The Interactions Measurement Payload for Shuttle (IMPS) consisted of engineering experiments to determine the effects of the space environment on projected Air Force space systems. Measurements by IMPS on a polar-orbit Shuttle flight will lead to detailed knowledge of the interaction of the low-altitude polar-auroral environment on materials, equipment and technologies to be used in future large, high-power space systems. The results from the IMPS measurements will provide direct input to MIL-STD design guidelines and test standards that properly account for space-environment effects

Guidice, D. A.

Pike, C. P.

English

NASA Technical Reports Server

T _
ir' , N85 "22518
INTERACTIONS HEASUREHENT PAYLOAD FOR SttUTTLE
_'- O, A, Gutdice and C_ P, Pl.ke
_ Alr ForCe Geophysics Laboratory
Hanscom Atr Force 6ase,_._Hassachusetts_Ol?.3l ......................................................................
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_ The purpose Of the InteractionS Measurement Payload for Shuttle (IMPS) is
i_ to develop a payload of engineering experiments to determine the effects of the
_ space environment on projected Air Force space systems. Measurements by IMPS
_ on a late-1980s po/ar-orbit Shuttle flight will lead to detailed knowledge of
_ the interaction of the low-altitude poLar-auroral environment on materials,
equipment and technologies to be used in future large, high-power space systems.
._ The results from the IMPS measurements will provide direct input to MIL-STD
_._ design guidelines and test standards that properly account for space-envlronment
,"_:- effects.
INTRODUCTION
The adverse effects of the space environment on space systems have
caused many operating anomalies in communication and surveillance satellites.
These anomalies were mainly associated with energetic-partlcle radiation or
with spacecraf-t charging at geosynchronous altitudes. For larger space systems
operating in low-earth polar orbits, a new set Of environment-induced inter-
i_ actions will affect the operation of various equipments and subsystems. These
_: adverse effect_s may lintit the construction or mechanical performance of large
:=.,_:. structures in space or limit the power levels available for solar-cell sources.
i_ Before any new Air Force space systems are built and deployed, we must obtain
sufficient environment-interaction information to assure their continued-effec-
: _ rive operation in Space.
i_,- .
i The effects of the space environment on large-structure, hlgh-power space
/: systems are unknown. Of particular concern is operation in the polar-auroral
region at low to medium altitudes (200 to 2000 kin). The physical processes of
this regime and the interactions of the environment with materials, subsystems,
i_ and technologies characteristic of Air Force space systems of the 1990s must be
quantified to assure the reliable operation of projected space systems. IMPS
:._!J will measure polar-auroral effects on solar-array panels, spacecraft materials,
_" structures, electronic subsystems, and astronaut EVA equipment. It emphasizes
!a" application to large, hlgh-power systems and is directed toward technologies
_ identified in the Military Space Systems Technology Model (MSSTM).
SPACE OPERATIONS AND POSSIBLE INTERACTIONS
The first step in deciding what instrumentation should be included in IMPS
is to define several Air Force space-operatlons objectives and determine how the
space enVironment will interact with the equipment or technologies needed to
i_ Carry out those Operations. Since IMPS will fly in polar orbit, polar-auroral
environment Interactlons will be emphasized. The purpose of the IMPS measurements
will be to quantify important environmental interactions -- those that will
restrict certain kinds of space Operation, limit the performance of a particular
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"_ 4_ i_: ......_ ...._ _._
--_ svstem, or prevent (or make ImpreciSe.el) the use of a co rtaln technology.
_:" After deciding _zat kinds of Interaetlon _e likely £o have serious effects,
_, we m_st determine wh_t Interaction parataeter.scan acttially be measured on
pola -o ItingSh tteflight, tn onj .ettonw ththe,.oasur 0 ntof• effects on matertalg,, equipments and technologies, we must char,_terize tim
_ physical, pgopergios of the ea_ironmen_ causing the interactions. The deter-
