Space & Astronomy/Space and Astronomy (October 1993).iso/mac/TEXT/SPACEDIG/V15_4/V15NO461.TXT

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Date: Thu, 26 Nov 92 05:08:14
From: Space Digest maintainer <[e-mail]>
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Subject: Space Digest V15 #461
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Space Digest                Thu, 26 Nov 92       Volume 15 : Issue 461

Today's Topics:
  Environmental group to sue NASA to stop rocket motor fuel testing
                      Galileo Update - 11/25/92
                         Shuttle replacement
                    What comes after DC-1 (2 msgs)

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Date: Tue, 24 Nov 1992 18:06:53 GMT
From: "Carlos G. Niederstrasser" <phoenix.Princeton.EDU![e-mail]>
Subject: Environmental group to sue NASA to stop rocket motor fuel testing
Newsgroups: sci.space

In article <[e-mail]> [e-mail] (UPI) writes:
>
>     NEW ORLEANS (UPI) -- Save Our Wetlands Inc. plans to file a lawsuit
> against NASA Tuesday, saying the space agency's proposed advanced solid
> rocket motor fuel testing program will release highly toxic substances
> into Louisiana's delicate wetlands.
>     Officials of the New Orleans-based environmental organization said
> the legal action will seek to stop NASA from proceeding with its testing
> at the John C. Stennis Space Center in Hancock County, Miss. They said
> it would be filed in U.S. District Court at Biloxi, Miss.
>     Under NASA's plans, the testing is scheduled to begin in the next 18
> to 24 months and will last for 30 years.
>     Luke Fontana, founder-director of Save Our Wetlands, said the testing
> calls for firing the rockets at the rate of two to four annually over
> the 30-year period.
>     ``Each test, according to NASA, will emit over 350 tons of
> particulates which release two major gases which we consider highly
> toxic,'' he said. ``They are hydrogen chloride and aluminum oxide.''
>     Fontana said NASA has claimed these gases will escape into the
> atmosphere and will not descend to earth. However, he said his group's
> studies have shown that hydrogen chloride when mixed with water or
> moisture forms hydrochloric compound which is highly toxic.
>     Fontana said the lawsuit will show the NASA testing will not only
> violate a number of the Clean Air Act provisions but also the Endangered
> Species Act because of its impact on a bald eagle nesting site in the
> Louisiana wetlands.
>     Officials were not immediately available for comment at the NASA
> center.

Ironic, that what NASA, NSC, and the Administration failed to do might be
accomplished by an environmental group.  Maybe this will finally get the ASRMs
of our backs.
--
---------------------------------------------------------------------
| Carlos G. Niederstrasser        |   It is difficult to say what   |
| Princeton Planetary Society     | is impossible; for the dream of |
|                                 | yesterday, is the hope of today |
|                                 |   and the reality of tomorrow   |
| [e-mail]   |---------------------------------|
| [e-mail]     |    Ad Astra per Ardua Nostra    |
---------------------------------------------------------------------

--
---------------------------------------------------------------------
| Carlos G. Niederstrasser        |   It is difficult to say what   |
| Princeton Planetary Society     | is impossible; for the dream of |
|                                 | yesterday, is the hope of today |

------------------------------

Date: Thu, 26 Nov 1992 14:17:29 GMT
From: Ron Baalke <[e-mail]>
Subject: Galileo Update - 11/25/92
Newsgroups: sci.space,sci.astro,alt.sci.planetary

Forwarded from Neal Ausman, Galileo Mission Director

                                   GALILEO
                       MISSION DIRECTOR STATUS REPORT
                                POST-LAUNCH
                          November 20 - 25, 1992

SPACECRAFT

1.  On November 20, delta Differenced One-Way Range (DOR) passes were
performed over DSS-14/63 (Goldstone/Madrid) and DSS-14/43 (Goldstone/Canberra).
Initial results indicate that both delta DOR passes were successfully
performed.

2.  On November 20, a routine sun vector update was performed.  This sun
vector is valid through December 3, 1992.

3.  On November 20, the Probe Mission Sequence Test (MST) was performed.  The
MST throughly tested the actual Probe mission, including the operation of the
data and command processor, and all of the Probe scientific instruments
including the valve actuations of the Neutral Mass Spectrometer (NMS).  Initial

results indicate that the Probe and the scientific instruments are operating
nominally.  Detailed analysis and test results from Ames and Hughes are
forthcoming.

     During the MST, the heaters on the scan platform were cycled off for
several hours to support power requirements for the test.  Due to thermal
isolation between the Photopolarimeter-Radiometer (PPR) and the scan platform
structure, the PPR temperatures continued to decrease after the scan platform
heaters were turned back on, violating the GLL-3-210 non-operating Limit of
minus 25 degrees C.  No real-time action was taken because the scan platform
was warming and the PPR temperatures were predicted to raise.  Analysis of
this anomaly is continuing.

4.  On November 21 and 22, delta DOR passes were performed over DSS-14/43 and
DSS-14/63.  Initial results indicate that both delta DOR passes were
successfully performed.

