NASA TECHNICAL MEMORANDUM NASA^TM-88481

/»- ,

X-RAY SATELLITE (ROSAT)

STATUS REPORT, 4TH QUARTER 1985

Deutsche Forschungs- und Versuchsanstalt

fuer Luft- und Raumfahrt DFVLR (German

Aerospace Research Establishment)

Translation of: "Roentgensatellit Statusbericht; 4. Quartal

1985", DFVLRi. Report -Nor RF^TN- 4, Porz^Wahn West Germany,

December 31, '1985, -pp. 1-68

fNASA-TM-88481 ) X-Rft X SATELLITE (EOSftT) M86-29889

Status -fieport, 1965 (National aeronautics

| and Space Administration) 54 p CSCL 22B

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

WASHINGTON, D. C. 20546 APRIL 1986
ORIGINAL

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X-RAY SATELLITE (ROSATJ. , STATUS REPORT,

• 4TH QUARTER 1985

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Deutsche Forschungs- und Versuchsanstalt fuer

Luf t- und Raumfahrt DFVLR (German Aerospace

Research Establishment)

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SCITRAN

Box 5456

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National Aeronautic* and Spaca Adisinistratlon

Waanington, D.C. 20546

Translation of: "Roentgensatellit Statusbericht;

DFVLR Report No. RF-TN 4, Porz-Wahn West Germany,

pp. 1-68

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4. Quartal 1985",

Decer±>er 31, 1985,

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An overview of the current status of the ROSAT X-Ray satellite project

is given. Areas discussed include an overview of problem areas,

systems and mechanical subsystems, the electrical subsystem, power supply,

data processing and transmission, the wide field camera, ground support

equipment, and the production scheduling. It is shown that the project

is proceeding according to schedule > including the hardware, production

and costs. However, it is stated that estimated additional costs will

exceed the plan. The previous schedule for production of the flight

model will no longer be met. A modified milestone plan has been

worked out with Dornier Systems . The current working schedule calls

for a launch date of December 21, 1987 j however, this does not take into

account a 4-week buffer prior to transporting the flight model to

the launch site. As of the date of this report, milestone M5 has been met.

Previous problems with the gold vapor deposition on the flight model mirror

due to contamination have been eliminated.

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GODD-102

DFVLR ROentgen SATellit (ROSAT) RF-TN4

Title:

Date:

Status Report; 4th quarter 1985

31 December 1985

Doc. No. TN4/0050

/s/,

Compiler

/s/ ,

Project Manager

/s/..,

Approved by

(Distribution list is self-explanatory)

-1-
Contents;

1.0 Summary and Prospects

1.1 Status of Tasks

1.2 Prospects

1.3 Overview of Problems

2.0 System

3.0 Mechanical Subsystem

3.1 Structure/ Mechanisms

3.2 Thermal Budget

4.0 Electrical Subsystem

4.1 Power Supply

4.2 Pyrotechnics

4.3 Harness

4.4 Data Processing

4.5 Data Transmission

4.6 Attitude Measurement/Attitude Control

5.0 Payload

5.1 X-ray Telescope

5.2 Wide Field Camera

6.0 Assembly, Integration and Test

7.0 Ground Support Equipment

7.1 Electrical GSE

7.2 Mechanical GSR

7.3 Optical GSE

8.0 ciission Safety

-2-
9.0 Vehicle Interface

10.0 Mission Operations

11.0 Schedule

12.0 Administrative Report (Special Distribution)

13.0 Annexes

13.1 Personnel Employment

13.2 Table of Abbreviations

-3-
WI%1 /2/

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1.0 Overview and Prospects

1.1 Status of Tasks

Summary

With respect to the engineering job, the project is

following the intended plan. The ROSAT total costs,

including Supplementary Contract No. 5 (in process) and

proposals for changes in the master contract received to

date, are also within the specif iedp_lan; however the runout

cost estimate (EAC 3) shows that the estimated additional

costs in the master contract will exceed the envelope of the

specified plan. The previous schedule for the production of

the flight model can no longer be met. There has been an

agreement with DS for a binding schedule plan with a

modified milestone plan at the end of February 1986 upon

conclusion of the solar simulation tests on the STM. In the

meantime a planning proposal from DS will be used as a basis

for work which shows a launch date of 21 December 1987, not

taking into account a four-week buffer prior to transporting

of the flight unit to the launch site.

Documentation

Project Plan:

Due to some reservations about the data processing concept

during the mission, the project plan has not yet been

submitted to DFVLR management.

— 4 —
Test and Integration EM/QM/STM Phase

The execution of the STH system tests is in accordance v/ith

the previous planning status with some partially readjusted

operating sequences. The integrated system test (1ST) was

successfully concluded. The electrical ground support

equipment (EGSE) with associated software was accepted

simultaneous with the 1ST.

Test and Integration FM Phase

The delivery of the NASA-furnished flight hardware (RSGF,

SURS) has been finished.

Reviews

The status review was carried out in November at the prime

contractor.

Milestones

Milestone M5 was met on schedule. A design review at the

prime contractor, using the test result presented and the

analyses done, showed that all design specifications were

proven to be attained or attainable.

