Transcript
Wide-Field Imaging Survey Polarimeter (WISP) Target: UVX7
Experimenter's Data Package Vehicle 36.172 UG Revision H Apr 6, 1999 Prepared for: National Aeronautics and Space Administration Wallops Flight Facility Wallops Island, Virginia Prepared by: K. H. Nordsieck & W. M. Harris Space Astronomy Laboratory University of Wisconsin Madison, Wisconsin 53706
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Change History Rev
Date
Description
F
18 Oct, 1998
Made UVX7 primary target with UVX6 backup. Incorporated electronic versions of all figures. Launch windows Nov 1998 - Jan 1999
G
13 Feb, 1999
Removed UVX6. Updated launch windows to Mar - May 1999
H
6 Apr, 1999
MRR: Add integration status; revise success criteria
i
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1. Description of Experiment The Wide-Field Imaging Survey Polarimeter (WISP) is a suborbital rocket payload that has been used to obtain the first wide-field polarimetric and photometric images of astronomical nebulae in the vacuum ultraviolet. The WISP instrument is designed to study the properties and geometric distribution of diffuse dust in our Galaxy and nearby galaxies; its wide field of view and high sensitivity also make in an excellent instrument for the study of diffuse emission in the zodiacal light and in the extended coma and tail of a comet. The first three successful flights of WISP have covered different representative objects in these categories, a local star cluster (the Pleiades - Vehicle 36.050 UG), a nearby galaxy (the Large Magellanic Cloud- Vehicle 36.128 UG), and a comet (Hale-Bopp- Vehicle 36.157 UL). For the upcoming mission our target is a direction in our Galaxy, "UVX7" (the "Sandage Area" near the external galaxies M81 and M82) that was identified as bright by previous UV diffuse light survey missions. If this light is due to reflection of UV starlight from Galactic interstellar dust, as has been commonly assumed, the light should be highly polarized, and the polarization angle should identify the illuminator, allowing a reconstruction of the path taken by the light, and a measurement of the properties of the dust. The payload configuration for this mission will be similar that used for the first three WISP missions, with the exception of changes to the detector, replacement of the tracker "aperture plate" with a standard shutter door, and the inclusion of a prototype aspect camera/star tracker that we are currently developing for our new rocket instrument, FUSP. The WISP optical package (Figure 1) is a wide-field F/1.9 off-axis Schmidt telescope with a polarizing Brewsterangle mirror and a waveplate modulator. Light from the target field enters the experiment at an angle of 40E from the vehicle spin axis. The octagonal-shaped aperture is covered by a door during launch and re-entry. The first optical element is the "stressed waveplate", which is a rotatable CaF2 plate with a programmable birefringence introduced by pneumatic actuators on two edges. This effectively rotates the plane of polarization of the incoming light, depending on the angle and the stress applied, which is controlled by the experiment processor based on strain gages. The light then encounters an off-axis Schmidt corrector mirror and a large flat mirror coated with a high-index monolayer, which polarizes the light by the Brewster effect. Finally the light is focused by a spherical primary mirror and imaged on a Charge-Coupled Device (CCD) detector. The CCD is preceded by a color filter slide (two filters are available), a shutter, and a field flattener/window. The CCD is cooled to -80EC by a Thermo-Electric Cooler (TEC), which discharges its heat into a copper heat sink on the rear of the evacuated housing. The heat sink is cooled to about -40EC by liquid N2 boil-off up until launch. The entire optical area is also purged with dry argon up until launch for cleanliness and to prevent condensation on the CCD window. The first two WISP missions called for two Attitude Control System startrackers, with tracker #1 aligned to the spin axis, and #2 (the "side tracker") pointed near the experiment line of sight at a trackable star. There are also two "sky monitors", miniature telescopes which focus the WISP field of view onto photomultipliers with fixed UV filters, mounted beside the startrackers. The sky monitor signals are used in post-mission analysis to calibrate the residual UV airglow and zodiacal light background. The trackers and sky monitors have been protected during landing by a guillotine "aperture plate"; for this mission the aperture plate will be replaced by a standard shutter door. The forward startracker is used to update the vehicle gyros and to slew to the correct experiment orientation; control was then switched to the side startracker for accurate tracking during the science exposure. Our choice of a moving target (comet Hale-Bopp) for the
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last mission, made the use of a the second tracker problematic, because a different trackable star was needed on each night of the launch window. Our approach was to align the second tracker for a single night of the window. When we failed to launch on this date, we were forced to abandon the second tracker, and accept the errors associated with gyro drift roll. To our pleasant surprise, our data quality was not compromised by this, and we now plan to eliminate the side tracker in future flights. This greatly simplifies instrument alignment and limits the risk to the dwindling supply of trackers in the sounding rocket program arsenal. A data sequence through one experiment filter consists of four exposures of the CCD with different stress and angle states of the waveplate. The Hale-Bopp and Pleiades missions used both available filter positions, resulting in a total of 8 science exposures. To maximize the signal/noise in the diffuse target for the upcoming flight(s), we plan to use a single filter/launch. The CCD readout bins 5×5 pixels into one, giving a ~1 arcmin effective pixel size. Each exposure will be roughly 80 seconds in length, with an additional 4 seconds required for CCD readout and mechanism operations. The exposures are differenced in later processing to obtain the polarimetric images.