,_ ruination,of the required interactlon_ measurements will lead to a definition
_i_. of IMPS mission objectives. -............................................................................
_,:, Some generic Air Force space operations to be addressed by IMPS are:
_iiI a. Operation of optical systems
_" b. Opera=ion of radar systems
• c. System deployment or on-orbit repair n_cessitating astronaut extra-
_ ' vehicular activity (EVA).
___; Operation in. the polar-auroral envlronment is to be stressed.
_ .... Possible space-environment effects on optical systems include:
--i!
_"'.,._ (l) Effects associated with large heat dissipation resulting from the low
-_._,_.,. efficiency of lasers or cryogenic refrigerators (for cooIed infrared detectors),
...._:_: (2) Effects of contamination and material property changes on optical
-_ surfaces.
_,_._ (3) Limitations--in power generation due to leakage or arc-discharge in
,:,_, solar arrays.
_o,_ (4) Plasma effects on solar-cell material.
_} (5) Differential charging of closely-packed small dielectric surfaces
--_--_. (multi-element infrared detectors).
___
,,,o
= ': (6) Effects on large high-preclsion struct_es used to support and point
_ complex optical assemblies.
?) Figure I shows a possible configuration for a space-based radar system,
-_." from which one can begin to perceive potential environ,rental interactionS.
Some possible Space-environment effects on radar systems inch, de"
J.
::- (I) Limitations in power generation due to leakage or arc-discharge In
_'.!!ii solar arrays,
(2) Plasma effects on solar-cell material.
• \
'_- (3) For power distribution utilizing high voltages: arc-discharges,
= dielectric breakdowns.
__ (4) For power distribution utilizing high currents: structural stresses
and torques due to large prime-power current loops and in-orbit varying
o terrestrial magnetic-field.
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(5) Electromagnetic intevfer_mce (EMI) affecting radar receiver performance,
(6) Plasma effc_s (such as dlffer_ntiaL-c_arging) on feed structure and
* rof le et o r- ma to ri aL_.
Fi-gure 2 shows astronauts engaged in spaCe-system deployment or in-Orbit
repair activities requi_iag EVA, So_c possible space-environment effects-on
this actix_ity include----
', (I) Differential charging between the astronaut and his spacecraft or the
spacecraft being repaired due to particular environmental conditions in the area.
(2) Interactive effects on the electronics of future EVA-systems due to
electromagnetic interference ov differentlal charging.
(3) Effects in the space-plasma environment due tO thermal-control water
d_tscharge in the astronaut's Life Support System (LSS).
IMPS-CONCEPTS .......
The objective of the Interactions Measurement Payload for Shuttle (IMPS)
program is to develop a payload of appropriate engineering experiments to
- measure the effects of the polar-auroral environment on materialS, subsystems,
and technologies that will be used in future Air Force space systems. The
payload Will con_o__stof:
a. A.complement of engineering experiments to measure and quantify the
different kinds of interactive effects Caused by the environment on various
part_ of projected future space systems.
b. In support of the engineering experiments, a limited set of polar-
auroral environment Sensors to characterize the environment causing the dis-
ruptive interactive effects.
Interactive effects to be investigated by the engineering experiments will
- inc lude:
(I) Interaction of the auroral plasma and current sheets on high-voltage
solar arrays, resulting in power leakage or arc-breakdown.
(2) Interaction of spacecraft electrical currents with polar magnetic
fields on large space structures, causing torques or structure deformation .....
(reducing the pointing accuracy of a large antenna, for example).
(3) Interactions that increase electromagnetlc interference, reducing the
effectiveness of space communications or surveillance systems.
(4) Interactions that degrade the properties or performance of materials or
electronic circuitry, resulting in operational anomalies or subsystem failures.
(5) Interactions that pose a threat to the astronaut during polar-orblt EVA
(causing a malfunction in the astronaut's Manned Maneuvering Unit, for example).
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¸Figure 3 iilustraX.e.sthe concept of-the Interact_Lons Measurement PaylOad-