Problems

An adjustment is required for the cost plan envelope and the

FM-schedule to match the current status. Also GSOC personnel

planning must be adjusted to the current status.

-5-
1.2 Prospects

In the course of the next quarter a binding milestone plan

is to be determined with the prime contractor which accords

with the current schedule for the FM-Phase.

As part of the EM integration procedure, there will be

carried out with the STM the solar simulations tests, the

postponed EMC tests and, if needed, additional systems

functional tests. Following this the STM will be dismantled.

Irregularities in the gold vapor deposition on the flight

mirror have been successfully eliminated, to the extent that

they could be traced to contamination before or after the

gold vapor deposition; following this, further contamination

was determined during gold vapor deposition which must be

more precisely identified and eliminated by the responsible

offices.

-6-
1.3 Problem Overview

Area Problem Area

£

W

2

Q

W

W

oi-q

u

1. Management

2. Svstem

3. Mechanical

subsystem

4. Electrical

subsystem

at the moment no problems at prime

contractor

agreement pending with NASA on HRI

random test loads

failure of high vacuum in the HRI detector with ion pump connected require

explanation and correction

time delays in the delivery of the

FI-FM require explanation and determination of corrective measures

no problem at the moment

failure of furnace-stabilized quartz

in the data processing must be explained in order to guarantee that

on the FM satisfactory operational

assurance is present at this "single

point failure" site,

exceeding of temperature limits on

solar generator when payload bay is

open in the shuttle and with direct

solar radiation into it requires

remedy by changing shuttle orientation in the PIP.

X

X

-7-
1.3 Problem Overview

Area Problem Area

s

w

p

w

w

o

J

u

5. Telecope

6. Assembly

Integration

7. Ground support

equipment

8. Mission safety

9. Vehicle interface

10. Mission

operations

stray light specifications of the star

sensor in the AKS cannot be met in

present form and require discussion

assembly of the FM mirror system

interrupted due to irregularities in

the gold vapor deposition of paraboloids P3 and ?4

current unavailability of the IABG

test chamber for the solar simulation test at the planned time will

require expensive substitute

measures

no problems at the moment

no problems at the moment

no problems at the moment

mission operation and simulator development are suffering personnel

shortage

open action item on data processing

concept

-8-
Area Problem Area

11. Schedule - deadline postponements have been

reported for the data processing

and component procurement subsystems

- a postponement of milestone M7 can be

assumed based on problems with the

gold vapor deposition of the FM mirror

system. Further impacts on the FM

schedule must be clarified', t

15

w

"Z

:LOSE

D
System

System Verification

As a submission for the review of milestone M5, the prime

contractor produced an exhaustive document which shows in

detail in tabular form those documents (engineering notes,

analyses and test reports) in which it has been shown that

the current design is oriented on the specifications for

system and subsystems.

System Magnitudes

The magnitudes for attitude measurement accuracy produced

for the system verification mentioned above, which contained

the very positive test results on the EM star sensor, showed

that the required attitude measurement accuracy can be

achieved.

The other system magnitudes also exhibit satisfactory

clearances within, the specified limits.

EMC Activities

During EMC tests at the component level, specified values

were exceeded in a few cases. Now it was demonstrated during

system test (1ST) that these excesses do not lead to

problem at the system level and therefore can be accepted.

In preparation for the EMC tests for the spring of '86,

tasks were started f or • delivery of the required hardware

and for working up the system EMC test procedure.

3.0 Mechanical Subsystems /9/

3.1 Structure/Mechanism^

Evaluation of the. modal survey tests took place employing a mass

matrix corresponding to the current status of the satellite in

which a total mass of m = 2390 kg has been determined. The

comparison shows good agreement of the measured characteristic

frequencies and forms with those magnitudes derived analytically.

All major characteristic frequencies agree within a deviation

< 10%. The Modal Survey Test fully validated the Finite Element

-10-
Model (FEM).

As was determined before the test, this result makes possible

elimination of adjustment of the FEM.

The test report on the static load was finished and presented. In

addition reports on structural stability and fracture mechanics

were completed. The FM drawing package was completed. A start was

made on fabrication of the piece parts for refurbishment of the

structure. The FM solar generator was finished and sent to DM for

thermal treatment.

In'the case of the mechanisms, fabrication of the flight models

of ABM, TDM and SSM was continued according to plan. The assembly

of the Telescope Door Mechanism (TDM) was able to be almost

completely finished. Assembly instructions for the ABM and

verification control sheets were prepared.

No problems exist at the moment in the two subssystems.

3.2 Thermal Budget /10/

Tasks in the thermal budget subsystem were continued according to

plan. Preparations for solar simulation test included matching of

the reduced ROSAT thermal model to the test chamber conditions at

IABG-WSA and the fabrication and integration of thermal and test

hardware. It was possible to complete all necessary tasks in the

thermal sector in a timely manner before the test.

It was possible to overcome difficulties in procurement of white

paint for thermal treatment of the FM solar generators by the use

of a similar paint from another manufacturer. Meanwhile, it was

possible to deliver the solar generators to AEG for installation

of the solar cells.

-11-
/ll/

4.0 Electrical Subsystems

4.1 and 4.2 Energy Supply, Pyrotechnics

The 1ST for the energy supply system and the pyrotechnics was

carried out successfully on 6 December 1985 with participation by

the project management team. All electrical specifications were

able to be verified.