2. Electronics The experiment system and electronics block diagrams are shown in Figures 2 and 3, and include the changes expected for the upcoming mission. In particular, we will install a new CCD detector/controller, will interface to the new startracker door, and will include a prototype for a new star-tracker/aspect camera that we are currently developing. These changes are discussed in detail below. All of the major experiment electronics are located in a separate electronics section of the experiment. The Dedicated Experiment Processor (DEP) controls the waveplate pneumatics and rotator, the filter and shutter, the focus mechanism, and the CCD detector based on internally stored sequences and two payload-generated signals, an "aspect picture" request of the experiment CCD from the ACS, and an "on target" signal from the ACS. The DEP also controls the CCD temperature by controlling the TEC current. All experiment system power is regulated from the vehicle 28V bus. Experiment outputs include a dedicated digital telemetry stream at 2 Mbit/s; the DEP will multiplex this data into a serial data channel complete with the required synch words. In addition, a number of analog monitors (see Interface Specification, attached) will be fed to the vehicle multiplexer to provide system status independent of the DEP. The experiment door and tracker door will be controlled directly by the payload timer.
3. Structure The experiment structure conforms to the standard 17.26 inch diameter bulkhead/skin. Total payload weight is ~770 lbs, broken down approximately as follows: Item Nose cone ORSA (750 lb) Offset Adaptor Upper Balance Wt ACS (Mk VI)
Weight (lbs) 21.6 87.4 5.5 11 112
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Item Telemetry S19 Experiment Main Cables/Baffling Misc Skins Experiment Door Tracker Plate/Door Lower Balance Wt Ignitor Thrust Term Total
3
Weight (lbs) 82 70 302 174.7 (See Table 1) 20 25 64.2 10 5 11 52.6 13.8 766
An outline of the experiment section is shown in Figure 4. Detailed weight and center of gravity estimates are listed in presented as determined for the previous mission. The experiment coordinate system used in Table 1 is as follows: Exp
ACS
Direction
On Pad
Zero
X Y Z
-Yaw -Roll -Pitch
Perpendicular to the spin axis, opposite the door Along spin axis, along LOS of startracker #1 Perpendicular to the spin axis, along ACS 0
West Down South
Spin Axis Exp/TLM I/F Spin Axis
Note that in this coordinate system, the experiment LOS is not along X, Y, or Z, but is rather displaced from Y by a +40E rotation about the +Z axis, or an ACS pitch of -40E.
4. Experiment History 1) 36.050 UG: The payload has flown previously on December 2/3, 1994. The mission was a success, with three anomalies: - ACS roll stability on the science target was degraded. - ACS pointing error in the roll direction was 22 arcmin - Experiment detector noise was about 50% higher than anticipated. The first two anomalies were traced to a wiring problem in the ACS and were corrected in advance of the second flight.
