NASA TECHNICAL MEMORNADUM fa or*- <4 NASA TM-77997

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X-RAY SATELLITE STATUS REPORT-THIRD QUARTER 1985

Deutsche Forschungs- und Versuchsanstalt £uer

Luft- und Raumfahrt (DFVLR)

(NASA-TH-77997) X-EAY SATELLITE Status N86-17370

Report, third guarter 1985 (National

Aeronautics and Space Administration) 49 p

HC A03/HF A01 CSCL 22B $3 Dnclas

05325

Translation of "Roentgen Satellit Statusbericht; 3.

Quartal 1985", Deutsche Forschungs- und Versuchsanstalt

fuer Luft- und Raumfahrt - DFVLR (German Aerospace

Research Establishment) , Cologne West Germany,

Report no. WF2/9143, September 30, 1985, pp. 1-72

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

WASHINGTON, D.C. 20546 NOVEMBER 1985
/.IVDARD 1 IT L E PAG E

NASA"TM-77997

X-RAY"SATELLITE STATUS REPORT - THIRD

QUARTER 1985

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Research Establishment)

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National Aeronautics and Space Administration

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Pun,.ni.rrK.i.. Translatlon of "Roentgen Satellit Statusbericht; 3. Quartal

1985", Deutsche Forschungs- und Versuchsanstalt fuer Lnft- und-Raumfahrt

DFVLR (German Aerospace Research Establishment), Cologne West Germany,

Report No. WE2/9143, September 30, 1985, pp. 1-72

U. Abn.oci The 3rd Quarter status Report on DFVLR's ROSAT project confirms that

with regard to technical performance and costs the project is on schedule. The

valid schedule for engineering model and flight mbdel completion on May 7, 1985

leads to a launch date on October 30-, 1987. Progress in each department is

compared to and explained with regard to the milestone plan. Continued problems

with the gold damping of the FM-mirror system and contamination of the sterile

rooms where the mirrors are stored have led to-postponement of milestone 7. -It

is not yet completely clear to what extent all successive milestones will be

affected by this factor.

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49

72- P«ic
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 -Wiring

4.4 Data Processing

4.5 Data Transmission

4. 6 Attitude measurement and control

5.0 Payload

5.1 X-Ray Telescope

5.2 Wide Field Camera

6.0 Assembly, Integration, and Test

7.0 Ground Equipment

7

 • * { Electric Ground Support Equipment (EGSE)

7-2

 | Mechanical Ground Support Equipment (MGSE)

7-3

 j| Optical Ground Support Equipment (OGSE)

i — - - _. - -

8. Mission Safety

9. Launch Vehicle Interface

-3-

FREQEDING PAGE BLANK NOT RLMED
10.0 Mission Operation

11.0 Schedule

12.0 Administrativ e Report (Special distribution)

13. 0 Appendix

13.1 Personnel Utilization

13.2 Key to Abbreviations

-4-
STATUS REPORT

1.0 Survey and Outlook /3*

1.1 Status of Projects

Summary

With regard to technical performance and costs, the project

is running according to plan. The valid schedule fqr EM- and

FM- completion on May 7, 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 aate of September 9, 1987, agreed upon in the

Payload Integration Plan.

Due to problems with the gold damping of the FM-mirror

system, we must reckon with a postponement of milestone M7. It

is not yet completely clear to what extent all successive

milestones will be affected by this factor.

Documentation

Project Plan:

The project plan has not yet been presented to the DFVLR

board Because of reservations regarding the data processing

design to be used during thermission.

Specification documents:

s,

Anothe r reworked version of the interface .specification for

^Numbers in margin indicate pagination in the foreign text.

-5-
the WFC--Issue 3, Revision A--dated June 6, 1985--was put into

effect.

Development and Production /4

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

Test and Integration

The FI-EM infeed for EM-integration is completed.

EM-integration corresponds to planning status of May 5, 1985.

The Modal Survey Test and Suitcase Test were completed at

NASA-JSC.

Review

The Phase 2 Safety Review for flight and ground operations

was completed successfully at NASA.

The tenth status review by the chief contractor was carried

out in September.

Milestones

Milestone M4 in which ROSAT is ready for Modal Survey Test

was reached on schedule.

Problems /5

The schedule cannot be changed. Should the IABG plant

become unavailable for the STM solar simulation test, it would

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

Exact determination of the postponement of milestone M7 and

the effects on the successive ones (M8-M11) are being

investigated in connection with a rescheduling of the

FM-integration. The effects of the announced delays for the

FI-FM and the WFC-FM must be reviewed.

The Integrated System Test (1ST) and the EMC Test for

conducted noise will be carried out in connection with the

EM-integration schedule.

When milestone M5 has been reached, verification of

EM-objectives will be reviewed separately from the design review

(DR 2) by the DFVLR project directors for the chief contractor.

The DR 2 is planned for the first quarter of 1986.

1.3 Survey of Problems

Area Type of Problem

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

2. System - Agreement with NASA on HRI random test loads

has not been reached.

Failure of high vacuum in the HRI-detector on

the attached ion pump needs to be clarified

and eliminated.*

Time delays in FI-FM completion require

clarification and determination of auxiliary

measures.*

3. Mechanical

Subsystems At present, no problems.

-7-
4.Electric

Subsystems

Failure of the oven-stabilized quartz in the

data processing system needs to be clarified

to guarantee that sufficient operating safety

exists for the FM on the "SinglePoint-Failure" position.

Exceeding the temperature limits on the solar

generator on the open loading bay in the

Shuttle and during direct contact with the

sun's radiation can be prevented by altering

Shuttle orientation in the PIP.*

5. Telescope The light scattering requirements of /7

the star sensor on the AKS-system cannot be

satisfied and need to be discussed.

6. Assembly,

Integration

Test

Assembly of the FM-mirror system has been

interrupted due to irregularities in the gold

damping of paraboloids P3 and P4.

Suitcase test date for JSC overlaps with

EM-AIT planning by about one week.**

The possibility that the IABG test chamber for

the solar simulation test may not be available

when needed would necessitate costly

replacement measures.

7. Ground

Equipment

At present, no problems.

-8-
8. Mission

Safety

Dragging construction part delivery from

MBB.**

Launch

Vehicle

Interface

At present, no problems.

10. Mission

Operation

Mission operation and simulator development /8

suffer from understaffing.

The data processing concept remains open.

11. Schedule Postponements are anticipated in the data

transmission and building parts acquisition

subsystems.

Due to problems with the gold damping of the

FM-mirror system, we must reckon with a

postponement of milestone M7. It is not yet

completely clear, to what extent all

successive milestones will be affected by this

factor.

(#Items 2b, 2c, and 4b are problems recently under

consideration. **Items 6a and 8 have been resolved.)

2.0 System

System Budgets

The system budget for energy expenditure and mass, as well as

for the telemetry and command* lists were continued. All

budgets still indicate a level sufficiently below specified

boundaries.

-9-
Reevaluation of the budget for site measuring precision for

the whole system was begun after the process for error addition

could be agreed upon and essentially clarified.

Chemical Purity

During the report period, contamination appeared on the

FM-mirrors in the sterile room at C. Zeiss. Details of

investigations on the causes and measures to eliminate possible

causes are given in section 5.

Based on experience gained from the mirror system, the

sanitary procedures for the DS sterile room were revamped.

At present, investigations are underway to determine to what

extent measures to prevent contamination during launch site

activities must be expanded.

3.0 Mechanical Subsystems /10

3.1 Structure/Mechanisms

The structure was delivered to DS on schedule on July 5,

1985 by MBB.

Since the dynamic analysis of the ROSAT was carried out

using a total weight of 2,800 kg, a new diagonal mass matrix had

to be used for the existing Modal Survey Test, since the real

ROSAT weight presently amounts to 2,460 kg.

The structure was subjected to the Modal Survey Test at DS.

Manual estimations and temporary test evaluations agreed well

with dynamic analysis. Only the final evaluation of test

results will determine if ROSAT will have to adapted to the

mathematical FEM (Finite Element Model).

-10-
The "as built status" of the STM could be presented and also

the analyses related to mass characteristics.

The three qualification models (QM) of the telescope

mechanism—antenna boom and separation switch--(TDM, ABM, SSM)

were delivered to AIT. The ADP's on these mechanisms were also

presented.

Flight model production was begun for the TDM. Integration

is to be completed in October, 1985.

The FM drawings for the ABM and SSM were nearly complete and

will be available at the beginning of October.

The roller leaves of the SSM were altered so that /ll

rolls can be secured onto the compression spring with two

screws, rather than as indicated before.

3.2 Thermal Budget

MLI-production was continued as planned. The first mission

analysis was reworked. Results from the orbiter/ROSAT thermal

analyses for open door situations showed that the solar

generator in the lower range (-z) became too hot when the

shuttle bay was aligned with the sun for 30 minutes. The

temperatures of the CSS I and III also exceeded permissible

values. This was caused by hollow spaces occurring due to

ROSAT's position, and these spaces absorbing incoming sunrays

via multiple reflection, even though the surfaces are

predominantly white.

To solve the problem, talks with NASA have resulted in

reduction of the maximum time (from 30 minutes previously, to 15

minutes now) the bay may be exposed to the sun with this time

recorded in the PIP. This allows all the endangered components

to remain within the permissible temperature range.

-11-
Preparations to carry out the solar simulation test have

begun. A description of the test was presented.

4.0 Electric Subsystems /12

4.1 and 4.2 Energy Source. Pyrotechnics

A status discussion was held on September 17, 1985, at DS to

review production status, FM-component schedule, and processing

status of documentation of both subsystems.

Production status for FM hardware is as follows:

Solar generator:

Design update is completed.

Preparatory work on the panel coating was begun. In

the process it was noted that the panel structures are

not smooth as is normally the case, but rather that

their surface has a wrapped structure. According to

AEG, this is necessary to verify adhesive binding using

additional sample tests (between approximately 1,000 -

10,000 temperature cycles). These tests will be

carried out beginning October 1985, and it was

guaranteed that test results would be available and

evaluated before the start of the actual panel coating

(planned start: December 1, 1985).

Electronic boxes (PDU, PCU, BCU, Shunt, Pyro):

The mechanical parts of the electronic boxes are being

prepared.

Cabling of the shunts has been started.

-12-
Battery (FM) /13

Dornier carried out compulsory inspection ("MIP") of

the FM-battery cells before the cells were capped at

SAFT. Results of this inspection are not yet

available.

Battery (EM)

During the report period, qualification tests on the

EM-battery were conducted successfully. The test

report has been written but not yet delivered to the

DFVLR for evaluation.

The status of subsystem documentation is as follows:

FM-production is being carried out on the basis of

specifications which have already been revised and

which will be presented to the DFVLR as of October,

1985 for evaluation.

The contractor has guaranteed that there have been no

changes in the specifications which would have required

a detailed consultation or else agreement by the

project directors before inclusion thereof.

With regard to NCR's and MRB's test and integration

regulations, there are no unresolved points which

interfere with the planned progression of the

EM-integration and the FM-production.

Scheduling, Problems /14

A review of scheduling (as of August 30, 1985) for

FM-component production showed that all FM-components

are included in the scheduling. This report took into

-13-
consideration the situation (as of September 12, 1985)

with delivery of HIREL construction parts.

HIREL construction parts are essentially available.

The delivery date for the remaining construction parts

(such as Relay M300 and M502) are, in accordance with

the "GPP Delay" list of July 27, 1985, acceptable for

FM-preduction.

Delivery (entrance DS) of the STM solar generator for

STM/EM-integration took place on August 9, 1985.

No technical problems occurred during FM-electronic box

production.

4.3 Wiring /15

As with the subsystems comprising energy sources and

pyrotechnics, status discussions were held at DS for this

subsystem on September 17, 1985.

The status of FM-cabling network production is as follows:

The power and pyrocable network is laid in the

auxiliary structure for cable network production.

The signal cable network will go into production

shortly in the placements.

The telescope cable network is laid; plugs are attached

on one side.

The STS-heater cable network has not been laid yet.

The STS-cable network will be installed as soon as the

signal cable network is finished.

-14-
The status of subsystem documentation is as follows:

Production on the FM-harness list will begin soon.

The cabling list for the STS-heater cable system has

been prepared.

Scheduling, Problems /16

Projects on the FM cable system are on schedule (as of

August 30, 1985). The contractor agreed to include

STS-heater cable system production in the scheduling.

Short-term problems with deliveries from Raychem-Kabel,

such as occurred at the beginning of the report period,

have been resolved and have no effect on FM-production.

4.4 Data Processing /17

The DBS was delivered to the system shortly before the start

of this report period. During integration in the ROSAT-EM, some

mistakes on the DHM or else on its exterior interface were

detected. However all of these were within normal, i.e.,

expected, limits. The mistakes were eliminated without problem

immediately after concluding integration activities.

Upon completing the radiation EMC qualification test, which

had been delayed, the DHS was available on shedule for the

planned compatibility test at JSC.

Due to the problems which arose on the oven-stabilized

quartz in the on-board clock, the current concept of this

single-point-failure component had to be reevaluated: For

reasons of reliability, DS suggests this oscillator be designed

for the FM-model.

-15-
FM-component construction was started along with these

EM-activities. The original concept of checking the planned

construction part exchange using SOS parts on the EM can no

longer be maintained due to late deliveries. As such,

disturbance-free use of SOS construction parts can first be

checked on the FM.

4.5 Data Transmission /18

A test set was assembled for the interface tests at NASA-JSC

to determine the data recording system's compatibility with the

Shuttle. This test set consisted of a transponder (FM), the

decoder function model, the data processing system's EM,

transponder test instruments, and several special instruments.

Test regulations were set by NASA.

Execution of the test at the end of September at NASA-JSC

determined that the ROSAT data recording system is completely

compatible with Shuttle requirements.

Transponder

One transponder was employed in each case for the interface

tests on the whole system and in the test set. To date, no

deviations from specified behavior have been detected.

Decoder

The EM was integrated into the satellite (EM/STM). There

were no notable difficulties during the interface test on the

whole system. Production on conductor plates and housing for

the FM was started.

Antenna

The EM was delivered. Flight model production was started.

-16-
4.6. Attitude measurement and control /19

Star Sensor

After the TV test, leakages and image errors caused by poor

focusing were determined in the EM of the STC. As a result of

this, the STC was returned to SIRA on July 17, 1985.

Gyroscope

Conduction plate production for the FM was started. The EMC

test report has been prepared.

AMCE

EMC tests were conducted, and test reports prepared.

Reaction Wheels

Magnetic parts such as reactors and transformers for the FM

were prepared.

Star Catalog

A re-worked version of the star catalog is available.

Documentation for it is being prepared.

Software

Preliminary statistical and dynamic tests on software parts

were conducted (standby-, checkout-, and safe-mode). Software

development for normal and degraded mode are to be completed by

the end of December 1985.

-17-
Problems /20

The EM-subsystem cannot be completely delivered to the 1ST.

Remaining software will be developed using the star sensor

prototype. Delivery difficulties with construction parts could

possibly influence the star sensor FM date.

5.0 Payload /21

5.1 X-Ray Telescope

5.1.1 Telescope QM and FM

During assembly of the telescope QM following the vibration

qualification test, the components were measured optically. No

significant changes were determined compared to conditions

before the test. Thus, the telescope successfully passed

vibration qualification. The test report has not been filed.

The telescope QM was remounted, equipped with thermal

hardware, and readied for installation into the spacecraft-STM

together with the integrated FI-EM on August 15, 1985.

Production on the CFK-barrels of the telescope flight

model's optical bank began during the report period. In spite

of a several-month delay in production startup, the date of

delivery to the telescope assembly is not in danger.

5.1.2 Mirror System

The projects on the flight mirror system have been stalled

substantially. One reason for this is the problem with the gold

damping of flight mirrors P4F and P3F, described in the last

report. To test the effects of the spots in the gold coating,

it was necessary to delay starting the flight mirror system

-18-
assembly. The measures which have been worked out are currently

being tested in the repairs on P4F.

Unfortunately, it was necessary to scrap a check on /23

whether P4F and P3F can be used X-ray optically in spite of the

small spots on less the 0.5% of the entire surface. At the end

of July, 1985 a substantial contamination on the gold coatings

was discovered during a control of the the test mirrors coming

from the sterile room at C. Zeiss. The quartz micro-vehicles

(QCMs) applied together with on-going environmental tests had

failed and provided no proof of contamination. Flight mirrors

P4F and P3F, stored in the sterile room, were likewise

contaminated, making an X-ray test meaningless.

The renewed contamination in the sterile room at C. Zeiss

leads to a further delay in production of the flight mirror

system. The expectation, based on measures taken after

discovering the contamination during verification model

production, that the causes were eliminated and controls

improved, proved unfounded. For this reason, a renewed thorough

investigation to determine and eliminate the contamination

sources was introduced. This resulted to a large extent in oils

being banned from the sterile room, as well as carbohydrates in

the sterile room air being eliminated by changing the air ducts

and improving filtering. The necessary precautionary changes

and resulting verification of the room's sterility led to flight

mirror system assembly being delayed until January 1986. This

means a 7-month delay in the delivery date.

Repairs to the sterile room at C. Zeiss determine the

critical course of the flight mirror system and with it of the

telescope-AIT-program. The contamination has caused DS to

reevaluate contamination risks during the AIT-program.

-19-
Plans are being made to separate the telescope program

from the spacecraft-Bus-program. This would likewise assist

largely in eliminating delays with the flight mirror system.

Additional time would be saved by reevaluating the necessity of

tests. Plans exist to rework the flight model-AIT-program by

the end of the year.

The status of projects in the contract (separate from those

for the entire system) on production of the individual flight

model mirrors at C. Zeiss is as follows:

With the exception of the concluding X-ray optical test of

H1F and H2F, as well as cutting the P1F, H1F, P2F, and H2F to

length, work is completed. The projects have been delayed

temporarily in connection with repair measures for gold spots

and contamination.

5.1.3 Focal Plane Instrumentation

The FI-EGSE and FI-EM were input on schedule. Acceptance

tests and electrical and mechanical integration into the

spacecraft were conducted successfully.

Production of Fl-flight model components were continued

during the report period.

Unresolved problems were considered further: /24

HRI-Random Vibration Loads

Based on telescope vibration test results, DS reevaluated

HRI-testloads. Because of unexpectedly high telescope

resonances in the range around 150 Hz, no reduction resulted,

but rather an increase of HRI loads. In discussions with DS and

GSFC it became clear, however, that DA had made very

conservative estimates of load calculations. For this reason,

-20-
it was agreed that GSFC should derive realistic HRI random loads

using available test data on the basis of joint ROSAT/STS

analyses. The results of this calculation are to be determined

with the DFVLR-PL, before the HRI is tested.

FI-FM-Delavs

Due to a three-month delay Fl-mechanical component

production delay at MBB (under contract with MPE) and

difficulties in procuring electronic components (ADC's, peak

detectors), the FI-FM-delays have become more critical. In

addition to this, design changes are necessary on the flight

PSPCs to guarantee proper functioning during the mission. These

changes and additional tests likewise influence the

FI-FM-schedule. The exact extent of the delays is presently

being worked out at MPE.

The effects of the delays on the overall ROSAT-shedule

remains open. It is planned to contain the delays by

restructuring the FM-AIT-plan.

Vacuum Loss in the HRI-EM

Following integration of the FI-EM into the telescope and

into the spacecraft it was determined that the vacuum in the

HRI-EM collapsed. The HRI-EM is to be repaired following its

completion at the beginning of October, 1985.

5.2 Wide Field Camera /25

The 0-level document "Spacecraft/XUV Wide Field Camera,

Interface Requirements" was reworked, and Issue 3—Revision A

from June 7, 1985, was signed into power by the DFVLR on

September 13.

On August 21, the DFVLR-PL tested the STM's ADP, and one day

later the STM from Dornier was in-feeded as specified in the

-21-
contract. This WFC-input took place—just as EM-input did at

the end of June 1985—once again before the date set in the

AIT-plan.

Further activities during the report period:

Preparations for Phase 2 Safety Review by NASA

Further discussion on the WFC check-out sequence on the

arm of the Shuttle and "go/no go" criteria (Issue 2

from August 28, 1985).

Routine interface discussion within the framework of

the status meeting at DS from September 17 to 19.

Acceptance of all interface drawings including

expenditure status in the "Configuration Status List

(CSL)" (construction document catalog).

Outlook /26

The English project scientist announced alteration requests

in the course of the AIT-program for the WFC-FM (Summer 1986),

in order to gain more time to be able to calibrate the

instrument better.

The DFVLR-PL is trying to supply the requested time.

Chances are good that this will occur.

6.0 Assembly, Integration, and Test /27

QM-Telescope Integration

Following the vibration test conducted in the last report

period, the telescope was inspected visually; the AKS was

optically measured; the QM-thermal heat shield star sensor mass

-22-
model, and gyroscope mass model were integrated; the mirror

system was tested optically, and the EM-FI was installed. The

QM-telescope could be released on August 15, 1985, for

Bus-integration after assembling thermal hardware and

instrumentation for the Modal Survey Test and the solar

simulation test.

Bus-Integration

Upon delivery of the DPS, which was completed late,

pre-integration of the subsystems on the auxiliary structure

could be continued and successfully concluded with tests from

tape recorder 1, pyrotechnics, and electronic integration of the

EM-WFC and the EM-FI.

The structure sent by MBB on July 5 was mounted in assembly

scales in the clean room. Transfer of the EM-cable network and

the subsystems to the central structure or else into the

compartments took place promptly.

The QM-telescope and thermic hardware were then installed.

Instrumentation for the modal survey and the solar simulation

tests were carried out, and the STM-WFC of the solar generator

central panel and the antenna layouts, the star sensors, magnet

spools, the MM-battery, and the solar generator side panels were

assembled. Mass models were built and assembled for missing

AMCS-hardware.

Modal Survey Test

DS decided to have the Modal Survey Test of the S/C STM

conducted by the IABG, but in the clean room at DS. A ten-day

gain in time caused by scrapped transports and better

environmental conditions supported this decision. The sterile

room was prepared by placing strengthening elements at the

foundation posts to support the 22-ton IABG test frame. The

-23-
test frame was cleaned, fastened in its ankerings, and subjected

to an Eigen frequency test. The X/C was transferred from the

horizontal trolley to the vertical trolley and turned to a

vertical position. Then it was placed in the acceptance box of

the IABG frame adapted for ROSAT. After constructing the

activator frame and coupling the activator with the S/C, the

test receivers were adhered (85 receivers with 250 measuring

points). The pre-test review and the test release took place on

September 9, the post-test review on September 27. Deviations

from values measured and reviewed during the test amounted to

approximately 8% compared to those derived analytically using

the ROSAT calculating model. The test was successfully

completed. The test report will be presented in two months, as

agreed.

The cooperation of the companies involved, IABG, DS, /29

and MBB, was remarkably good, a fact which led to essentially

friction-free test execution.

Solar Simulation Test

The period of time from January 7 to February 26, 1986,

planned for ROSAT, remains unchanged.

The time period planned for use by TV-SAT from January 20 to

February 26, 1986 was changed to February 5 to February 26,

1986. In addition, the test may be extended by eight days.

The two periods overlap by fourteen workdays.

On September 9, 1985, talks with all involved parties took

place at the IABG. They discussed the interrelated effects each

one of the involved projects would have on the others if it were

given priority.

-24-
JPL, DS, and the DFVLR-PL met for talks at JPL in Pasadena

on September 27, 1985. They discussed the use of test

facilities located there. JPL will quote ROSAT a price by mid

October.

RF Compatibility Test /30

The suitcase instrument set was prepared and delivered to

JSC. The tests successfully proved the compatibility of the

ROSAT telecommunication with the Shuttle.

7.0 Ground Equipment /31

7.1 EGSE and Checkout Software

Hardware and software were ordered to connect a data

interface between the S/C-EGSE and the GSOC. The data interface

for the GSOC was included in the specification "EGSE and

Checkout Software." The specification was brought up to date

(Version 3.2).

The available monitor tables were reworked. ETOL-test

sequences were plotted for integration and checkout of the DHS,

the WFC, and the FI. These sequences were brought up to date.

Further service programs for AIT-support were calculated. The

C/0 test sequences were entered onto a list.

The AMCS-SCOE (special checkout equipment) was presented by

DS, and interface tests were conducted with the S/C-EGSE.

7.2 MGSE

The vertical assembly frame was completed and has been in

use since the Modal Survey Test. The telescope tracking frame

is likewise already in use.

-25-
Preparation of test and operation regulations is being

cont inued.

The contract was signed for completing the WSA-adapter to be

used for the solar simulation test. The activities involving

the MGSE will be extended by three months until December 1985 to

allow for production of additional instruments.

7 3 Optical Ground Support Eauipment (OGSE)

No projects.

8.0 Mission Safety /33

STS Safety (Flight and Ground Operation)

The integrated data packets for saftey inspection of Phase 2

were released by the project directors and forwarded to

NASA-GSFC project directors for release to the inspection

committee at NASA-JSC.

Upon conferring with NASA-JSC and -KCE, the NASA-GSFC

directors confirmed the May 1985 date set for safety inspections

of flight and ground operations.

Safety Inspection Dates:

Flight Operation: October 2-3, 1985

Ground Operation: October 10, 1985

Inspection by NASA-GSFC directors of the material lists

included in revisions No. 4 has not been completed. Information

for reference documents requested in the meantime was sent to

NASA-GSFC in mid September 1985.

-26-
Dependability

Analysis of the FMECA and SPF lists for the subsystems by

the DFVLR directors could not be completed yet since DS still

has not delivered the system analysis.

Quality Control

During the report period, a total of 67 more disturbances

and second stage MRB's involving EM and FM components of the

satellite system have been checked and evaluated by the project

directors.

On the occasion of the tenth status discussions on September

17, 1985 at DS, the status of all level 2 disturbances were

checked in accordance with the DFVLR control list from September

12, 1985.

The result was that from a total of 111 second stage

disturbance reports, 54 had been resolved, and 55 remained

open. With regard to the open disturbance reports, it was

requested of the contractor, that measures be introduced

promptly to resolve the problems.

On June 6, 1985, an inspection was conducted at Teldix Co.

in Heidelberg following final controls of eight FM-lots each

involving eight^ types of double-sided PCB' s (printed circuit

boards) for the reaction wheels' control electronics. This

acceptance test was necessary after Teldix had applied for an

RfW (request for waiver) on a release of the production of

double-sided PCB's for the ROSAT Project. Based on the quality

test, all FM-lots for ROSAT were accepted.

During the sight test which was then conducted on a sampling

of 2 PCB's per lot, a lot deficiency was discovered which would

effect performance (excess soldering material caused parts to

-27-
stick). This deficiency was classified as critical with regard

to subsequent piecing.

For this reason, this lot and successive lots having /35

the same design were not released for use.

It was agreed, that Teldix should present corrected PCB's

for another inspection after taking necessary measures to

eliminate the deficiency.

Central Construction Part Acquisition

During the report period, two discussions took place (on

July 29 - 30, 1985 at the agency, and on September 9, 1985

within the framework of the tenth status talks at DS) regarding

the status of construction part acquisition.

Accordingly, the following status may be reported at the end

of this quarter:

After analyzing the agency's "delay" list 15A, dated

September 9, 1985, the contractor and the DFVLR directors made a

list with a total of 39 "line items" (Li's). A number of these

items have substantial delivery delays, and for a number of them

no alternative accelerated delivery can be provided.

It was agreed, that the agency and DS would promptly clarify

the outstanding delivery dates (between KW 43/85 to KW 9/86)

with the involved parties regarding problems with dates for the

production of FM-components.

The delivery situation of two radiation hard RCA CMOS-blocks

has not changed. Anticipated delivery date for the industrial

types is mid October 1985, and the beginning of December 1985

for the HIREL types.

-28-
Tests on 20 "upgrading" construction parts which are /36

being conducted at present at the EPI could not be completed in

the report period.

As mentioned already in last quarter's report, the project

directors prepared two acquisition status lists for internal

use. These are based on the entire acquisitions list and

"delay" list 14A made by the agency on July 27, 1985 and are to

serve the project directors as an instrument with which to

better judge the delivery situation for FM-components.

9.0 Launch Vehicle Interface /37

ICD-A-18410

NASA-JSC presented a so-called "preliminary version" of

DFVLR/DS commentary on the temporary "Draft Version" (from

February 15, 1985) of the ICD. This preliminary version is to

be discussed within the framework of a NASA interface discussion

to be held at the beginning of October 1985 at NASA-JSC. The

aim of this discussion is to prepare a "baseline version" of the

ICD which can be signed into effect.

On the basis of the edited document TN-2002-2180 DS/017, 2nd

edition dated July 9, 1985, in which the electric interfaces

(hardlines) of the ROSAT to the OIB are defined, the "design

review" (DR) of the OIB was conducted on September 30, 1985 at

NASA-JSC. The second part of this review will take place in the

first week of October, also at NASA-JSC.

A summary of results or else decisions on the DR will appear

in the next report.

PIP-Annex

Preparations were completed for discussions on the PIP-A8

-29-
(launch site support plan draft from June 1985) and the PRD with

NASA-KSC on October 9 and 11, 1985 at NASA-KSC.

Suitcase Test at NASA-JSC

The so-called suitcase test (compatibility test of the

ROSAT-RF system with the STS) was conducted successfully at

NASA-JSC from September 24 - 30.

The corresponding compatibility test ("Van-Test") of /38

the ROSAT RF-system with the NASA ground stations will be

conducted on October 1-3 using the NASA-GSFC test instrument

("Van"), also at NASA-JSC.

"Contingency EVA"

The concept for the problem configuration of a "contingency

EVA" was prepared by agreement with the contractor. Plans are

being made to present and discuss this concept on October 7,

1985 at a special work discussion with NASA-JSC experts.

10.0 Mission Operation /39

Basically, projects ran according to schedule. A number of

projects could not be carried out as planned due to insufficient

information or delayed experiment operation requirements

(EORD). This compensated partially for a lack of manpower.

Coordination

Regular meetings between GSOC and the chief contractor,

Dornier System (DS), were set to improve agreement on mission

operation preparations with the satellite producer.

-30-
Flight Operation

A preliminary, not entirely finished outline of the

completed "Experiment Operations Requirements Document (EORD)"

is available and is being discussed with MPE. A baseline

version of the EORD cannot be expected before the beginning of

November 1985. The keypoint here lies in prepartion of

telemetry and commando information needed to establish data

banks at the GSOC. For the same reason, it is necessary to hold

talks with DS regarding the operation manual.

Ground Operation

The ROSAT project requirement document (GSOC-PRD) has been

presented in outline form. The preparatory projects for the

NASA-SIRD are not yet completed. Agreement on the "remote POCC

interface" (PIP-Annex 5) between NASA-JSC and GSOC has been

reached except for several inquiries regarding the last

DFVLR-NASA talks.

Precision investigations on ground station computer /40

time allotment have not been completed.

Investigations are under way on the possibility of including

the Australian ground station "Alice Springs."

Mission Planning and Analysis

Definition of mission planning system (MPSS) requirements

progresses haltingly. "Beta"-angle and shadow time calculations

beyond the nominal ROSAT mission in high dissolution were

conducted to support ROSAT thermal analysis.

Post-facto site determination software was developed

further. In order to continue this development, information

from the ROSAT project was needed, which is not yet available

-31-
(for example, converstion of AKS telemetry datainto telescope

axes direction values).

Projects in the division of "site control" depend on

availability of the star catalog software from the ROSAT

project. Availability dates for star catalog software packets,

set in an earlier schedule (status DRI) for July 1985, will

occur later in accordance with the project schedule which is now

valid (as of May 7, 1985).

Data System

Data interface specifications between GSOC and the ROSAT

FM-satellite during the IST-phase were completed. The off-line

computer capacity at WT-DV for support of GSOC requirements

(ROSAT and other projects) was analyzed. