NASA TECHNICAL MEMORANDUM NASA Th-77923 

X-RAY SATELLITE STATUS REPORT - SECOND QUARIER 1985
 

Deutsche Forschungs- und Versuchsanstalt
 

fuer Luft- und Raumfahrt (DPVLR) 

Translation of "Roentgen Satellit Statusbericht, 2. Quartal 

1985," Deutsche Forschungs- und Versuchsanstalt fuer Luftund Raumfahrt (German Aerospace Research Establishment),
 

Cologne West Germany, Report No. WF2/8734, June 30, 1985, 

pp. 1-63
 

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
 

WASHINGTON, D.C. 20546 SEPTEMBER 1985
 

(NASA-TM-77923) X-RAY SATELLITE Status 
 N86-10273
 

Report, second quarter 1985 (National
 

Aeronautics and Space Administration) 44 p
 

HC A03/MF A01 
 CSCL 22B Unclas
 

G3/18 2747 
1985 

STANDARD TITLE PAGE 

1. Report No. 2. Government Accession No. 3. Recipront's Catalog No.

NASA TM-77923
 

4. Title and Subhtle 5. Report Date 

SEPTEMBER 1985
 X-RAY SATELLITE STATUS REPORT - SECOND QUARTER 6. Performing Organizati6n Code 

7. Aulhor(s) 8. -Performing Organization Report No. 

Deutsche Forschungs- und Versuchsanstalt fuer
 

Luft- und Raumfahrt (DFVLR) 10. Work Unit No. 

11. Coniroct or Grant No. 9. Performing Organization N... and Addr... I NASW.4006 

The Corporate Word, Inc. 13. Type of Report and Period Covered 1102 Arrott Bldg, Pittsburgh, PA 15222 TRANSLATION' 

&.. nsorgng Agency Name and Address NAT ONAL AERONAUTICS AND SPACE 'ADMINISTRATION 

WASHINGTON D.C. 20546 14. Sponsoring Agency Code 

15. Supplementary Notes 

Translation of "Roentgen Satellit Statusbericht, 2. Quartal 1985,"
 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt (DFVLR)
 (German Aerospace Rsearch Establishment), Cdlogne West Germany, Report No. 1F2/8734, June 30, 1985, pp. 1-63 

16. Abstract 

m overview of the second quarter 1985 development of the X-ray satellite 15roject is presented. It is shown that the project is ?roceeding according to plan and that the projected launch date 

Df September 9, 1987 is on schedule. An overview of the work
 :ompleted aAd underway on the systems, subsystbns, payload, assembly, gound equipment and interfaces is presented. Problem areas shown
 nclude cost increases in the area of focal instrumentation, the
 

tar sensor light scattering requirements, and postponements in
 

fhe data transmission subsystems. 

17. Key Words (Selected by Author(s)) 18. Distr;bution Statement 

Unlimited - Unclassified 

19. Security Clossif. (of this report) 20. Security Clossif. (of this page) 21- Na. of Pages 22. Price 

hclassified Unclassified 44
 
TABLE OF CONTENTS
 

1.0 Survey and Outlook
 

1.1 Status of Projects
 

1.2 Outlook
 

1.3 Survey of Problems
 

2.0 System
 

3.0 Mechanical Subsystems
 

3.1 Structure/Mechanism
 

3.2 Thermal Budget
 

4.0 Electric Subsystems
 

4.1 Energy Sources
 

4.2 Pyrotechnics
 

4.3 Cabling
 

4.4 Data Processing
 

4.5 Data Transmission
 

5.0 Payload
 

5.1 X-Ray Telescope
 

5.2 Wide Field Camera
 

6.0 Assembly, Integration, and Test
 

7.0 Ground Equipment
 

7. 1 Electric around ' ipbrF~quyient f-C SFl 

7.2 Mechanical Groinid ! tB-ifoir-
 t&XM-GCSflJ'
 

7.3 Optical Ground Sjpp6r-t-Eqaip-enf- OGSB)
 

8. Mission Safety
 

9. Launch Vehicle Interface­
10.0 
 Mission Operation
 

11.0 Sdhedule
 

12.0 
 Administrative Report
 

13.0 Appendix
 

13.1 Personnel Utjllzatij:Of
 

13.2 Key to Abbreviations
 
STATUS REPORT
 

1.0 Survey and Outlook /3*
 

1.1 Status of Projects
 

Summary
 

With regard to technical perfomance and costs, the project is
 

running according to plan. The valid schedule for EM- and FMcompletion on April 20, 1985, leads to a launch date on October
 

30, 1987. This corresponds to the contract milestone plan and,
 

taking the four-week buffer into consideration, meets with the
 

Launch__ 'date of September 9, 1987, agreed upon in the Payload
 

Integration Plan.
 

The FM-mirror system remains under critical pressure to meet
 

the schedule due to problems with the gold platilng
 

Documentation
 

Project Plan:
 

The project plan has not yet been presented to the DFVLR
 

board because of reservations regarding the data processing
 

concept during the mission.
 

Main Contract:
 

Contract addition No. 2 to the main contract was signed.
 

The reworked version of the interface fecificatofor the WFC
 

from May 9, 1985, was put into effect.
 

*Numbers in margin indicate pagination in the foreign text.
 

5 
NASA-STS Interface Documents:
 

An adapted version of the launch Site Support Plan (PIP-Annex
 

8) was presented by NASA as "Preliminary Issue."
 

The Phase 2 Safety Data Packet was sent to NASA, so that /4
 

the planned safety tests can be carried out as planned in
 

September and October.
 

Development and Production
 

Production of FM-instruments is to be continued as planned.
 

Test and Integration
 

The infeed of the WFC-EM for EM-integration is completed,
 

Infeed of the flight mirror pairs P3-H3 and.P4-H4 is completed in
 

the C/D contract. EM-integration corresponds to the planning
 

status of April 20, 1985.
 

Review
 

The ninth status review by the chief contractor was carried
 

out in May with NASA participating.
 

Milestones
 

No changes.
 

Problems
 

The schedule cannot be changed. Should the IABG plant become
 

unavailable for the solar simulation test of the STM, it would /5
 

be necessary to use a facility outside Europe to keep on
 

schedule. Cost increases in the area of focal instrumentation
 

exceed the average estimates for the payload in the project plan.
 