2) 36.128 UG: The payload was flown on November 17, 1995. This mission was a complete success with the following anomalies which did not significantly affect flight performance:
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- Thermal noise in the experiment detector was higher than expected for the temperature recorded within the housing. - We were unable to cool the back plate to the desired temperature due to a low temperature leak in the evacuated housing. The causes of these anomalies were identified. The thermal noise was determined to be correlated with higher than normal water levels inside the detector, which caused a well known detector problem where ice formation in the space between the CCD and cold sink creates a thermal insulating wall. Since our temperature sensor was attached to the cold sink, we were given an erroneous signal for the temperature of the detector. The source of the low temperature leak was not specifically identified, however we were able to fix it by replacing all of the sealing O-rings with new ones optimized for low temperature operation.
3) 36.157 UL: The payload was flown on April 8, 1997 to observe comet Hale-Bopp. This mission was a comprehensive technical and scientific success with two anomalies. - Our initial launch attempt was aborted due to a failure in the camera shutter 3 minutes before launch. - During the flight we noted some significant increasing in sky background noise from what appear to be multiple sky background sources. The primary anomaly for this mission was the shutter failure. We were able to isolate this failure to a slowly decreasing tension on a restoring spring in the shutter assembly. When the detector was cooled, either ice formation or shifting/warping of the shutter blades froze the mechanism. We added a new spring that more than doubled the restoring force and made the system highly reliable from that point on. We have implemented new protocols to monitor shutter performance before and during flight. The sky background anomaly may have been due to the low elevation of the target for this flight, however, since it was greatest in the last image, we plan to terminate the last exposure at a higher altitude, and then look at the zenith in an attempt to measure what we believe to be an airglow feature.
5. Experiment Modifications 1) Upgrade to the CCD detector: As part of the preparation for this mission we plan to replace the current WISP CCD with a new controller/detector combination. The current 1200x400 pixel Reticon CCD and controller will be replaced with a modern 1024x1024 SITe device that will more than double quantum efficiency and reduce read noise by more than a factor of 2. This system will be enclosed in a new, better sealed, detector housing with an upgraded thermoelectric cooler that will permit lower temperature operation. From an interface to NASA perspective, there will be no difference between this device and the current detector. 2) Replacement of the tracker "aperture plate" with a standard shutter door. Due to repeated damage to the startracker during past landings, the experiment was requested to replace the simple "guillotine" type tracker shutter with a standard shutter door. This has been accommodated by the addition of a connector (P750; see Interface Specification, attached), and the rewiring of the Ignitor Housing connector (J5). Note that in this document, the shutter door
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protecting the tracker is referred to as the "Tracker Door", and the shutter door protecting the experiment optics is the "Experiment Door". Both are sometimes referred to as the "Shutter Door" in vehicle documentation, and our terminology is preferred to prevent confusion. 3) Incorporation of a prototype aspect camera/star tracker: We are planning to replace the now redundant second star tracker with a new device that we are developing for our second payload (FUSP: 36.173 UG). This device will be installed in the area occupied by tracker 2 and will be bore-sighted to tracker 1. This unit is capable of providing simultaneous centroiding data similar to the current Ball tracker and compressed image output. We will modify our current harness to downlink the centroiding data for post-flight analysis, and these signals will be incorporated into our engineering data stream (no changes in the TM system are required to accommodate this). Also, we are requesting that the vehicle TM system be modified to accept and transmit 38400 baud RS232 serial telemetry from this device. We do not intend to use this device for tracking on this mission.
6. Experiment Events The experiment is controlled entirely by preplanned sequences and the timer- and ACS-based signals. The experiment requirements for these signals are as follows (Electrical interface details are given in the Telemetry, Commands, and Electrical Interface Specification Attached): Event
Origin
Requirement
On Target Exp Power Off
ACS Timer
Leave on. Parachute deploy - 20 sec.
