelectric microphone element attached to the rear
shield.)
DETECTOR_ID : DID 4, DID 3, DID 2
DETECTOR_TYPE : PIEZOELECTRIC
(PZT 5A piezoelectric microphone elements attached to the rear of the
spacecraft front shield.)
DETECTOR_ID : DID 1
DETECTOR_TYPE : PIEZOELECTRIC
(A PZT 5A piezoelectric microphone element attached to the front
shield which is used in combination with the plasma detectors (1A
and 1B) below.)
DETECTOR_ID : DID 1A, DID 1B
DETECTOR_TYPE : IMPACT PLASMA
(Impact ionization detectors for submicron and micron size particles.)
ELECTRONICS
===========
The Cetral Data Formatter (CDF) performs functions for each detector.
The CIS electronics exhibits one of two processes. If a particle
strikes the sensor, a conduction path is set up by the formation of
a plasma. The RSM/MSM electronics subsystem performs both analog and
digital processing of the signals arising at each sensor from a
particle impact. The signals from the IPM subsystems are processed in
parallel to reduce dead-time. The IPM/M electronics also performs
both analog and digital processing.
PLATFORM MOUNTING DESCRIPTION
=============================
DIDSY is mounted inside the dust shields along the front of the
spacecraft.
INSTRUMENT SECTION DESCRIPTION
==============================
The DIDSY system has been designed so that, as far as possible, the
individual subsystems may operate independently of each other for
operational reliability. At the same time, by operating in overlapping
ranges of incident particle mass, comparison of results from the
different subsystems will yield greater 'scientific' reliability.
Despite independent operation, some coincidence information for
individual impacts is exchanged between Subsystems for event
validation. However, the failure of one detection subsystem should
not in any way affect the correct operation of another. The Central
Data Formatter (CDF) performs a primary task of collecting data from
each subsystem, processing it as required, and passing it into the
telemetry stream. In addition to handling data formatting the CDF
also supplies power to each subsystem via a separate current-limiter
so that, for example, a short-circuit in one subsystem does not
affect operation of the others. Unregulated power is supplied by the
spacecraft power subsystem on a single current-tripped supply.
Data within the DIDSY subsystem are divided into two broad categories,
namely: (i) discrete data, which represent a set of measured values
for single event detected by one subsystem, and (ii) cumulative data,
which represent the total event amplitude distribution from each sensor
and are generated by accumulation of discrete data events within the
CDF. Such an approach results from the telemetry allocation, which
makes it impossible to transmit full information on all detected
impacts, except at very low impact rates. A limited quantity of
discrete data are mixed with the cumulative data and passed into the
spacecraft telemetry stream by the CDF every 1.3 s during the last
hour before closest approach and every 2.83 s prior to this. A brief
description of the constituent elements of the DIDSY system is given
below.
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Constituent elements of DIDSY
Designation Description Location Subsystem
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DID 1,1A/B Impact plasma, momentum Located in cut-out in IPM/M,
and ambient plasma sensor front shield IPM/P
DID 2,3,4 Piezoelectric momentum Various locations MSM
sensors on front shield
DID 5 Piezoelectric momentum Rear shield RSM
sensors
DID 6 Central Data Formatter Experiment platform
DID 7 Capacitor Impact Sensor Front shield CIS
DID 8 Roll-up cover Front shield over DID 1
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