6 
1.2 Outlook
 

The next general talks with NASA on safety tests, as well as
 

on lift-off preparation and launch vehicle operation will begin
 

in the last weeks of September.
 

With regard to completion of EM-integration, the EM-subsystem
 

will be transferred from the auxiliary structure to the flight
 

structure.
 

The effects of the irregularities with the gold plating of
 

the flight mirror on the FM-schedule need to be clarified.
 

1.3 Survey of Problems 	 /6
 

Area 	 Type of Problem
 

1. Management -	At present, no problems with chief contractor.
 

2. 	System - Agreement with NASA on HRI random testloads has
 

not been reached.
 

3. 	Mechanical - At present, no problems.
 

Subsystems
 

4. Electric -	 Failure of the oven stabilized quartz in the 

Subsystems 	 data processing system needs to be clarified to
 

guarantee that sufficient operation safety
 

exists for the FM on this "Single-Point-


Failure" position.*
 

5. Telescope -	 The light scattering requirements of the star
 

sensor on the AKS-system cannot be satisfied
 

and need to be discussed.
 

- Assembly of the FM-mirror system has been
 

7 
interrupted 	due to irregularities in the gold
 

l,)j!ag-jof paraboloids P3 and P4.* 

6. 	Assembly, - Suitcase test date for JSC overlaps with EM-AIT
 

Integration planning by about one week.*
 

Test
 

- The possibility that the IABG test chamber /7
 

for the solar simulation test may not be
 

available when needed would necessitate costly
 

replacement measures.*
 

7. 	Ground - At present, no problems.
 

Equipment
 

8. 	Mission - Dragging construction patt delivery from MBB.
 

Safety
 

9. 	Launch - At present, no problems.
 

Vehicle
 

Interface
 

10. 	Mission - Mission operation and simulator development
 

Operation 	 suffer from understaffing.
 

- Data processing design not finalized.
 

11. 	Schedule - Postponements are anticipated in the subsystems 

of data transmission and building parts supply. 

(* Items 4, 5b, 6a, and Sb are problems recently under
 

consideration.)
 

2.0 System 	 /8
 

System Construction
 

Concluding detailed projects related to the interface on the
 

8
 
Shuttle included: 

-- current supply for heaters from the Shuttle over the SURS 

-- cable line from the SUNS to the ROSAT harness 

-- details of the SUNS plug assembly on the ROSAT structure. 

System Budgets
 

The summary of the measured mass characteristic values of the
 

components into a system-related value is still being prepared.
 

A review of the attitde measUremetbudggt is lOt yet---­

completed.'
 

System Documentation
 

A review of system and subsystem specifications is nearly
 

completed. Inclusion of DFVLR commentary is to be carried out by
 

Dornier.
 

3.0 Mechanical Subsystems
 

3.1 Structure/Mechanisms
 

A review of results of coupled analyses carried out by NASA
 

and MBB revealed that both calculations contained errors. After
 

clearing up errors, NASA presented results of another
 

calculation. Whether MBB will carry out another coupled analysis
 

is being determined at present.
 

The solidity analyses and investigations on fracture
 

mechanics were continued. The concept for structure verification
 

was established in the "Verification Control Sheets."
 

Verification for all structural components was begun using
 

measures outlined in these sheets.
 

9
 
The static load test was carried out successfully on the
 

structure. Results for channels and spans correlated well with
 

calculations. Distortion measurements remaining after the test
 

are of subordinate dimensions and lie within alignment
 

tolerances.
 

The Modal Survey Test was carried out by the IABG, since
 

DFVLR-Goettingen had retracted their offer to carry out the test.
 

At present, it is finder consideration whether the test can be
 

carried out by DS with IAGB test equipment This would save two
 

weeks.
 

It is anticipated that the STM-structure will be transfered
 

from MBB to DS on July 5, 1985.
 

Qualification of the telescope opening, as well as of /10
 

the antenna boom mechanism was completed successfully. There
 

were no problems.
 

The welding spot of a "roller leaf" broke during the
 

vibration of the isolator switch mechanism. The cause is being
 

investigated at present. Suggestions for a suitable test for
 

flight hardware are being considered. The thermal tests on the
 

isolator switch were completed successfully.
 

After completion of the documentation, the three OMmechanisms are available for AIT.
 

3.2 Thermal Budget
 

The projects for implementing the STS-fedl heaters are
 

running according to plan. The maximum temperatures of these
 

heaters were calculated for the Safety II Report. The
 

compartments were coated with thermal paint using lacquer
 

patterns.
 

10
 
Mission temperature forecasts were made available using the
 

readapted large nodal model.
 

At present there are no problems.
 

4.0 Electric subsystems
 

4.1 and 4.2 Energy Supply, Pyrotechnics
 

After delivery of the EM-electronics boxes (PDU, PCU, BCU,
 

Shunt, and Pyro) to the EM-Bus integration, the ADP ("Acceptance
 

Data Package") was made available and pr6duction documentation
 

for the FM-electronics boxes was readapted.
 

Mechanical production of the FM-electronics boxes was begun.
 

Preparations for the qualification of the batteries are
 

completed.
 

Development and production of the STM-solar generator is
 

nearly completed following mechanical adaption projects on the
 

satellite structure by MBB. Its integration into the system is
 

planned for the KW 30/85.
 

4.3 Cabling
 

The EM-laced wiring harness, consisting of the three parts-­

power/pyro/signal--was delivered for integration to the laced
 

wiring harness transport/integration frame in the middle of
 

April, 1985. The ADP was made available.
 

Adaptation of production documentation and preparation work
 

for production of the FM-laced wiring harness were begun.
 

II 
4.4 Data Processing /12
 

The DHS subsystem was tested at the end of June and delivered
 

to the structure for integration. Only small modifications need
 

to be discussed, if any are necessary for the flight model.
 

This delivery schedule means a delay of almost exactly two
 

months from the original planning. Unfortunately, these two
 

months became necessary to eliminate several errors and
 

disturbances, and--as already reported--to adapt the necessary
 

software to the limited storage facility. This delay has been
 

taken into account in the present schedule, status as of April
 

20, 1985.
 