Table 2 gives an experiment event program based on a nominal apogee altitude of 375 km and an ACS "on target" at T+161 (nominal); T+187 (latest) seconds. The low voltage logic power will be on at lift-off and telemetry will be continuous. CCD dark frames commence on despin. The high voltage powering the mercury focus testlamp and the sky monitors will be turned on at T+96 seconds, controlled by the experiment internal timer. Science exposures begin on receipt of "On Target" from the ACS. If the "On Target" is not received, science exposures begin automatically at T+187 seconds, the latest time for this signal, with the entire imaging sequence. Regardless of the timing of the ‘On Target’ signal (or lack thereof) the entire image sequence is designed to fill the time until an altitude of 106 km is reached. This will consist of four science images, which will end at altitude ~180 km, plus a low-altitude sky background image. High voltage is turned off at experiment door close and CCD dark frames are then continued until experiment power off. The protoype camera/ startracker will be controlled by the ACS signals that were used for the "side" tracker in previous missions. The current wiring harness causes the FOV and brightness ("Cmd") controls to be shared between the main Ball ("forward") tracker and the UW tracker, so these will be used on a non-interference basis. As summarized in the table below, during gyro update star #1 and #2 fine modes, we require an acquisition signal. We assume that neither limited FOV bits will be asserted. At the end of each gyro update star fine mode, we require an extra step, longer than 0.25 s, when the Ball tracker- based fine mode continues but the UW tracker acquire is removed (this is for acquisition of a stable aspect image). During the on-target
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period on the science target, we require a UW tracker acquire signal, plus FOV and Cmd signals as shown below. Event
Ball Acq
UW Acq
2E FOV
4E FOV
Cmd 1
Cmd 2
Time
GS #1,
On On Off Off
On Off Off On
0V 0V don't care 28V
0V 0V don't care 28V
don't care don't care don't care GND
don't care don't care don't care OPEN
Fine mode >0.25 s
GS #2 Science
On Target
7. Pointing Requirements: We made starmaps for UVX7 (Figures 5a,b) and windows for each month starting in March 1999 and ending in May, 1999 (Table 3). The windows are defined by a combination of time of night, elevation of target, angular separation of the target from the moon, and the distance of the Sun below the depressed horizon. The roll for UVX7 was chosen to optimize the placement of the known diffuse clouds as seen by IRAS. The position of the target area is given below. The windows are chosen for an optimal launch after midnight. UVX7 Position
RA (J2000)
09h 40m 00s
DEC
70E 00' 00"
(J2000)
90E
Roll Window:
0 - 2h MST, 14 - 19 Mar, 1999 1 - 2h MDT, 12 - 17 Apr, 1999 0 - 1h MDT, 10 - 15 May, 1999
Experiment roll is defined as the angle measured clockwise (looking at the experiment LOS) from North (J2000 coordinates) to the ACS 0 (experiment Z axis). As noted above, there is a 40E offset between the startracker axis and the experiment axis. During science exposures the startracker (-Roll axis), and the ACS pitch axis are then pointed at UVX7 Tracker LOS ACS +Pitch Axis
RA (J2000) Dec (J2000) RA (J2000)
9h 40m 00s 30E 00' 00" 15h 40m 00s
Dec (J2000)
00E 00' 00"
Figure 5a,b shows the starchart containing the experiment and startracker lines-of-sight for UVX7. Stars down to 3rd magnitude are shown in the wide field, identified by SAO number. Pointing accuracy is to be ±0.1E in experiment LOS and ±1E in experiment roll. Pointing stability is to be < 60 arcsec rms diameter for 85 seconds (the duration of one exposure).
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8. Launch Window Requirements Launch window criteria are based on minimization of the risk of sunlight hitting the experiment or trackers in flight and celestial/terrestrial backgrounds. They are: 1) Target Zenith Distance (ZD) < 25E 2) Sun > 30E below depressed horizon at Apogee 3) Moon > 20E below depressed horizon at Apogee 4) Launches after local midnight are preferred to minimize airglow. Windows for March - May, 1999 are shown in Table 3. The current nominal Launch time is 0100 MDT on the night of April 12/13, 1999 (shown as "N" in table 3).
9. Comprehensive Mission Success Criteria 1) Vehicle: 835 lb to nominal apogee minimum 2) ACS: experiment LOS pointing error < 0.15E. "
" stability/100s < 60 " (rms diameter).
3) Experiment: All science exposures obtained. 4) Payload recovered in good condition.
10. Minimum Success Criteria 1) Vehicle: 835 lb to a minimum of 3s below nominal apogee. 2) ACS: experiment LOS pointing error < 0.3E. "
" stability/100s < 120 " (rms diameter).