As part of the Milestone 5 (M5) Review held 10-12 December 1985

at DS, DS, using the verification document presented,

TN-2002-2160 DS/019, along with other reference documents, was

able to demonstrate successfully that both subsystems meet the

specifications set. One of six deficiency notes produced deals

with a still outstanding re-qualification of the solar generator

with respect to the adhesive strength of the;- solar cells on a

solar cell structure fabricated by MBB using the roller

technique. This qualification test has been under preparation at

AEG beginning in December 1985 and will be completed in February

1986.

With respect to status of the tasks and problems, it can be

reported that

the fabrication of the FM electronic boxes is on schedule

despite some delay due to lack of HiRel parts

no engineering problems have emerged in the fabrication of

the FM electronic boxes

fabrication of the FM solar generator has begun

mechanical and electrical fabrication of the /12/

FM electronic boxes has been continued during some time

delay in electrical fabrication due to lack of HiRel parts

mechanical fabrication of the FM battery housing has started

all specifications of the subsystems have been reworked and

reflect the latest design status taking into account all

EC's set.

-12-
4.3 Cable Harness /13/

The project management also waived a status review on this

subsystem in this reporting period based on the M5 milestone

review.

From the monthly status reports from DS it can be determined that

fabrication of the FM signal harness was continued

fabrication of the FM power/pyro harness has been

finished up to the "hot line" connector

fabrication is completed on the FM telescope harness

appropriate preparations have been made for testing of

the harnesses

the mass computations have been done for the complete FM

cable harness

the FM computer harness list has been reworked.

As part of the Milestone 5 (M5) review DS has demonstrated, in

varification document TN-2002-2160 DS/019, along with other

reference documents, that the harness meets all the

specifications set for it.

With respect to schedule and problems, it can be reported .that

fabrication of the FM harness is on schedule

no engineering problems have arisen in fabrication /14/

of the FM cable harness and in the incorporation of required

modifications on the FM cable harness.

4.4 Pata Processing

After successful completion of the RF compatability tests at JSC

the DPS was modified in conformity v/ith some AE' s and MRB's, and

was then available according to plan for the remaining

integration work, the pre-IST and finally the 1ST. During these

activities also some defects were noted which were provisionally

taken care of in the EM so that it was possible finally to finish

the EM-IST.

-13-
However, to some extent these defects mean still larger

modifications. For example, a header check of the incoming data

frames is essential for the real-time handler in the DPS to

prevent malfunctions of the DPS.

FM fabrication and installation of circuit boards is suffering

from piece part delivery problems (especially ceramic condensers

and RCA-SOS-RAM's), such that the previously planned FM delivery

date (end of April 1986} can not be met. It has even been

necessary, even in the FM to install as the first boards those

with radiation sensitive Harries parts instead of the radiation

hardened SOS-RAM1 sj-, this in order to get on with the program at

all.

Both FM tape recorders have been successfully accepted at DS.

4.5 Data Transmission /15/

Tests on the data transmission system as part of the "Integrated

System Test" showed that the integrated system meets the

established specifications. Some confusion in the setting and

definition of the modulation indices for both data channels which

already cropped up during NASA interface tests remains to be

cleared up.

Transponder

The ADP's were worked over, refined and presented at the M5

milestone review. A transponder was returned to the

manufacturer at year's end to investigate instabilities in

the modulation input which came out during the NASA

interface tests. The reworking of both transponders and the

necessary follow-up qualifications', were agreed to'both as

to content and schedule.

Decoder

The EH integrated in the satellites (EM/STM) operated

without problems.

-14-
The fabrication of the flight model has been slightly

delayed by problems in the procurement of condensers for

ROSAT.

Antennas

The EM worked perfectly. The fabrication of the flight model

was continued.

4.6 Attitude Measurement/Attitude Control /16/

Star Sensor

The star sensor EM was subjected to a series of further tests:

vibration, functional, performance tests. Evaluation of these

tests has started.

The thermal budget of the star sensors was checked out for the

worst case (orbit with the greatest heat radiation). The result

shows a small rotation of the radiators is necessary. A precise

analysis was carried out on the orientation of the radiators.

The measurement accuracy for the AKS stars was able to be

considerably improved by the production of a supplementary

correcting polynomial.

Reaction Wheels

Fabrication of the mechanical parts of the reaction wheels is

almost complete. The circuit boards for the WDE are finished and

approved.

AMCE

The AMC simulator for the static and dynamic subsystem tests is

finished.

Parts /17/

Despite the, in part, considerable delays in the delivery of some

parts, it can be predicted that the individual components of the

AMCS (up to the AMCD) can be delivered on schedule. One

uncertainty here are the condensers. The AMCD delivery depends on

the RCA parts delivery.

-15-
Softv/are

The development of further portions of the software (pointing

mode) was able to be finished and underwent the first tests. The

fabrication of the scan mode software is still pending.

-16-
5.0 Payload /18/

5.1 X-Ray Telescope

5.1.1 Telescope QM and FM

The telescope QM is being employed as part of the system AIT

tasks.

Manufacture of components for the flight model of the telescope

will be finished on time in spite of the late start in the

fabrication, so that the schedule for FM telescope assembly will

not be endangered.