5.  On November 21, the EE-9 (Earth-Earth 9) sequence memory Load was uplinked
to the spacecraft without incident.  This sequence covers spacecraft activities
from November 23, 1992 to December 5, 1992 which is the approach phase of
the Earth 2 encounter.

6.  On November 21, Delayed Action Commands (DACs) were sent to perform wobble
compensation on November 23 in preparation for the Earth 2 encounter.  The
Linear Boom Actuators (LBAs) were moved to decrease the current spacecraft
wobble from 1.2 milliradians to within 0.5 milliradians to support scan
platform pointing requirements for science data gathering.  Initial results
from the wobble ID performed on November 23 indicates the spacecraft wobble is
now approximately 0.35 milliradians.

7.  On November 23, the Solid State Imaging (SSI) instrument was turned on and
its memory Loaded nominally along with turning the SSI replacement heater off.
Also, the Near Infrared Mapping Spectrometer (NIMS) instrument was turned on
and its associated replacement heater and shield heater turned off.  Initial
indications are that both instrument are operating nominally.

8.  On November 23, all of the Gaspra data was played back over DSS-63 (Madrid
70 meter antenna).  Initial results indicate that all of the data was received
on the ground.  Additional playbacks are scheduled on November 24 and
November 25.

9.  On November 23 and 25, No-Op commands were sent to reset the command Loss
timer to 96 hours, its planned value for this mission phase.

10. On November 23, real-time commands were sent to update the AACS (Attitude
and Articulation Control Subsystem) Bright Body Avoidance (BBA) parameters in
preparation for the Earth-2 encounter.  The commands were executed on the
spacecraft without incident.

11. On November 23, a Plasma Wave (PWS) calibration was performed.  Its
purpose was to determine the sensitivity of the PWS search coil as a function
of frequency with a known input signal.  Initial results indicate the PWS
calibration executed nominally.  Detailed analyses is in progress.

12. On November 23 and 24, Magnetometer (MAG) scan platform interference
calibrations were performed.  The calibration characterized the scan platform
interference at five different cone angles.

13. On November 24, the MAG external Calibration Coil (CALCOIL) was performed
to determine the alignment of the science boom in the remaining four instrument
modes which were not done during the Earth 1 encounter.  The CALCOIL was
performed nominally.  Analysis of the results are in progress.

14. On November 24, an Energetic Particle Detector (EPD) calibration was
performed which used both an electronic calibration signal (generated within
the instrument) and a radioactive source (mounted on the instrument).  The
test was performed nominally and data analysis is in progress.

15. On November 24 and 25, a Plasma Wave (PWS)/Ultraviolet Spectrometer (UVS)
interference map was performed to determine the PWS search coil response to
UVS grating stepping as a function of their relative orientation with respect
to the spacecraft.  Simultaneously, a UV map of the anti-sun hemisphere
measuring background Lyman-alpha was collected.  The test was performed
without incident and analysis is in progress.

16. On November 25, a Photometric Calibration Target (PCT) calibration was
performed which provided SSI flat field and noise removal information along
with inter-instrument comparison measurements.  The Photopolarimeter-Radiometer
(PPR) instrument was turned on in support of the PCT.  Analysis of the data is
in progress.

17. The AC/DC bus imbalance measurements exhibited some change.  The AC
measurement has ranged from 15DN to 17DN and now reads 17DN (3.9 volts).  The
DC measurement has ranged from 133 DN (15.6 volts) to 144 DN (16.9 volts)
and now reads 137 DN (16.1 volts).  These measurement variations are
consistent with the model developed by the AC/DC special anomaly team.

18. The Spacecraft status as of November 25, 1992, is as follows:

       a)   System Power Margin - 73 watts
       b)   Spin Configuration - All-Spin
       c)   Spin Rate/Sensor - 2.89 rpm/Star Scanner
       d)   Spacecraft Attitude is approximately 6 degree off
            sun (lagging) and 16 degrees off-earth (lagging)
       e)   Downlink telemetry rate/antenna - 67.2 kbps (coded)/LGA-1
       f)   General Thermal Control - all temperatures within
            acceptable range
       g)   RPM Tank Pressures - all within acceptable range
       h)   Orbiter Science - PWS, PLS, UVS, EPD, MAG, SSI,
        HIC, NIMS, and DDS are powered on
       i)   Probe/RRH - powered off, temperatures within
        acceptable range
       j)   CMD Loss Timer Setting - 96 hours
            Time to initiation - 89 hours


UPLINK GENERATION/COMMAND REVIEW AND APPROVAL:


1.  The Trajectory Correction Maneuver (TCM-17) design package was approved
by the Project on November 24, 1992.  TCM-17 is a one portion maneuver
scheduled to execute on November 28, consisting of one axial and one lateral
segment.  The estimated total delta velocity for TCM-17 is 0.03 m/sec.


TRAJECTORY

     As of noon Thursday, November 25, 1992, the Galileo Spacecraft trajectory
status was as follows:

    Distance from Earth         10,073,900 km (.07 AU)
    Distance from Sun           156,958,200 km (1.05 AU)
    Heliocentric Speed          121,200 km per hour
    Distance from Jupiter       898,004,200 km
    Round Trip Light Time       1 minutes, 6 seconds


SPECIAL TOPIC

1.  As of November 25, 1992, a total of 8699 real-time commands have been
transmitted to Galileo since Launch.  Of these, 3675  were initiated in the
sequence design process and 5024 initiated in the real-time command process.
In the past week, 15 real time commands were transmitted: 15 were initiated in
the sequence design process and none initiated in the real time command
process.  Major command activities this week included commands to uplink the
EE-9 stored sequence memory load, perform wobble compensation, update the AACS
Bright Body Avoidance (BBA) parameters, and to reset the command loss timer.
     ___    _____     ___
    /_ /|  /____/ \  /_ /|     Ron Baalke         | [e-mail]
    | | | |  __ \ /| | | |     Jet Propulsion Lab |
 ___| | | | |__) |/  | | |__   M/S 525-3684 Telos | Learn to recognize the
/___| | | |  ___/    | |/__ /| Pasadena, CA 91109 | inconsequential, then
|_____|/  |_|/       |_____|/                     | ignore it.

------------------------------

Date: Thu, 26 Nov 1992 07:37:41 GMT
From: Hugh Emberson <[e-mail]>
Subject: Shuttle replacement
Newsgroups: sci.space

>>>>> On Wed, 25 Nov 1992 22:19:34 GMT, [e-mail] (Henry Spencer) said:
[...]

Henry> The DC designs are a great deal more redundant than either Harriers or
Henry> helicopters.  They can lose an engine -- or have to shut one down due
Henry> to something like a gimballing malfunction -- and carry on.  This is
Henry> one of the virtues of really powerful engines.

Will the DC-{X,Y,1} have gimballed engines?  I can understand that the
DC-X might need then since it only has a small number (~4) of engines,
but will DC-Y need them?

Surely when you have a large number (~20) of engines around the base
of a rocket you can steer the rocket by throttling some of the engines
down a bit.


Now that I think about it, I am not completely sure that DC-{Y,1} will
have a large number of engines.  Will it, or have cosmic rays flipped
some bits in my brain?

Hugh

------------------------------

Date: Thu, 26 Nov 1992 08:36:00 GMT
From: Hugh Emberson <[e-mail]>
Subject: What comes after DC-1
Newsgroups: sci.space

>>>>> On Wed, 25 Nov 1992 22:46:35 GMT, [e-mail] (Allen W. Sherzer) said:
Allen> In article <deanr.722718879@sco> [e-mail] (Dean Reece) writes:

>Could we strap on SRB's to the DC-1 to increase payload (bad joke...
>forget I said it :-)

Allen> Well, people have proposed it (not SRB's but strap ons). It defeats
Allen> most of the purpose and adds cost but it might be worth while if DC1
Allen> turns out to be more marginal than expected.

Has anyone read "Fallen Angels" by Niven, Pournelle and one other
(Barnes?, Green?).  Not one of their best (probably the best candidate
for worst though).

Anyway the point of this posting is that there is an SSTO in the book.
Built by Gary Hudson and the person who built the Voyager (Rutan? - He
also designs unconventional light aircraft).  Hudson is quoted in the
book as saying that his SSTO could have what he calls a zeroth stage.

The zeroth stage would be like a big SSTO with fuel tanks, lots of
engines and guidance.  It would sit under the SSTO and act like a
first stage booster for the SSTO.  When it was nearly out of fuel it
would seperate, fly back down and land -- ready for reuse.  The book
says that with this the SSTO could reach GEO.

Has McDD thought of this?

Did McDD get their ideas from Hudson?


Hugh

------------------------------

Date: Thu, 26 Nov 1992 08:41:03 GMT
From: Hugh Emberson <[e-mail]>
Subject: What comes after DC-1
Newsgroups: sci.space

>>>>> On Wed, 25 Nov 1992 22:46:35 GMT, [e-mail] (Allen W. Sherzer) said:
Allen> In article <deanr.722718879@sco> [e-mail] (Dean Reece) writes:

>Could we strap on SRB's to the DC-1 to increase payload (bad joke...
>forget I said it :-)

Allen> Well, people have proposed it (not SRB's but strap ons). It defeats
Allen> most of the purpose and adds cost but it might be worth while if DC1
Allen> turns out to be more marginal than expected.

Has anyone read "Fallen Angels" by Niven, Pournelle and one other
(Barnes?, Green?).  Not one of their best (probably the best candidate
for worst though).

Anyway the point of this posting is that there is an SSTO in the book.
Built by Gary Hudson and the person who built the Voyager (Rutan? - He
also designs unconventional light aircraft).  Hudson is quoted in the
book as saying that his SSTO could have what he calls a zeroth stage.

The zeroth stage would be like a big SSTO with fuel tanks, lots of
engines and guidance.  It would sit under the SSTO and act like a
first stage booster for the SSTO.  When it was nearly out of fuel it
would separate, fly back down and land -- ready for reuse.  The book
says that with this the SSTO could reach GEO.

Has McDD thought of this?

Did McDD get their ideas from Hudson?


Hugh

------------------------------

End of Space Digest Volume 15 : Issue 461
------------------------------