3) Experiment: All science exposures obtained.
11. Support Requirements 1) Purge gas: A continuous low pressure (2-3 psig) flow of dry argon is to be maintained into the experiment optical section, venting into the experiment electronics section and into the startracker section. We estimate a maximum consumption of one high pressure bottle every two days when the experiment is integrated into the payload. 2) Detector coldsink coolant: A 35 liter liquid nitrogen dewar will be located underneath the launcher, attached to the payload coolant pullaway by approximately 60 ft of insulated coolant line. The experimenter will provide the dewar, coolant line, and pullaway mechanism. We estimate a maximum consumption of 5 liters per cooldown cycle (detector coldsink from 20EC to -40EC in 30 minutes), and 3 liters/hour to maintain -40EC prior to launch. The dewar should be topped off each night a launch is attempted. In addition, one standard high pressure gaseous nitrogen bottle will be required underneath the launcher to back pressurize the LN2 dewar if
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necessary. The experimenter will provide a regulator to drop the gaseous nitrogen to low pressure (10 psig). The cooling system was operational at all times (including during arming) for the Hale-Bopp mission, and we are requesting the same operational status for the upcoming mission. 3) Environmental control: The experiment section of the payload skin (70" length) should be enclosed in a thermally controlled enclosure. The temperature should be maintained at 20EC ± 5EC from T-6 hours until launch.
4) Access to experiment prior to launch: While the experiment is horizontal the experimenter requires access via the electronics section access door to refill the waveplate system high pressure tank and to connect a portable vacuum pump system to the detector head vacuum line. The high pressure tank will require refilling on an as-needed basis prior to each night's launch attempt. It is anticipated that the detector head will be pumped down continuously to maintain an optimum vacuum. The pump will be external to the payload, electrically isolated and on an uninterruptable power supply. It will be turned off and disconnected just prior to taking the rail vertical.
12. Flight Qualification Status In March-April the integrated payload underwent Testing and Integration at University of Wisconsin and WSMR. The following issues were identified: - The experiment processor sometimes fails to start its timeline at T-60 secs. This is due to an unidentified software error. The workaround is to cycle power to the instrument, re-equilibrate the detector cooling, and re-start the timeline. This procedure was exercised in the Range Horizontal Test and found to take less than 5 minutes, with no impact on the rest of the flight. - The experiment processor does not restart during the power backup test. Since power cycle at launch is an extremely rare occurrence, we elect to fly as is. - The experiment is now taking about 10 minutes longer to reach flight detector temperature. Once it is reached, all else is nominal. This will require going vertical 10 minutes earlier. - The prototype star tracker roll analog telemetry is not being transmitted, apparently due to a wiring error in the experiment. Since roll data is available in the digital telemetry, we will fly as is.
13. Redundant Systems Other than redundant batteries on the experiment system timer board, there are no redundant hardware systems. There are fallback software routines within the experiment processor that will be used in the event of certain hardware failures. For instance, in case the processor is reset by a power glitch, the processor will check the system timer and resume the observing program from the pre-programmed time table stored in ROM.
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14. History of Items to be Flown The flight hardware was flown on 36.050UG in December 1994, on 36.128UG in November 1995, and in April 1997 as 36.157UL.
15. Experimenter's Launch Criteria Launch criteria are based entirely on the preplanned launch window requirements (section 7 above) and on experiment health. All experiment health measurements are available to the experiment processor, so that experiment health will be judged based on performance of an experiment self-test during the launch count-down.
16. Interface Requirements See Attachment 1 (Telemetry, Commands, and Electrical Interface Specification, WP1100-S-0010 Rev E) for electronic interface requirements.
17. Special Requests: To support our apogee requirements we are requesting enhanced launch vehicle (Mark 70) for our flight. This would be a repeat of the vehicle configuration for 36.157UL.
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Table 1. Mass and Center of Gravity Estimates
Pcs 1
Part # Assy 5087 5085 5084 5022 5016 5030 5029 5005,9 5093 5018,27 5077 5076
1
Assy 5017 5105 5046 5104,5
1 1 1 1 1 1 2 2 1 1
Assy
Name Optics Section: Brewster Mirror Primary Mirror Corrector Mirror Detector Assembly Detector Rails Primary Bulkhead Corrector Bulkhead Vertical Rails/Supports Brewster Flex Beams " Supports Corrector Mount Primary Mount Optics/Electr. Flange Electronics Section: STD Card Cage Electr Base Plate Electr Supp Legs Detector Electr Pwr Supply/Distr Box Power Cubes Pneumatic System System Timer Box Waveplate Assy #1 Star Tracker " Mount Prototype Tracker " Mount Sky Mon Electr Box Sky Monitor " Mount Str Gage Amp Box Lamp Power Supply
Center of Mass
Total Weight
X
-1.275 "
Y
29.74 "
Z
0.084 "
174.7 lbs
Wt Ea Total 78 lb 78
Method X(") Actual -2.4
Y(") 34.75
Z(") 0
55
55
Actual
0.25
8.25
0
7.0 11 1.2 8 4.4 1.0 2.1 1.2 1.0 1.5
7.0 11 1.2 8 4.4 1.0 4.2 2.4 1.0 1.5
Est Est Act Est Est Est Act Act Est Est
-4.0 -5.8 -5.5 2.0 2.0 0 0 0 0 0
30.8 58.8 58.8 58.8 58.8 56 58.3 57.3 41.8 26.8
0 0 0 0 0 0 0 0 6.3 6.3
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Table 2. Preliminary Flight Timeline for UVX7 /* Flight Timeline for WISP 36.172UG
PREADLEN 256
*/
/*
Target: UVX-6
*/
/*
Revision 1: 29 July 1998
*/
/*
Clock start at t-60 secs
/*
Short Wavelength exposure only
/*
No focus motion
/*
Start mechanism motions 2 sec after
/*
*/
*/
*/ */
/*
TEC FLIGHT=4 , filter hold launch or reentry
*/
TAKE 52
SECONDS 40
FILTER B
ROTATION 0
VALVE ENABLE
MECH 96
PRIMARY_GAUGE A
FILTER A
SECONDARY_GAUGE B
PRESSURE 0
PRESSURE0 000
/* zero pressure */
ROTATION 0
PRESSURE1 400
/* launch pressure */
SKYMON ON
PRESSURE2 1800 /* half-wave short wavelength */
TEC 4
PRESSURE3 2900 /* half-wave long wavelength */
VALVE ENABLE LAMP ON
PRESSURE4 0
PRESSURE6 0
SBIN 2
PRESSURE7 0
PBIN 2
TL_TYPE FLIGHT
SORIGIN 256
OFFSETA 860
PORIGIN 256
OFFSETB 890
SREADLEN 256
EXPTYPE NORMAL
CAM -59
SECONDS 1
SBIN 4
MECH 102
PBIN 4
PRESSURE 0
PREADLEN 256 /* 3 sec dark, 4x4 binning */
ROTATION 0 SKYMON ON
EXPTYPE DARK
TEC 4
SECONDS 3 /* prelaunch 40-sec dark */
VALVE ENABLE LAMP OFF
EXPTYPE DARK
CAM 102
SECONDS 40 /* launch mech preps during CCD dark */ /* short wavelength */
PBIN 4
PRESSURE 1
/* launch pressure */
SREADLEN 281
/* 4x4 dark */
PREADLEN 256
ROTATION 0
TAKE 102
SKYMON ON
EXPTYPE DARK
TEC 4
SECONDS 40
VALVE ENABLE /* launch mech preps - II */
TARGET 187
/* complete 142; earliest on-target 148 */ /* latest possible on-target */
NOBS 4
FILTER HOLDB
TAKE 187 REPLAN
PRESSURE 1
/* long wave Q- */
EXPTYPE NORMAL
ROTATION 0
SECONDS 79
SKYMON ON
MECH 268
TEC 4 /* disable control for launch */
/* r/o start + 2 sec */
FILTER B PRESSURE 3
TAKE -9
/* GO TO long wave pressure */
ROTATION 0
EXPTYPE BIAS
SREADLEN 281
/* lamp off */
SBIN 4
FILTER B
PBIN 4
/* MECH for first science exposure */
FILTER B
SREADLEN 281
SBIN 4
/* 2x2 centered images */
TAKE 96
OFFSETD 817
CAM 48
/* lamp on for focus */
PREADLEN 256
OFFSETC 803
VALVE DISABLE
/* longwave for focus */
CAM 96
PRESSURE5 0
MECH -15
/* re-enable valves */
LAMP OFF
PARAMETER -60
MECH -46
/* Skymon On */
TEC 4
BEGIN -60
TAKE -52
/* P/L sep at 64- filter hold off */
PRESSURE 0
SKYMON ON TL_VERSION 4
TAKE -58
/* will finish at 90 */
MECH 75
*/
beginning of readout All images 4x4 bin full image
/* bias */
EXPTYPE BIAS
EXPTYPE DARK
*/
/*
TAKE 48
/* 4x4 cam mode again, for safety */
SKYMON ON TEC 4 VALVE ENABLE TAKE 269 REPLAN
/* long wave Q+ */
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EXPTYPE NORMAL SECONDS 79 MECH 350
/* r/o start + 2 sec */
FILTER B PRESSURE 3 ROTATION MINUS /* GO TO minus position */ SKYMON ON TEC 4 VALVE ENABLE TAKE 353 REPLAN
/* long wave U- */
EXPTYPE NORMAL SECONDS 79 MECH 434
/* r/o start + 2 sec */
FILTER B PRESSURE 3 ROTATION PLUS /* GO FROM minus TO plus position */ SKYMON ON TEC 4 VALVE ENABLE TAKE 439 REPLAN