5.1.2 Mirror System

The problem of the spots in the gold vapor deposition on the

flight mirrors P3F and P4F has been solved. Improvements

introduced in cleaning and spot-checking of mirrors before the

vapor deposition have been tested for their effectiveness: the

gold coating of P4F was washed off, the mirror cleaned and

re-vapored. The gold coating is without any visible deficiencies.

With this, the improvement actions at the firm of C. Zeiss and

Balzer to insure a zero defect preparation of the gold vapor

deposition have been successfully verified.

The structural and engineering modifications in the cleanroom at

C. Zeiss in which the flight mirror system is to be assembled and

which were reported on in the previous reporting period, have

been carried out; this is in order that in the future any

hydrocarbon contamination of the mirrors is ruled out.

Despite the great extent of the work needed, it was /19/

finished in November 85 on schedule.

It is necessary to verify cleanliness before starting the

-17-
assembly of the flight mirror system. For this purpose there is

employed a test program in which small gold-coated test mirrors

are set out in the clean room and checked on a recurrent

schedule. The first test with such test mirrors with the "SIMS"

method yielded an unexpected result: Mirrors which had been gold

coated in the same plant as the flight mirrors appeared to have

incorporated hydrocarbons in the gold layer. This finding was

confirmed with X-ray tests in the PANTER facility. The cause

could be that, during the vapor deposition process, hydrocarbons

from residual gas in the plant were picked up and embedded in the

gold layer.

It can be assumed that this will also apply to the newly-coated

P4p flight mirror. It is to be feared that without measurements

to improve the gold vapor process itself, e.g. by suitable

modification of the vacuum system at the vapor deposition

facility, similar effects will apply to the gold vapor coatimg of

further flight mirrors. At the moment checks are being made with

the firm of C. Zeiss and Balzer as to what measures must be

taken.

Since the introduction of these measures and the verification of

their effectiveness will involve considerable expenditure of

time, a new postponement of the start of assembly of the flight

mirror system can be reckoned on.

The status of work on the contract at C. Zeiss for manufacture of

the individual mirrors of the flight model which is separate from

that of the overall system is as follows:

/20/

All tasks have been successfully |completed with the exception of

the cutting to size of•the not-yet-delivered flight mirror.

Cutting to size and delivery have been deferred in order to be

able to install the mirrors more securely in the supporting

-18-
structure.

5.1.3 Focal Plane Instrumentation

Tests of the FI as part of the system tests (1ST) proceeded

successfully.

The first assembly tasks of the FI flight model started during

the reporting period.

Open problems were pursued further:

HRI random vibration loads:

New random loads for the HRI were derived by GSFC during the

reporting period based on coupled analysis and using the

data available from the telescope and FI vibration tests.

These loads are significantly less than the previous system

permissible levels, but they are higher than the magnitudes

previously proposed by GSFC. It was agreed to test the HRI

with the new loads. Before the random test, a sinus test

should determine whether accelerations exceeding 27g occur

on structural parts of the HRI; this is the loading during

the HRI centrifuge tests. In this case, suitable notching

must be planned.

With this a decisive step will have been taken nearer to the

solution of the problem.

Slippages in the FI-FM: /21/

MPE estimates the schedule delay for the delivery of the

FI-FM at 6 months. It is planned to take the delay into

account in reworking the schedule for the flight model of

the satellite. Due to the problems with the mirror' system

and the associated required adjustments to the FM-AIT it can

be expected that the FI-FM will be ready in a timely manner.

-19-
Vacuum Loss on the HRI-EM

After attachment of the HRI-EM to the structure and

transport to MPE, the vacuum was restored by evacuation with

supplementary pumps. A leak was not determined in the

HRI-EM. A male plug connector in the electrical power supply

cable for the HRI ion-getter pump was identified as the most

probable cause of the collapse of the vacuum. The cable has

been replaced.

A new vacuum loss in the HRI-EM was discovered on 16

December 1985. It is supposed that the cause is defects in

the buffer battery of the ion-getter pump power supply since

the vacuum loss occurred after a (planned) shutdown of the

house power.

Subsequent determination of the failure cause and its

correction are pending. It is planned together with GSFC to

introduce improvement in the reliability of the power

supply.

/22/

5.2 Wide Field Camera (WFC)

Activities during the reporting period:

o 1ST successfully finished

o routine interface meeting at DS, as part of the status

meetings, 13-15 November

o information exchange re: possible EVA's

o preparations for the solar simulation test

Prospects:

Agreement on modified readiness dates (FM) with DS based on

the new AIT planning

-20-
/23/

6.0 Assembly, Integration and Test

Integrated System Test of the EM

The outstanding occurrence in the reporting period was the

carrying-out of the Integrated System Tests (1ST).

Electrical satellite and EGSE equipment functions were

successfully verified.

The focal plane instrumentation (FI) of the telescope and the

wide field camera was operated by the experimenters through the

S/C EGSE using their own programs based on mission-similar

conditions, and was successfully tested in all planned functions.

The S/C EGSE and checkout software met the specifications for

function and compatibility with the overall system.

The data attained in the 1ST v;ill also serve as reference data in

subsequent testing.