being developed under Project 2822+ The IMP-Seffo_-t is one Of three projects
_: _ in Program Eleme_t 63410F, Space Systems Envlronmental Interactions Technology,-
PE 634_0F _ an integral par_ of tl_eAgreement_ for NASA/0A_ - OSAF/AFSC Space
Interd_.pendency on Spacecraft-Environment Lnteractlon (blay i980), Under
PE 63410F, IMPS is responsible for polar-auroral interactions measurements.
IHPS will make substantial use of th_ space techn logies and.instrumentation
, developed by NASA technology centers and Air Force organizations such as Air
, Force Wright Aerona_ttical Laboratories (AFWAL).
" IHPS PRELIMINARY-NORK
InLtial Payload Concept Study
In FY82, Jet Propulsion Laboratory (JPL), under the direction of Air Force
Geophysics LaboratOry (AFGL), carried out a basic shuttle payload concept study.
_" It was through this study that many of the basic concepts for IMPS were first
defined. In December 1981, JPL hosted a meeting attended by about 70 experts
:_ in a number of key spacecraft interaction areas. Experiment questionnaires
.... were distributed to the meeting's participants; ultimately about 70 were re-
--:ii_ turned. The information from these queStionnair-es was used by JPL to put
_!_: together an initial IMPS experiments list which was subsequently reviewed and
_ modified by AFGL. Additional reviews and meetings with AFGL, JPL, and AF
_': Space Division personnel lead to further refinements in the payload concept.
Eventually, three sequential payloads were defined, each of the latter payloads
adding to the experi_aents of-the _revious one..
_ Payload A consisted of engineering experiments and environmental sensors,
=__ but had no "active" engineering experiments (experiments that contribute to the
_- environment causing the interactions). Payload B had, in addition to A's
-_" experiments and sensors_ two "active" engineering experiments: a Charge Control
-7_.:f
-_i System (CCS) and a Plasma Interactions Experiment (PIX). Payload C added (to
Payload B) an experiment evaluating interactions with astronaut EVA systems.
Payload C is shown in Figure 4. AFGL has submitted a Space Flight Request (DD
Form 1721) for IMPS utilizing JPL's Payload C to the Space Test Program (STP).
__i" IMPS (AFGL-306) now ranks high on the priority llst for Shuttle flight under STP.
IHPS Baseline Definition
Before beginning the full-scale development of instrumentation for IMPS,
one must first develop a program baseline. For this purpose_ Jet Propulsion
• Laboratory, under AFGL's direction, recently began an IMPS baseline definition
effort to include:
a. Determination of wlmt will be required of the IMPS mission to satisfy
Air Force space-operations objectives.
b. Preliminary and final recommendations for selection (by AFGL) of engi-
neering experiments and environmental sensors for IMPS through the work of an
Englneerlng/Sclence Working Group (ESWG).
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9_'_@_' "'¸ ''_¸" '_" _"'" _'__ i_
:Z_t c. A recommended IMPS fmplementat_..or_ pl_n to serve as a guld@ for tlie
large-scale-future work to develop, test, integrate, and fly IMPS.
• d. A Cost estimate for the IHPS program (for later trade-off studies)°
_: IMPS FOLLOW-ON WORK
_:_i In general, the engineering experiments for IMPS will be obtained throogh
the AF laboratorles, NASA technology =enters, and other science and engineering
.... organizations that will be developing hardware and technology for future space
_ application. Because these organizations are looking forward to the successful
_ usage or operation of their hardware/technology in Space, they have shown a-strong
_'_i interest in the ItIPS program as a means of finding out how their hardware/tech-
_ nology will be affected by the space environment. AFGL will provide tO these
organizations support from the IHPS program to put together engineering experiments
_ involving their internally-developecL materials, equipment, or technologies. These
=_' experiments will be designed, fabricated, and tested under the direction of the
_-"_ of the particular AF laboratory, NASA technology center, or other S&E organization.
_._i : In most instances, the detailed work will be carried out through contracts with
-_,__ universities, research organizations, and industrial companies.
_d- [_",
_'_ Experiment _nd Sensor Development
--._,_.
...... Work on I_IPS instrument development will include:
_:'_ a. Selection of required engineering experiments and environmental sensors
_ .__ by AFGL.
. .%
_' b. Design of the individual engineering experiments.-)
:. c. Development and fabrication of the experiments and sensors.
. d. Testing of individual engineering experiments and environmental sensor
_-- packages at the builder's facility to ensure that they fulfill IMPS requirements .
" for making the variOus measurements. Testing to ensure that they conform to IMPS
_: guidelines regarding command and power distribution, recording and telemetry, etc.
" Testing to ensure the experiments and sensors meet Shuttle operations and safety
standards.
_'_ Integration and Shuttle Flight
w .... AFGL Will bring together the engineering experiments and environment sensors
obtained from the various organizations responsible for their development and
deliver them to the Space Test Program for integration. STP _¢iiI then become
responsible for ItIPS. Shuttle flight arrangements and scheduling will also be
handled by STP.
Data Analysis
y
• During the Shuttle flight of IMPS, there will be a need for real-time
_' monitoring of so_,_eof tile instruments. Although IMPS operation will be made
C
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O0000007-TSE08
essentially automatic, ear_e£ul monitoring wiLL be requLr.ed when an "active"
part o£ an _xperi_en_ (a phsnh_ source, for example) i9 turned on ..... It is _lso
important that during a slgnific_tnt ev_n_ (_n encounter t_lth-an auroral aro_
for example) the data-coll_ctio_ race be £ncr.eaeed, so as to permit late_ high-
time-reSolutlOn analysis of imo_nt phenomena. ..............................................................
After the flight of IrlPS aboard Shuttle_ the Space Test Program will provide
AFGL with data for the various engLneering experiments and environmental sensors.
Additionally, STP will provide orientation and geographic position of the Shuttle,
position and orientation of any packages moved out of the bay, information on
thruster fi_l=gs, "housekeeping" data, etc. Under a data utilization plan t
developed before the Shuttle flight, AFGL will distribute the data for analysis. '
The data will go not only to those responsible for the indlviduaZ experiments
but also to organizations selected to do Comprehensive analyses olivarious 13
interaction phenomena. Particular attention will be paid to correlating changes
in the physical properties of the environment with e_lanced interactions noted
on particular materials or equipment.
=_ Uitl_in the first year following a successful IMPS Shuttle flight, AFGL will
conduct a series of data workshops at which the IMPS data. would be made avail-
=_ able so that experimenters Can compare their results. Workshops would be con-
q
-_, fined to key topics such as contamination & materials degradation, or charging
,: & arc-dlscha_ges, or EMI generation, etc. By keying on a particular topic, it
should be possible to generate an authoritative report on that subject as the
output of the workshop. These reports can then be directed toward improving
relevant MIL-STD design guidelines and-test standards by providing the proper
-, en_ironmental interaction input,
CONCLUSIONS
The successful operation of the Interactions Measurement Payload on a late-
1980s Shuttle flight will lead to detailed knowledge of the effects of the polar-
auroral environment on materials, equipment and technologies of future space _"
systems. The output from IMPS will provide direct input to the development of
MIL-STD design guidelines and test standards for planned military space systems.
The data collected by IMPS can be used to validate computer-alded design (CAD)
tools that properly account for space-envlronment effects, _le utilization of
the information gathered from tile I}IPSmeasu=ements will prevent operational
failures due to unanticipated environmental effects and minimize costly down-
stream redesign of expensive sp_ce systems. Risks to spacecraft and crews
will be greatly decreased by the elIinination of uncertainties about the disrJap-
tlve effects of the polar-auroral environment.

iOE-POOR QLUALiTY
Figure 2. - Extravehicularactivityin space.
; Figure3. - Interactionsmeasurementpayloadfor Shuttle (IMPS)
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Interactions measurement payload for Shuttle

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