/* long wave U- */
EXPTYPE NORMAL SECONDS 79 MECH 520
/* r/o start + 2 sec */
FILTER A
/* long-wave filter */
PRESSURE 1
/* reentry pressure */
ROTATION PLUS SKYMON ON TEC 4 VALVE ENABLE TAKE 523
/* attempted flat-field on low altitude sky */
EXPTYPE NORMAL SECONDS 30 MECH 555
/* reentry filter, wvplt posn */
FILTER B PRESSURE 1 ROTATION 0 SKYMON OFF TEC 4 VALVE ENABLE TAKE 558 EXPTYPE BIAS MECH 559 FILTER HOLDB
/* reentry mech preps - II */ /* filter hold */
PRESSURE 1 ROTATION 0 TEC 4 VALVE DISABLE TAKE 563
/* disable pressure control for reentry */ /* 40-sec dark */
EXPTYPE DARK SECONDS 40 TAKE 606 EXPTYPE DARK SECONDS 40
/* 40-sec dark */
TAKE 649 EXPTYPE BIAS TAKE 654 EXPTYPE BIAS TAKE 659 EXPTYPE BIAS END 670
/* finishes at 664, 0 sec from power-down */
12
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Table 3: Launch Windows UVX7 Launch Window for WSMR, March 1999. Target
RA=
9 40 0
Dec=
70 0 0
Sea Level Altitude Sun
<
-30
Moon
<
-20
Target > yymmdd 18 |
25 19
20
21
22
23
0
1
2
3
4
5
6
|
|
|
|
|
|
|
|
|
|
|
|
990301 sssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss 990302 sssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss 990303 sssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss 990304 sssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss 990305 sssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssss 990306 sssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssss
990307 sssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssss
990308 sssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssss
990309 sssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssss
990310 sssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmsssssssssss
990311 ssssssssssssssss
mmmmmmmmmmmmmmmmmmsssssssssss
990312 ssssssssssssssss
mmmmmmmmmmmmssssssssssss
990313 ssssssssssssssss
mmmmmmmmssssssssssss
990314 ssssssssssssssss
mmmssssssssssss
990315 ssssssssssssssss
ssssssssssss
990316 ssssssssssssssss
ssssssssssss
990317 ssssssssssssssss
ssssssssssss
990318 ssssssssssssssssmmm
ssssssssssss
990319 ssssssssssssssssmmmmmmmmmm
sssssssssssss
990320 ssssssssssssssssmmmmmmmmmmmmmmmmm
sssssssssssss
990321 ssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmm
sssssssssssss
990322 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmm
sssssssssssss
990323 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmm
sssssssssssss
990324 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990325 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990326 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990327 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990328 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990329 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990330 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990331 sssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999
14
UVX& Launch Window for WSMR, April 1999 Target
RA=
9 40 0
Dec=
70 0 0
Sea Level Altitude Sun
<
-30
Moon
<
-20
Target > yymmdd 18 |
25 19
20
21
22
23
0
1
2
3
4
5
6
|
|
|
|
|
|
|
|
|
|
|
|
990401 ssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss 990402 ssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss 990403 ssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssss 990404 ssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssss 990405 ssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssss
990406 ssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss
990407 ssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmmmssssssssss
990408 ssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmmmssssssssss
990409 sssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmssssssssss
990410 sssssssssssssssssssssssss
mmmmmmmmmmmmssssssssss
990411 sssssssssssssssssssssssss 990412 sssssssssssssssssssssssss
mmmmmmmmssssssssss N
mmmsssssssssss
990413 sssssssssssssssssssssssss
sssssssssss
990414 sssssssssssssssssssssssss
sssssssssss
990415 sssssssssssssssssssssssss
sssssssssss
990416 sssssssssssssssssssssssss
sssssssssss
990417 ssssssssssssssssssssssssssmmmmmmm
sssssssssss
990418 ssssssssssssssssssssssssssmmmmmmmmmmmmmm
ssssssssssss
990419 ssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmm
ssssssssssss
990420 ssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmm
ssssssssssss
990421 ssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmm
ssssssssssss
990422 ssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssss 990423 ssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990424 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990425 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990426 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990427 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990428 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssss 990429 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990430 sssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999
15
UVX7 Launch Window for WSMR, May 1999 Target
RA=
9 40 0
Dec=
70 0 0
Sea Level Altitude Sun
<
-30
Moon
<
-20
Target > yymmdd 18 |
25 19
20
21
22
23
0
1
2
3
4
5
6
|
|
|
|
|
|
|
|
|
|
|
|
990501 ssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990502 ssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990503 ssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmmssssssssssssss 990504 ssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss 990505 ssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss 990506 ssssssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssss
990507 sssssssssssssssssssssssssssss
mmmmmmmmmmmmmmmmmmmsssssssssssssss
990508 sssssssssssssssssssssssssssss
mmmmmmmmmmmmmmmsssssssssssssss
990509 sssssssssssssssssssssssssssss
mmmmmmmmmmmsssssssssssssss
990510 sssssssssssssssssssssssssssss
mmmmmmssssssssssssssss
990511 sssssssssssssssssssssssssssss
ttmmssssssssssssssss
990512 sssssssssssssssssssssssssssss
ttttssssssssssssssss
990513 sssssssssssssssssssssssssssss
tttttssssssssssssssss
990514 ssssssssssssssssssssssssssssss
tttttssssssssssssssss
990515 ssssssssssssssssssssssssssssss
tttttssssssssssssssss
990516 ssssssssssssssssssssssssssssssmmm 990517 ssssssssssssssssssssssssssssssmmmmmmmmm 990518 ssssssssssssssssssssssssssssssmmmmmmmmmmmmmmm
tttttsssssssssssssssss tttttsssssssssssssssss ttttttsssssssssssssssss
990519 ssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmtttttsssssssssssssssss 990520 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssssss 990521 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssssss 990522 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmmsssssssssssssssss 990523 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990524 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990525 sssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990526 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990527 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990528 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990529 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990530 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmmssssssssssssssssss 990531 ssssssssssssssssssssssssssssssssmmmmmmmmmmmmmmmmmmmmmsssssssssssssssssss
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999 Figure 1. WISP Optics Section
16
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999 Figure 2. WISP System Diagram
17
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999
18
Figure 3. WISP Electronics Block Diagram
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999
Figure 4. Experiment Structure Outline and Interfaces
19
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999
Figure 5a. UVX7 Star Field & Tracker Positions
20
WISP-IV EDP: 36.172 UG
Rev H Apr 6, 1999 Figure 5b. UVX7 Narrow Field
21