1ST Follow-on Test

For the first star sensor, delivered during the 1ST, the test was

carried out afterwards. A test will be repeated in May for the

AMCS software, up until now incomplete.

Integration .and Test of the EH

The tasks of integration, alignment and optical measurements on

the WFC, the FI, the AMCS sensors such as magnetic coils,

/24/

wheels, star sensors, on the antenna booms and magnetometers were

-21-
all able to be handled according to plan.

Integration tasks had to be interrupted for four days on account

of the delayed delivery of the AMCS. During the electrical

integration, I/F problems arose between the AMCS computer and the

S/C EGSE.

Considerable problems arose in the pre-IST of the FI on account

of I/F errors in the S/C data processing (DHS). The errors were

explained and eliminated, through joint efforts of DS, S/C

operators and the experimenters from MPE.

In order to make up for the time delays that arose, shift work

was employed beginning in mid-November and thermal hardware was

adjusted and integrated in parallel with this.

All problems were disposed of before the 1ST began, and no

failure reports are pending which would call into question the

success of the 1ST.

Prospects

Solar simulation testing of the EM at IABG, 7 January to 5 March

1986.

/25/

7.0 Ground Support Equipment

7.1 Electrical Ground Support Equipment

A reworking of the test sequences was undertaken for the pre-IST

and the integrated system test (1ST). The electrical integration

of the AMCS was supported. The monitor table was updated.

The new version of the ETOL software was implemented by ESOC in

the EGSE computer and the errors that occurred were corrected.

The EGSE specification was revised.

Hard and software problems which occurred on the IEEE bus, the

-22-
S/C EGSE and the AMCS-EGSE were eliminated. The acceptance of the

EGSE and the checkout software took place simultaneously with the

1ST. Service programs were prepared for support of the AIT. The

latest version of the send/receive tasks from the S/C EGSE was

made available to GSOC. Still to be investigated are the effects

on the data compatibility test (Gateway/DEC net) of the delayed

delivery of the Micro VAX II to GSOC.

The analog device delivered by MPE is defective.

It has been turned over to the supplier for repair.

/26/

7.2 Mechanical Ground Support Equipment

Most of the tasks in the MGSE subsystem have been completed. The

test adapter for the IABG-WSA was completed and delivered.

After production of the manuals and test protocols and the work

on failure reports, no more activities will take place.

7.3 Optical Ground Support Equipment

No activities.

*

manufacturer's name for the computer employed

-23-
/27/

8.0 Mission Safety

o STS Safety

The "Safety II Review" for the overall ROSAT system was

carried out at NASA-JSC and HASA-KSC on the basis of the

GSFC-approved data packet for STS flight and ground

operations which was accepted by NASA JSC/KSC for review.

The results are essentially as follows:

oo Flight Operations:

- a number of hazard reports submitted in Phase II

(seven for the ROSAT system, four for the S/C, four for

the FI, and five for the WFC) were approved.

oo Ground Operations:

- Of the eight (3) hazard reports submitted to the

"Review Team" from NASA KSC for Phase Iir six were

approved and two were not approved. These must be

resubmitted in revised form.

Reliability

Meantime a number of FMECA's and SPF lists for the system

and subsystems have been delivered by DS. The project

management has started with an anaylsis/checking of the

FHECA's.

/28/

Quality Assurance

oo During the reporting period, the project management

checked and evaluated altogether 24 further failure

reports/HRB's of Level 2 on the EH and FM components of

the satellite system.

-24-
oo There was a total of three inspections following final

checks of double-sided circuit boards at the firms

Teldix and MB3

Central Parts Procurement

oo Passive Parts

- All Li's to and including all ceramic (condensers of

the Jahre firm which, on account of cracks in the

ceramic bodies, had to be ordered again from other

manufacturers either from stock (LCC Co.) or new

production (Union Carbide), have been distributed to

the users.

The delivery of all replacement and/or newly ordered

ceramic condensers will be finished in the fifth

calendar week of 86.

oo Active Parts

- All diodes and all transistors through Type MAT 01

have been distributed.

- For those IC's which can no longer be delivered in

1985 due to delivery problems of the manufacturer,

cancellation or modification of test times in

"upgrading" and to lack of timely replacement

procurement, there will be some considerable delivery

postponements in 1986.

9.0 Vehicle Interface /29/

o ICD-A-18410

As part of the NASA interface discussions at NASA JSC on 1

October 1985, the "preliminary version" of the ICD produced

by NASA and reviewed by DS was a subject for discussion.

As a result of these discussions a "baseline version" signed

by NASA JSC and the project managements at GSFC and DFVLR

was adopted.

-25-
The second part of the "Design Review" (DR) of the ROSAT/OIB

was carried out on 3 October 1985.

PIP Annexes

PIP Annex 5;

PIP Annex 4: Based on the agreement reached NASA, JSC

produced a preliminary version which has been

commented on by the project management in a

so called "red marked copy".

This annex was finally discussed with NASA on

3 October 1985 and meanwhile the project

management has a "preliminary version" for

a

comment.

The "Launch Site Support Plan" (LSSP) and the

associated PRO were discussed as part of the

NASA interface discussions at NASA KSC. The

results of this discussion were incorporated

by NASA KSC into the document.