Several disturbances with and failure of the furnace
 

stabilized quartz are cause for concern at present. This has
 

given rise once more to discussions about the redundant
 

construction of this single-point-failure-construction part.
 

Due to delivery difficulties in the case of construction
 

parts tempered to withstand radiation, delays on the DHS-FM must
 

be feared.
 

4.5 Data Transmission /13
 

Transponder
 

Delivery of the transponder is expected on July 12, 1985.
 

Integration into the EM-Bus had been planned until now for July
 

11, 1985. Effects on EM-integration completion can be
 

circumvented.
 

Decoder
 

Following conclusion ofsubsequent work, the EM was reinstalled in the EM-Bus.
 

12
 
Antenna
 

A repeated measuring of the radiation diagram following
 

mechanical changes in the hybrid building blocks could not be
 

carried out because of bottlenecks in the measuring area
 

condensor plates. For this reason, an antenna for a test
 

integration with the transponder is being temporarily prepared.
 

This will circumvent effects on EM-integration completion.
 

4.6 At4tude 	Measurement and Control. 

Star Sensor: 	 EM-tests completed, preparations for FM-production
 

begun.
 

Gyroscope:. 	Execution of EMC-test on the EM, preparations for FMproduction begun.
 

AMCS: 	 Preparation of EMC-tests for the EM, preparations for FMproduction begun.
 

Reaction Wheels: EMC-tests on EM still outstanding; FMproduction (wheel and WDE-tests and plates) are
 

begun.
 

Schedule Situation for Subsystems
 

Subsystem tests (safe mode, rotary table tests, checkout
 

mode) are being carried out. Delivery of an operational EMsubsystem is planned for the beginning of September 1985 and
 

would be available for the Pre-IST of the EM-Bus. Mass-produced
 

models will be used again when necessary for previously run EM-


Bus integration activities. This will not disrupt the currently
 

valid EM-integration schedule, status as of April 20, 1985.
 

13 
5.0 Payload /15
 

5.1 X-Ray Telescope
 

5.1.1 Telescope-QM
 

Since all components were completed on schedule, the
 

integration of the telescope's qualification model (QM) could be
 

completed on May 24, 1985. Afterwards the vibration
 

qualification of the telescope QM (ordal and random vibration)
 

was carried out on the new device of the IABG with four
 

simultaneous vibrators. In spite of a failure of the test device
 

which lasted several days, the qualification was completed
 

successfully on June 25, 1985.
 

Test data are now being evaluated. At the same time, the
 

telescope is being disassembled under control to test if the
 

mechanical adjustments remained in tact.
 

5.1.2 Mirror System
 

The mirror system-STM was installed in the telescope-QM.
 

Projects on the flight mirror system: While preparing the
 

assembly of the flight mirror system, both flight mirror pairs,
 

P4-H4 and P3-H3, were adjusted in the C/D contract. The
 

paraboloids, P4 and P3, which were mounted first, were jiated
 

with gold by Balzers Co. In spite of careful cleaning and
 

testing of the surafces before platfgo there are small areas on
 

the gold layers which do not perfectly reflect the light of a
 

highly sensitive testing device. This error had not been
 

observed by the VM-mirrors.
 

Since it is not clear if the X-ray reflectivity is /16
 

disturbed in this or even other areas, the assembly of the mirror
 

system was stopped temporarily. Investigations of the error must
 

14
 
be carried out. This delays work on the mirror system assembly
 

by about five months. At present, measures are being considered
 

which would prevent missing the scheduled integration of the
 

mirror system into the telescope.
 

Because of the problem with the gold damping and the
 

postponement of the mirror system assembly resulting from it, the
 

approximately four-week delay of the production of the Invar
 

structure parts is not critical.
 

The status of the projects in this contract, separate from
 

contracts for the entire system, for producing the individual
 

mirrors of the flight model is as follows:
 

The mirror pairs P4-H4 and P3-H3 were received from the
 

DFVLR-PLe and adjusted in the C/D-contract. Mirrors PI and P2
 

were process treated, X-ray-optically measured and accepted. The
 

hyperboloids Hl and 112 can be repolishe4 easily to attain the
 

specified surface quality.
 

5.1.3 Focal Plane Instrumentation
 

The development and production of the FI underwent the
 

following progress at MPE during the time involved in the report:
 

- Conclusion of EM-component tests,
 

- Conclusion of FI-EM-integration,
 

- Execution of a reduced thermal vacuum test with FI-EM,
 

- Determination of mass characteristics of FI-EM,
 

- Execution of "Pre-Environmental Review" for HRI at SAO /17
 

through GSFC,
 

- Start of production of FI-FM-components,
 

- Delivery of FI-mass models for telescope vibration, and
 

- Preparation of documentation for FI-EM-adjustment.
 

*DFVLR-PL = DFVLR Project Management
 

15 
Furthermore, the design of the structure verification plan of
 

the F1 and the F1 supports were worked on at the DFVLR-Pl for
 

NASA safety inspection (phase 2) under agreement With MPE.
 

Open-ended problems from the last status report were taken up
 

again:
 

- Following discussions between DFVLR, NASA/GSFC and DS, an 

approximation of the understandings regarding random 

vibration was reached. DS agreed to define the most 

realistic possible input loads into the FI, based on the 

telescope vibration tests. From this, readapted HRItestloads can be derived. 

- The question of the FI-FM-delays remained unanswered.
 

- The problem of the carousel drive is solved. Due to the 

late date, at which DS needed the FI-EM, MPE was able to 

provide a suitable substitute drive. The FI-EM will be 

delivered with the substitute drive. 

5.2 Wide Field Camera /18
 

After receipt of the two technical memoranda No. 29 and 30
 

from DS, the level 0 document "Spacecraft/XUV Wide Field Camera,
 

Interface Requirements" was reworked. The currently valid
 

version is 'the one from May 9, 1985 (received from DS by TA 36).
 

Of the seven existing requests for waiver,
 

RfW EM LU 001 to 004 (EMC) was approved,
 

RfW EM LU 005 (EMC) was withdrawn,
 

RfW STM LU 001 (vibration) was approved, and
 

* RfW STM LU 002 (vibration) is being processed.
 

The small deficiencies on the WFC's electric ground auxiliary
 

instruments (EGSE) noted in the protocol at the time of the
 

16
 
adjustment (March 1985) have, in the meantime, been completely
 

eradicated.
 

In April, the DFVLR-PL checked the ADP of the EM of the WFC
 

at MSSL. On the basis of spot checks in the presence of DS, the
 

good working condition of the EM was verified,and its fundamental
 

transmitting ability was licensed.
 

All points which remained open could be decided upon in about
 

eight weeks.
 

In June, the engineering model (EM) of the wide field camera
 

was:
 

* sent from England to DS,
 

* accepted'after a successful trial run of the DFVLR-PL, and
 

* adapted in accordance with DS' contract.
 

Adaptation took place ahead of schedule, namely about /19
 

two weeks before the date anticipated in the AIT-plan.
 

The routine interface talks on May 22 in the framework of the
 

status meeting at DS served to clarify unanswered problems.
 

The data packet for the Phase 2 Safety Test was prepared by
 

the DFVLR-PL from the WFCC-reports and sent to DS. A possible
 

problem:. parts of the rose bearings on the struts are made of a
 

steel which tends toward stress corrosion according to NASA
 

safety classifications.
 

In mid-June, talks on mission operation were held in the SOC
 

with marked English participation (10 people).
 

Outlook for the next quarter:
 

No problems are seen with regard to on-schedule STMadaptation.
 

17
 
6.0 Assembly, Integration, and Test /20
 

Bus Integration
 

According to the schedule, this began with the preintegration of the subsystems on an auxiliary structure.
 

The following were carried out: integration, test of the EMlaced wiring harness, of energy supply and of the decoder.
 

The data handling system (DHS) was prepared for integration.
 

Telescope Integration
 

Preparation of the FI-mass model took place on schedule.
 

Since the heat shield was prepared punctually, as well, telescope
 

integration could be carried out according to plan. The
 

vibration test at IABG was successful. The optical measurements
 

did not deviate from those made before the test. After the
 

remaining hardware is installed, transmission to the S/C can take
 

place promptly.
 

WFC-Adaptation
 

The WFC and its component EGSE were delivered by RAL, and
 

following successful acceptance tests it was adapted to the DS.
 

The WFC-integration manual has been released, which allows S/C
 

integration to be carried out according to plan.
 

EM-FI Preparation /21
 

Contrary to the assumption feared up until now, that the EM-


FI would be delivered with the FM carousel drive, which would
 

require adaptation later at the MPE, the MPE was able to procure
 

the substitute drive remaining in the EM-FI on-time, so that no
 

additional time was required.
 

18
 
AMCS Mass Models
 

AMCS mass models are being constructed until the modal survey
 

test, since the EM probably will not be delivered on-time and
 

thermically representative STM are too expensive.
 

RF-Compatibility Suitcase Test
 

Dates for carrying out the tests were agreed upon with the
 

GSOC and JSC. An overlap with the EM-AIT schedule still has to
 

be attended to.
 

Solar Simulation Test at the IABG
 

During the period of January 1 to March 4, 1986, set for our
 

test, the TV-SAT Project wants to use the WSA-chamber from
 

January 20 to February 24, 1986. Two talks with the IABG and one
 

with BMFT were held to pursue avenues which would make it
 

possible for both projects to be carried out.
 

The IABG plans an additional integration room to make
 

parallel projects possible during rigging and the dismantling
 

phases. In the meantime, relevant drawings have been distributed
 

to the projects for their consideration.
 

A change in schedule one way or the other would affect the
 

projects SKYNET or HIPPARCOS.
 

IABG intends by mid-September 1985 to distribute a suggestion
 

corresponding to the detailed project planning and actual project
 

status; it is possible, however, that -this suggestion will not be
 

compatible with the ROSAT schedule.
 

Alternatives to the IABG-WSA for the proposed time are only
 

available outside Europe (JPL).
 

19 
FM-Integration
 

It was agreed upon with the chief contractor, to integrate
 

the subsystems of the flight model on to the exisitng auxiliary.
 

structure, just as with those of the EM. This procedure saves
 

time and allows more flexibility.
 

7.0 Ground Equipment /23
 

7.1 Electric Ground Equipment
 

Developmental projects and tests on various software packets
 

were continued.
 

The Interface Acceptance Test for integrating the FI-EGSE
 

into the ROSAT-EGSE was concluded successfully. The monitoring
 

tables. for the ESA-checkout-software for the system test were
 

presented and reworked a number of times. ETOL-test sequences
 

for the integration system were developed for power supply
 

system, decoder, focal instrumentation, and wide-field camera.
 

More module function tests were made on the TT&C and on the
 

S/C-EGSE software. Performance tests including simulation of
 

transmission of telemetric data were carried out successfully
 

with the FI-EGSE and, also, with the WFG-EGSE. Service programs
 

were developed for AIT-support.
 

System function tests were carried out in the TT&C-station
 

and the S/C-EGSE.
 

7.2 Mechanical Ground Equipment /24
 

A large part of the MGSE is ready for production, has been
 

tested and is already in use (S/C-ttansport container, vibration
 

adapter, telescope picture mounting frame, cargo sling, etc.),
 

To ensure application safety, an additional telescope repository
 

20
 
must be built'to avoid damage to the telescope during removal of
 

the separate carrier ring. A new cargo sling was required for
 

assembling the finished mounting of the carrier support
 

structure. This allows the support structure to turn from the
 

vertical to, the horizontal position.
 

Production-of the vertical trolley began on schedule.
 

Preparation of test and operation instructions was continued.
 

7.3 Optical Ground Equipment
 

The optical testing stand was employed successfully during
 

integration of the telescope-QM.
 

8.0 Mission Safety 	 25
 

STS Safety (Flight and Gr'ound Operations)
 

The integrated data packets for safety testing for Phase 2
 

were delivered by the chief contractor on schedule. On July 10,
 

1985, they were handed over to the DFVLR-PL and, following
 

internal review and approval by project directors for NASA-GSFC,
 

were sent'to the NASA-JSC review board.
 

The project directors count on a confirmation of the date
 

decided on with NASA in May 1985 (beginning of September/October
 

1985) for safety tests of flight and ground operations.
 

The status of documentation felevant to safety is as follows:
 

* 	FI structure verification plan has been finished by PT,
 

commented on by MPE, and integrated into the test packet
 

for Phase 2 safety testing.
 

21
 
* 	Adaptation of material lists has been completed. The
 

results, set down in Revisions No.- 4, were sent to NASA-


GSFC project directors at the beginning of May 1985 for
 

review.
 

22 
The test pattern of the circuits produced by Reinshagen Co.
 

according to Mil-C-27500-24-TF-2-MI4-019-0 and Mil-W-22759/17, 25
 

passed the combustability test in accordance with NHB 8060.1B at
 

NASA.
 

This information was relayed to the company by HAN at the
 

beginning of May 1985.
 

* Dependability /26
 

The FMECA and SPF lists for the S/C subsystems were handed
 

over to the DFVLR-PL. At present they are being analyzed.
 

Delivery of the system analysis, which also covers operational
 

aspects, has still not taken place.
 

* Quality Control
 

By the end of the period covered in this report, 79
 

disturbances and second stage MRB's involving EM and FM
 

components of the satellite system had been checked and evaluated
 

by the project directors. Supervision of MRB decisions released
 

to the public is controlled by lists which in the future will
 

also contain information on the status of decisions affecting
 

disturbance controls.
 

On June 24, 1985, a quality audit on the production of twosided PCB's (printed circuit boards) was carried out at MBB.
 

This audit became necessary after MBB had submitted three
 

"requests for waivers" 
(RfWs) arising from the MBB-process for
 

the decoder, star sensor electronics aid AMCE. These requests,
 

directed to other ESA-qualified producers, suggested alternatives
 

to the use of PCB's. The results of this audit were
 

overwhelmingly positive. It was determined that MBB is suited to
 

fulfill the technical requirements and removal criteria of the
 

ESA-PSS-50 (August 1979). The RfWs were approved.
 

23
 
It was announced that, in the meantime, MBB has entered a
 

qualification contract for two-sided PCB's with ESA. To date,
 

the first test pattern has been presented to ESA and tested /27
 

by them. For this reason, it was agreed that MBB report on its
 

progress with ESA-qualification as part of the status report.
 

* Central Construction Part Acquisition
 

In the period covered by this report, two talks were held (on
 

May 21, and June 26, 1985) on the status of construction part
 

acquisitions. The following outlines this status at the end of
 

the report period:
 

** Acquisitions
 

- The agency was able to avoid further delays in delivery 

of construction parts by increasing the number of 

workers and through organizational measures controlling 

intake of goods and transit storage. 

- Alternative plans were worked out and accepted regarding
 

the grave delays still existing on the delivery of "line
 

items (LI's).
 

An alternative plan for counteracting delays in the
 

production of the FM-construction groups AMCD and DPS
 

(DS-portion), resulting from an export license which is
 

still unavailable for two radiation-proof RCA CMOS
 

construction parts from the US State Department, has yet
 

to be worked out. At present, there are justified hopes
 

that the US State Department, encouraged by NASA, will
 

issue to RCA the export license for these parts by the
 

middle of July 1985.
 

Of the 30 "upgrading" construction parts, there are /28
 

presently 20 being tested at EPI Co. in Wiesbaden. In the first
 

24
 
week of July, this company intends to carry out a test
 

documentation control and, also, a goods intake control (WEK),
 

which is to be combined with the last function test at the
 

company, since MBB cannot carry out any WEK on these construction
 

parts due to technical problems.
 

The remaining 10 "upgrading" construction parts Mill be sent
 

to the testing houses of EPI and Electronics Central (DK) in July
 

1985. Those construction parts which are needed most by the user
 

have priority.
 

The project directors are working presently on two
 

acquisitions' lists for internal use. They are based on overall
 

acquisitions and the agency's "delivery delay" lists. These
 

lists will contain the most important information on the delivery
 

status of LI to the 12 users and/or delivery measures to avoid
 

hardware delays for the users.
 

** Reduction in Quality of Delivered Construction Parts
 

The discoloring of connections located directly at the
 

discharge from the "dual in-line" housings, discovered during the
 

WEK on integrated CMOS-circuits (IC) from the SGS Co. (F), were
 

the subject of an MRB held on April 25, 1985 at SGS. During this
 

MRB, three IC's, subjected to an accelerated moisture test by the
 

SOS Co., were handed over to MBB/ERNO, DS, and ESTEC for error
 

analysis. The results of error analyses are now available. So
 

far they have shown that discoloring has no negative effects /29
 

on connection quality. Upon the suggestion of the agency, the
 

affected and already tested CMOS IC's were immediately delivered
 

to the user, without changing the packaging.
 

The delivery delays resulting from the involved CMOS IC's
 

have not had any effect on the course of the project.
 

25
 
9.0 Launch Vehicle Interface 	 /30
 

Private discussions wdre held between DS and NASA
 

representatives during the ninth status discussions from May 20
 

to 23, 1985. They discussed thermal, structural and launch
 

vehicle interfaces (flight/ground). On May 28, 1985, the results
 

were summarized by the DFVLR. The results of the thermal and
 

structural discussions are recorded in Sections 3.1 and 3.2.
 

IOD-A-18410
 

The participants 	in talks on launch vehicle interface
 

presented a tentative "draft version" (Feb. 15, 1985) ICD (with
 

commentary from DS made on May 6, 1985) for discussion and final
 

draft., It was agreed that NASA-JSC review all commentary and
 

present an improved tentative version of the ICD to the project
 

directors by June 30, 1985.
 

The "design review" of the OIB was postponed from June to the
 

end of September 1985, since discussion results on the electric
 

setup of the OIB call for a reworking of the related document TN2002-2180 DS/017 defining its electrical interfaces. This
 

adapted version could not be ready before the end of June 1985.
 

* . PIP-Annexes 

* 	PIP-Annex 2: NASA-JSC will provide the 'basic" annex by
 

August 30, 1985.
 

* 	PIP-Annex 4: NASA-JSC will send DFVLR forms which it /31
 

will fill out based on a NASA master
 

project.
 

* PIP-Annex 5: NASA-JSC will provide the basic version by
 

September 15, 1985, and include results of
 

the GSOC interface discussions on May 20,
 

26
 
1985, in Oberpfaffenhofen.
 

** PIP-Annex 8: 	 The reworked version, "Preliminary Issue,"
 

was handed over at the launch vehicle
 

interface talks.
 

* Suitcase Test 	at NASA-JSC and JPL
 

The dates for the suitcase test at JSC were set by NASA.
 

All necessary information on test set-up and the equipment
 

lists were made available to NASA-JSC at the end of May 1985.
 

Consignment of the test plan for the "Suitcase Test", agreed upon
 

with NASA-JSC on May 28, 1985, is planned for the beginning of
 

September.
 

Dates
 

It was agreed with NASA to group the next talks on lift-off
 

preparation and launch vehicle operation around the Phase 2
 

safety tests for flight and ground operations at .JSC and KSC
 

(planned for October 2, 3, and 10, 1985).
 

* 	 Status of NASA Modifications arding t Pf 6 Dec. 3, 1985: 

Figure 15-1 /32 

- RSGF-Mock up : 	delivered on March 15, 1985 

(planned return to NASA: March 15, 

1986) 

additionally:
 

* 	Retention Spring : delivered on May 22, 1985
 

(Flight-Type)
 

- RSGF-FM : 	requested delivery date: April 30, 

1986 

27
 
SURS-Combination : the delivery date of Sept. 01, 1985,
 

(Assembly/Pigtail/ upon agreement with Dornier was postbonding strap) poned to Nov. 29, 1985, in order to
 

incl. install "repluggable" version
 

documentation
 

Confirmation of the following dates were made by telephone
 

with NASA:
 

RSGF-Mock up: return to NASA: March 15, 1986
 

and RSGF-FM : delivery date: April 30, 1986
 

10.0 Mission Operation /33
 

Work structure planning, scheduling, and documentation for
 

the ground operation system were reworked and coordinated. A
 

review of mission operation requirements was planned for Fall
 

1985.
 

Flight Operation
 

The concept of the experiment operations requirements
 

document (EORD) was presented and commended to the MPE for
 

completion. It was determined that MPE should coordinate and
 

represent the requirements of all experimenters in dealings with
 

the GSOC in the EORD.
 

Network Operation
 

Definition of network support system requirements was
 

continued with JSC assuming responsibility for determining the
 

"Remote POCC." NASA has agreed to the use of American ground
 

stations in emergencies.
 

Mission Planning and Analysis
 

Implementation of the post-facto site determination software8
 
was begun. Further analysis of site-regulating division
 

requirements for ground operation system was undertaken. Mission
 

.planning requirements were discussed in talks with MPE.
 

Facilities /34
 

To simplify completion of projects, plans were set forth to
 

devise the data system compatibility test originally planned with
 

S/C in Weilheim in such a way that mission operation
 

installations can be connected with S/C and a system test place
 

at Donier or IABG.
 

An analysis of WT-DV's off-line computer's capacity to
 

support ROSAT requirements was introduced, taking requirements of
 

all projects into consideration.
 

The GSOC-commando system was extended to a sender rate of 1
 

kbps.
 

Insufficient investment funds for analog tape recorders have
 

not as yet become a problem, since the test for which they are
 

necessary was postponed until the beginning of 1986.
 

AMCS-Simulator
 

The simulator concept was completed.
 

The development of simulator hardware was begun at Dornier
 

under the conditions of the ROSAT phase C/D-contract.
 

Software requiremehts were completed at the GSOC about eight
 

weeks behind schedule. Projects for creating software--with the
 

exception of entries from the British project partners--were not
 

yet begun because of manpower deficiencies (approximately twomonths' delay). A related request for special financing has not
 

yet been decided upon by the BMFT.
 

29
 
11.0 Schedule /35
 

Planned Dates
 

Currently valid schedule: In agreement with the contract
 

milestone plan, EM, QM, STM AIT, and FM AIT on April 4, 1985, all
 

indicate October 10, 1987, as the lift-off date.
 

In the PIP, NASA scheduled Septeiber 30, 1986, as the liftoff date (reference milestone "ready for launch"). Taking into
 

consideration the four-week buffer before transport of the flight
 

unit to the launch pad, this date will be kept.
 

Actual EM-Status
 

Considering the schedule on April 4, 1985, EM-integration
 

shows no delays which cannot be avoided by measures such as:
 

sequence readjustment, overtime, or use of robots.
 

Actual FM-Status
 

Delays in FM-integration have thus far been qualitative.
 

Their quantitative effects must still be reviewed.
 

30 
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I () n ' 
prepared: ROSAT Original Schedule: July, 16. 1984
 

Missin Ground Ops Mgr. MISSION GROUND OPERATIONS Last Schedule Change: June, l8. 1985
 

COSC/DFVLR Status as of; June, 18. 1985
 

Page I of 3 

1985 1986 1987 19889 

Work Packages: 
 1988 1989
 

IQQJJI.tIO CR0INn OPS COORDTNAT-ON PO 

00 FLIGHT OPERATIONS 

__210 
 LORD 
 4O f 

Mission Cpa System Def CMOS-Plan)
 

230 Functional S/W Requ.
 

ZAU Flight Operations Plan
 

250 Flight Operations ProcedurA
 

260 Performance Analysis and Control
 

0220 


270 Orbit and Attitude Ops
 

.280 Sequence of Events
 

300 NETWORK OPERATIONS
 

310 Requirements Defin. (PR: STRD)
 

320 Network Operations Plan
 

33 Network Operations Procedures
 

340 Control Center Operations
 

350 Ground Station Operations
 

360 MDR/EDR Tape Generation
 

. ,00 MISSION PLANNING AND ANALYSTS SUBSYSTEM 

410 Mission Analysis and Planning-- 1----­

420 Definition of Subsystems 

4_430 Attitude Determination
 

0 PRELIMINARY 1) TLM+CMD Requirements L = Launch
 

0 BASELINE 2) OPS+ATTITUDE Requirements EOM = End of Mission
 KUINALE
 

UPDATE 

ARK-VENT
 
prepared- " ; AS ROSA? Original Schedule; July, 16. 1984 
 

Mis s round Ops'gr. SSPa 
 HISSION GROUND OPERATIONS Last Schedule Change: June, 18. 1985


GOSC/DFVLR Status as of: June, 18. 1985
 

Work Packages 
 e2 of 3


*985 
 1986 
 1987 
 198a
 

J JJSO0 J00OD1i ASN F IJSONJDIJPHJA IJ J ASUND0
 

1.440
 Attitude Control
 

__450 
 AMOS Performance Analysis8
 

460 Orbit Determinqtion and Prediction
 

500 DATA SUBSSTESHS
 

510 Command System ConfiguratiLn
 

515-rn Station Configuration~ _ 530 Data Compression and RoutinI 

540 CSOQLS/kC. That Tnrerfsre,
 

__ 560 Off Line Computing Facility 

_.1-570 Communication System 

1600 AMCS SIMULATOR


610 Simulator Concept
 

620 Interface System Development
 

630 Dynamics and Sensor Simul. S/W
 

650 Integration and Test
 

660 Operations 

O PRELIMINARY i) DOSY-EGSE/GSOC Data I/F implemented and teted o) BASELINE' 

I INAL,


V UPDATE


J MARK-EVENT 
repared: -- ROSAT Original Schedule; July, 16. 1984 

Miss Ground Ops Mgr. MISSION GROUND OPERATIONS Last Schedule Change: June, 18. 1985 

COSC/DFVLR Status as of: June, 18. 1985 

Page3 oft3 

lork'Packages 1985 1986 1987 1988 1989 

*T7-(F-IEST AND TRAININGJJ ASO DJ ii 501 DJF J JASONIF JIASONO JfHA JJASONO 

710 RF Comp. Tests 

720 Data System Comp. Tests 

730 End--to-End Tests 

7_40 Interface Tests 

750 Network Ops. Tests and Training __ -

76 raft/Mission Ops. Tst and Trail 

t 

810 RT Telemetry S/W 

820 Command Verification S1W 

'830 S/C Performance Analysis S/W 

840 Data Selection S/W . 

850 MDR/EDR Software 

REVIEWS 

MOS Requirements Review 

MOS esigTn-Review 

OS Readiness Review 

Plight Ops flandbook 

0 PRELIMINARY 

cA [ BASELINE 2,FINAL

UPDATE' 

MARK-EVENT
 
13:0- Appendix 

,'3 1' Personnel Inventory fo DFVLR-PT an'd DFVLR-WT 

IDFVLR RdNTG ENSATELLITStus

30.06.85 PT-WF2 

36 
L ____/VT._N,___ f 

Personnel- Inve'norsf fT?­l DF-VCR-PT 

(F T(Man-months') - STATUS' 30.06.1985 

-er 4 ea jlll . " 4 I f 

Cat ______________________, 

12/84 13.0 8.2 q~Ida]Atapriodjldeal1.85 13.5 

Aeu 

8.1 

Pria 

2/85 

il~alh Actua P6Thad Idj1 j ti 

13-. 8L S..5 6 3/5. V____1 S ______ 

Category

tCatpgory II

I 3.5 

4.0 

0.9 

4.1 

3.5 

4.0 

1.0 

3.5 

3.5 

4.0 

1.0 

3.1 

3.5 

4.0 

1.0 

3.4 

20.5 13.2 21. 0 12.2 21J. 12 _ __ 2 13.5 

"i~at -12 

pateA ir 

l1 tiryII 

l -

4/8 

.... 

, 

13.5 

3.5 

4.0 

9.3 

1.1 

3.9 

5/85 13.5 

3.5 

4:0 

9.6 

1.1 

3.9 

6/85 13.5 

3.5 

4.0 

10.8 

1.1 

.3.7 

.T=joa --21 .0 1 14.3 21.0 14.6 21.0 15.6 0OO 

ff. T 

.<e 
T Per!onnel Inventory for DFVR-WT 

(Ka)n7months ) STATUS: 30.06.1985 sA.rLLI _r$,vTP§ (Mn.mots .. -__KP;;!'dovJ______ -- _ Period'Ide - I .....dealAtalPeriod ideal AtualPer'iod Ideal L~tuallei Iezl:ti 

Category I 1/85 6.0 2/85 6.0 3/85 6.0 4/85 6.0 5.4
 

qqt_-E-ry 11 6.0 6.0 6.o 6.0 2.8
 

Cate.gory III 1.0 1.0 1.0 1.0 0.2
 

Total - 13.0 5.6 13.o 7.6 - 13.o .._4.i. 1 13-n - _ 

--- i0.5 2.8* 10.5 2.8* 10.5 2.8* 10.5 2 ntractors 
 .8* *Aerage

for.-first 


of yea
 Category I 5/85 6.0 6.3 6/85 6.0 6.1 hal 


'ategory II .- 6.0 3.1 6.0 2.9 4
 

Category II 1.0 0.2 1.0 0.2
 

Total 13.0 9.6 13.0 9.2 " Contract, o m...__ 10.5 2 8* 1 0 c 2.8 

'J
 

0
 

I 
13. 2 Key to Abbreviations'
 

ADP Acceptance Data Package 

AIT Assembly, Integration and Test 

AMCD Attitude Measurement and Control Data Unit 

AMCE Attitude Measurement and Control Interface 

Electronics 

AMCS Attitude Measurement and Control Subsystem 

BAT Battery 

BCU Battery Control Unit 

Bit. Sync. Bit Synchronizer (Synchronization) 

BMFT Bundesminister f~r Forschung und Technologie 

CCD Charge Coupled Device 

CCL Charge Current Limiter 

C&DH Command and Data Handling 

CEL Control Electronics 

CFK kohiefaserverstarkter Kunststoff 

CFRP Carbon Fiber Reinforced Plastics 

CITE Cargo Integration Test Equipment 

Cmd Command 

CPU Central Processing Unit 

CSA Charge Solar Array 

CSS Coarse Sun Sensor 

CZ Firma Carl Zeiss 

DC Direc Current 

DEC Decoder 

DFVLR Deutsche Forschungs- und Versuchsanstalt fUr 

Luft- und Raumfahrt 

DFVLR-PL DFVLR-Proj ektleitung 

D FVLR Status:
 RONTGENSATELLIT 

PT-WF2 30.06.85 

39
 
DHS 


DMA 


DMOD 


DNEL 


DPS 


DS 


ECS 


EED 


EEL 


EGSE 


EM' 


EMC 


EOL 


EORD 


EPD 


ESA 


ETOL 


EUV 


FI 


FLS 


FM 


FMECA 


FWHM 


GF 


GSE 


GSFC 


GSOC 


GVS 


GYP 


DFVLR 


PT-WF 2 

Data Handling Subsystem
 

Direct Memory Access (Direct Assess to Memory)
 

Demodulator
 

Disconnection of Non-Essential Loads
 

Data Processing System
 

Dornier System
 

Environmental Control System 

Electro-Explosive Device 

Experinent-Electronics 

Electrical Ground Support Equipment 

Engineering Model 

Electromagnetic Compatibility -. 

End-of-Life 

Experiment Operations Requirements Document 

External Power Dumper 

European Space Agency 

ESA Test Operation Language 

Extreme Ultraviolet 

Focal Plane Instrumentation
 

Fiducial Light System
 

Flight Model
 

Failure Mode Criticallity Analysis
 

Full Width at Half Maximum
 

Grapple Fixture
 

Grdund Support Equipment
 

Goddard Space Flight Center
 

German Space Operations Center
 

Gas Supply System
 

Gyropackage
 

Status:
 RNTGENSATELLIT 


30.06.85
 

40
 
GYPE 

GYPS 

Gyropackage Electronics 

Gyropackage Sensor 

HC 

HEAO-2 

HK 

HP 

HRI 

Heater Control 

High Energy Astronomy Observatory ("Einstein") 

Housekeeping 

High Power 

High Resolution Imager 

ICD 

INVAR 

IST 

Interface Control Document 

(Handelsname flr eife besondere Stahllegierung) 

Integrated System Test 

JSC Johnson Space Center 

kbps 

KSC 

Kilobit per second (deutsch: kbit/s) 

Kennedy Space Center 

LCL 

LED 

LHC 

LP 

. Latching Current Limiter 

Light Emitting Diode, 

Left-hand Circulation 

Low Power 

MA 

MAC 

Xbps 

MC 

MCC 

MCP 

1DM 

MED 

MES 

Mirror Assembly 

Mirror Attachment Cone 

Megabit per second (deutsch: Megabit/s) 

Magnetic Coil 

Missiep Control Center 

Microchannel Plate 

Multiplexer/Demultiplexer 

Magnetic Electron Deflector 

Mechanisms Subsystem 

e rD FVLR RdNTGENSATELLIT Status: 

PT-WF2 30.06.85 

41 
MGSE 


MLI 


MM 


MOU 


MPE 


MPG 


MPSS 


MRB 


MSA 


MSSL 


MUC 


MUDAS 


MVL 


NASA 


NRZ/L-Code 


NSI 


OBC 


OGSE 


OIB 


OSR 


PCU 


PDU 


PETS 


PGHM 


PHP 


POCC 


PPF 


# DFVLR 


PT-WF 2 

Mechanical Ground Support Equipment
 

Multilayer Insulation
 

Magnetometer
 

Memorandum of Understanding
 

Max-Planck-Institut fUr Physik und Astrophysik,
 

Institut fUr Extraterrestrische Physik
 

Max-Planck-Gesellschaft
 

Mission Planning and Scheduling System
 

Material Review Board
 

Main Solar Array
 

Mullard Space Science Laboratory
 

Multi-Use Container
 

Modular Universal Data Acquisitioeani
 

Control System
 

Main Voltage Limiter
 

National Aeronautics and Space Administration
 

Non-Return-to-Zero/L-Code
 

NASA Standard Initiator
 

Onboard Computer
 

Optical Ground Support Equipment
 

Orbiter Interface Box
 

Optical Surface Reflector
 

Power Control Unit
 

Power Distribution Unit
 

Paylo&'d Environmental Transportation System
 

Payload Ground Handling Mechanism
 

Paraboloid-Hyperboloid Pair
 

Payload Operations Control Center
 

Payload Processing Facility
 

RdNTGENSATELLIT 
 Status:


30.06.85
 
PSE Payload Support Equipment
 

PSK Phase-shift Keying
 

PSPC Position Sensitive Proportional Counter
 

PSS Power Supply Subsystem
 

PYB Pyrotechnics Electronic Box
 

QM Qualification Model
 

RAL Rutherford Appleton Laboratory
 

RE Radiated Emission
 

RF Radio Frequency
 

RfW Request for Waiver
 

RMC Right-hand Circulation
 

RMS Remote Manipulator System
 

ROSAT R6ntgensatellit
 

RS Radiated Susceptibility
 

RSGF Rigidized Sensing Grapple Fixture
 

RSS Rotating Service Structure
 

RT Real Time
 

RW Reaction Wheel
 

RX Receiver
 

S/C Spacecraft 

SERC Science & Engineering Research Council
 

SEU Single Event Upset
 

S/L Serial Load
 

SOC Science Operations Center
 

SPF Sihgfe Point Failure
 

SPL Code Split Phase Level Code
 

SSM Single Surface Mirror
 

ST Star Tracker
 

STC Star Tracker Camera
 

z z DFVLR RNTGENSATELLIT Status: 

PT-WF2 30.06.85 

43 
STE Star Tracker Electronics 

STM Structural Thermal Model 

STS Space Transportation System 

SURS Shuttle Umbilical Retraction System 

TA Technische Anweisung 

TC Telecommand 

T/C Thermal Control 

TCE Thermal Conditioning Equipment 

TCS Telecommunication Subsystem 

TM Telemetry 

TR Tape Recorder 

TT & C Telemetry, Tracking and Command 

TV Thermal-Vakuum 

TX Transmitter 

US Subsystem 

VPHD Vertical Payload Handling Device 

VPF Vertical Processing Facility 

WDE Wheel Drive Electronics 

WFC Wide Field Camera 

TFCC WNC-Consortium 

WSA Weltraumsimulationsanlage 

XRT X-Ray Telescope 

ZERODUR (Handelsname f~r den Glas-Keramik-Werkstoff 

des Spiegels) 

ZDE Central Data Electronics 

DFVLR Status:
 RdNTGENSATELLIT 

30.06.85
 PT-WF2 


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