/30/

Suitcase Test at NASA JSC

PIP Annex 8:

At NASA JSC the appropriate compatibilities of the ROSAT

RF-system ("Van" Test) were carried out with the NASA ground

stations using the test vehicle ("van") furnished by NASA GSFC.

The "down-link" test was successful, the "up-link" test, however,

could not any longer be continued due to technical problems with

the "van". The compatibility tests will be repeated as part of

launch preparations.

/31/

10.0 Mission Operations

10.1 Progress of Work

The important milestone in the reporting period just past was the

successful carrying-out of the "Mission Operations Requirements

Review" on 5 December 1985. But here it became clear that the

-26-
buildup of the ROSAT ground segment has been in part seriously

hindered in some areas by the non-availability of information.

Coordination

Several requirements for the mission operations system are not

covered in the present budget planning and this must be handled

Additional costs are to be expected. Steps were introduced for

improved coordination of GSOC activities and the course of the

work at DS. The manpov;er shortage at GSOC was not able to be

eliminated at the end of 1985 and this is to be taken into

account in following years with respect to planning.

Flight Operations

The Mission Operations Requirements Review was carried out on the

basis of the first "preliminary" Experiment Operations

Requirements Document (EORD) of 4 November 1985, of the

GSOC-ROSAT Project Requirments Document (PRO) and the pertinent

satellite specifications. In this connection, "Mission Operations

Meetings" (MOID have been set up with DS in order to be able on a

regular basis to discuss open questions concerning the

satellite/ground interfaces. The "Mission Operations Support

/32/

Plan" could not be started. Participation took place in the "WFC

Preliminary Design Review".

-27-
Ground Operations

The ROSAT-PRD was completed in preliminary form and is being

submitted to an approval process at the moment at GSOC.

The draft of the SIRD submitted by NASA takes into account the

support functions desired by the project.

For a test of the receiving readiness at the 15m ground station

at Weilheim for 1 MBPS telemetry, the IRAS satellite v/as

activated by RAL, Chilton, UK and made available to GSOC.

Mission Planning and Analysis

The main activities centered around preparation of detailed

specifications as a basis for the software design of the attitude

measaurement/control software. The main program of the attitude

determination software has been developed. The definition of the

requirements in the area of mission planning was further

deepened.

An analysis of the satellite antenna aspect angle behaviour

showed that no significant reduction in data reception is to be

expected as a result of antenna pattern breakins.

Data System

The ground station software was modified for the processing of

data rates up to 250 kbps for manipulation of the 1 MBPS

telemetry data registered in the analog band.

Intersection point adjustments of the command software were

defined for the acceptance of external command files. A start

/33/

was made on working up a concept for command verification (from

telemetry).

The software specification was prepared for the GSOC/ROSAT data

-28-
system interface tests (DS/IABG-GSOC boundary).

The testing of the concept for the development of DV requirements

for ROSAT and other projects in future years presented by WT-DV

led to a modification of ROSAT specifications which should result

in a cost reduction in the WT-DV concept.

AMCS Simulator

A first version of the "Dynamic Sensor and Actuator" software was

delivered by RAL and tested. Essentially the tasks are proceeding

according to plan. To bridge over the lack of the AMCD and

simulator interface hardware, first expected in February 1986, an

unplanned software simulation package had to be developed in

order not to impede the integration and test work. Accordingly,

the development of the simulator system software was lagging

behind the schedule.

Test and Training

No activities.

Software

After first analyses of the requirements in the EORD, the

definition began of the intersection points in the attitude,

orbit, commnand and mission planning data sets. A description was

prepared of the telemetry-data basis system. A preliminary design

was presented of the "Special Master Data Record" (SMDR).

-29-
/34/

10.2 Problems

The acceptance of the telemetry and command data basis of the

satellite EGSE (ETOL) into the GSOC data system requires

clarification since it represents a prerequisite for the

configuration of the GSOC ROSAT telemetry/command software.

Confusion about the previous definition of requirements and lack

of information led at GSOC to 1985 activities being put over

until 86, which still can be handled from a personnel standpoint.

Important delays in some areas arose in the development of

attitude determination/attitude control software on account of

some delays in delivery of documents and specifications and

software to be made available by project management. The delayed

delivery of the AMCD simulator hardware and the associated

interface system is leading to delays in the development of the

AMCS simulator.

10.3 Personnel Status

See Annex 13.1

10.4 Schedule

Postponements in the GSOC schedule cannot be avoided due to the

problems named in the above report. Changes from the last

schedule dated 18 June 85 are indicated with marginal notes. On

account of the holdover of activities into 1986/87, the influence

on operational readiness at launch date still remains

insignificant. However, this can only be guaranteed if the

existing manpower deficit is removed and is appropriately taken

into account in the future in planning estimates.

-30-
11.0 Schedule /35/

Nominal Specified

The noninals layed out in the contract milestone plan with a

launch date of 30 October 1987 no longer agree with the

actual status. The same applies for the NASA schedule in t.he

PIP with the launch date (reference milestone "ready for

launch") at 30 September 87.

EM Actual Status

The currently valid DS schedule for STM integration dated 6

November 85 shows, when compared with the previous plan of 7

Hay 85, the same termination point with closeout of the

structural updating on 7 July 1986. Only operating sequences

have been switched around. Milestone M5 was met according to

plan. Design Review 2 is scheduled for May 1986.

FM Actual Status

At the management discussion in November DS presented a

planning proposal, status 12 November 1985, which currently

is serving as a basis for the work. In this planning

proposal, the four-week buffer before transporting the

flight unit to the launch site is no longer included. Taking

into account the delayed readiness of the flight mirror

system caused by contamination problems in the gold vapor

deposition, and delays in parts procurement, the following

slips appear in the milestones:

M7, readiness of flight mirror system: 4 months

M8, FM ready for environmental tests : 4 months

M9, preshipment review : 3 months

M10, launch : 2 months

-31-
/36/

Binding schedule planning with a modif.ied'milestone plan has

been agreed with DS to take place at the end of February

1986 after the close of the solar simulation tests.

With restoration of the four week buffer, this binding

milestone plan shows a launch date in the first quarter of

1988.

-32-
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TERMS FOR PAGE 38

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17. MIO launch

-36-
/39/40/41/

PAGES 39, 40 AND 41 ARE IN ENGLISH

PAGES 41-57 WERE LIMITED DISTRIBUTION- NOT IN THIS PACKAGE

-37-
/57/

JL3.0 Annexes

13.1 Personnel Employment at DFVLR-RF-TN and DFVLR-RF-Rti

-38-
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-41-
TERMS FOR PAGE 59

1. Personnel Employment

2. Cost citation

3. Time Period

4. nominal

5. actual

6. Total

7. Out-of-house work:

Budgeted 1985

7A. Man years

8. Expended through 31 Dec 85

9. Produced in work:

nominal--planned

actual contracted

-42-
TERM

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i
TERMS FOR PAGE 60

1. Personnel Employment

2. Cost citation

3. Time Period

4. nominal

5. actual

6. Total

7. Out-of-house work;

Budgeted 1985

7A. Man years

8. After spending deferral to 1986, for 1985 there remains

(numbers)...per spending authority document, BMFT, 2 Dec 85

9. Expended through 31 Dec 85

10. Produced in work:

nominal--planned

actual contracted

11. 1) reduction in nominal associated with spending deferral

2) increase in actual on account of tasks done over again

in period 1-9/85

-44-
13.2 Table of Abbreviations

/61/

ABM

ADP

XA

AKS

AIT

AMCD

AMCE

AMCS

Antenna Boom Mechanism

Acceptance Data Package

Change Proposal

Pointing Controls-System

Assembly, Integration and Test

Attitude Measurement and Control Data Unit

Attitude Measurement and Control Interface

Electronics

Attitude Measurement and Control Subsystem

BAT

ECU

Bit. Sync.

BMFT

CCD

CCL

C&DH

CEL

CFK

CFRP

CITE

Cmd

CMOS

C/0

CPP

CPU

CSA

CSS

CZ

25^7-DFVLR

r RF-TN4

Battery

Battery Control Unit

Bit Synchronizer (Synchronization)

Bundesminister fUr Forschung und Technologie

(Federal Minister for Research and Technology)

Charge Coupled Device

Charge Current Limiter

Command and Data Handling

Control Electronics

( Carbon Fiber Reinf orce_d Plastic

Carbon Fiber Reinforced Plastics

Cargo Integration Test Equipment

Command

Complementary Metaloxyde Silicon

Checkout

Central Parts Procurement

Central Processing Unit

Charge Solar Array

Coarse Sun Sensor

Firma Carl Zeiss

RtfNTGENSATELLIT ' Status:

31 .12.85

-45-
762/"

DC

DEC

DFVLR

DFVLR-PL

DBS

DMA

DMOD

DNEL

DPS

DR

DS

DV

EAC

ECR

ECS

BED

EEL

EGSE

EM

EMC

EOL

EORD

EPD

ESA

ETOL

EUV

EVA

Direct Current

Decoder

German Research and Test Establishment f or. ..

Aeronautics and Space Flight

DFVLR-;Project Management

Data Handling Subsystem

Direct Memory Access (Direct Assess to Memory)

Demodulator

Disconnection of Non-Essential Loads

Data Processing System

Design Review

Dornier System

jData Processing

Estimate At Completion

Engineering Change Request

Environmental Control System

Electro-Explosive Device

Experiment-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

Extravehicular Activity

FEM Finite Element Model

FI Focal Plane Instrumentation

A

s rJ j HPVI P

V RF-TN4

RBNTGENSATELLIT

Status :

31 .12.85

'-46-
/63/

FLS

FM

FMECA

FWHM

GF

GSE

GSFC

GSOC

GVS

GYP

GYPE

GYPS

HC

HEAD-2

HIREL

HK

HP

HRI

IABG

1C

ICD

IEEE

INVAR

1ST

JSC

kbps

Fiducial Light System

Flight Model

Failure Mode Criticallity Analysis

Full Width at Half Maximum

Grapple Fixture

Ground Support Equipment

Goddard Space Flight Center

German Space Operations Center

Gas Supply System

Gyropackage

Gyropackage Electronics

Gyropackage Sensor

Heater Control

High Energy Astronomy Observatory ("Einstein")

High Reliability

Housekeeping

High Power

High Resolution Imager

Industrial. Facilities Operating Co.

Integrated 'Circuit

Interface Control Document

Institute of Electrical and Electronics

Engineers

(trade name for a particular steel alloy)

Integrated System Test

Johnson Space Center

Kilobit per second (deutsch: kbit/s)

/T^rZDFVLR

Y RF-TN4

R6NTGENSATELLIT

Status :

31 .12.85 .

-47-
/64/

KSC

KW

LCL

LEO

LHC

LI

LP

MA

MAC

Mbps

MC

MCC

MCP

MDM

MED

MES

MGSE

MIP

ML I

MM

MM

MOM

MOU

MPE

MPG

MPSS

MRS

MSA

MSSL

Kennedy Space Center

Calendar Week

Latching Current Limiter ••

Light Emitting Diode

Left-hand Circulation

Line Item

Low Power \

Mirror Assembly

Mirror Attachment Cone

Megabit per second (deutsch: Megabit/s)

Magnetic Coil

Mission Control Center

MicroChannel Plate

Multiplexer/Demultiplexer

Magnetic Electron Deflector

Mechanisms Subsystem

Mechanical Ground Support Equipment

Mandatory Inspection Point

Multilayer Insulation

Magnetometer

Mass Model

Mission Operating Meeting

Memorandum of Understanding

Max-Planck-Institut ftlr Physik und Astrophysik,

Institut ftir Extraterrestrische Physik

Max-Planck-Gesellschaft

Mission Planning and Scheduling System

Material Review Board

Main Solar Array

Mullard Space Science Laboratory

^2Z7DFVLR

V RF-TN4

RBNTGENSATELLIT

Status :

31 .12.85

-48-
/65/

MUC

MUDAS

MVL

Multi-Use Container

Modular Universal Data Acquisition and

Control System

Main Voltage Limiter

NASA

NCR

NRZ/L-Code

NSI

National Aeronautics and Space Administration

Non Conformance Report

Non-Return-to-Zero/L-Code

NASA Standard Initiator

OBC

OGSE

OIB

OSR

Onboard Computer

Optical Ground Support Equipment

Orbiter Interface Box

Optical Surface Reflector

PCB

PCU

PDU

PETS

PGHM

PHP

PIP

POCC

PPF

PRO

PRO

PSE

PSK

PSPC

PSS

PYB

Printed Circuit Board

Power Control Unit

Power Distribution Unit

Payload Environmental Transportation System

Payload Ground Handling Mechanism

Paraboloid-Hyperboloid Pair

Payload Integration Plan

Payload Operations Control Center

Payload Processing Facility

Program Requirements Document

Project Requirements Document

Payload Support Equipment

Phase-shift Keying

Position Sensitive Proportional Counter

Power Supply Subsystem

Pyrotechnics Electronic Box

DFVLR

RF-TN4

R&NTGENSATELLIT

Status:

31 .12.85

-49-
/66/

QM Qualification Model

RAL

RAM

RCA

RE

RF

RfW

RMC

RMS

ROSAT

RS

RSGF

RSS

RT

RW

RX

S/C

SCOE

SERC

SEU

SIRD

S/L

SMDR

SOC

SOS

SPF

SPL Code

SSM

SSM

ST

ZjdjZDFVLR

V RF-TN4

Rutherford Appleton Laboratory

Random Access Memory ' •

Radio Corperation of America

Radiated Emission

Radio Frequency

Request for Waiver

\

Right-hand Circulation

Remote Manipulator System

Rontgensatellit

Radiated Susceptibility

Rigidized Sensing Grapple Fixture

Rotating Service Structure

Real Time

Reaction Wheel

Receiver

Spacecraft

Special Checkout Equipment

Science & Engineering Research Council

Single Event Upset

Support Interface Requirements Document

Serial Load

Special Master Data Record

Science Operations Center

Silicon on Sapphire

Single Point Failure

Split Phase Level Code

Single Surface Mirror

Separation Switch Mechanism

Star Tracker

RONTGENSATELLIT Status:

31 .12.85

-50-
/67/

STC

STE

STM

STS

SURS

S/W

Star Tracker.Camera

Star Tracker Electronics

Structural Thermal Model

Space Transportation System

Shuttle Umbilical Retraction System

Software :

TA

TC

T/C

TCE

TCS

TDM

TM

TR

TT & C

TV

TX

Telecommand

Thermal Control

Thermal Conditioning Equipment

Telecommunication Subsystem

Telescope Door Mechanism

Telemetry

Tape Recorder

Telemetry, Tracking and Command

Thermal-Vakuum

Transmitter

UK

US

VPHD

VPF

United Kingdom

Subsystem

Vertical Payload Handling Device

Vertical Processing Facility

WDE

WFC

WFCC

WSA

Wheel Drive Electronics

Wide Field Camera

WFC-Consortium

XRT X-Ray Telescope

DFVLR

RF-TN4

R0NTGENSATELLIT

-51-

Status:

31 .12.85
/68/

C

ZERODUR

ZDE

'(trade name for the glass/ceramic material

' of the mirror^

Central Data Electronics

DFVLR

RF-TN4

R8NTGENSATELLIT

-52-

Status:

31 .12.85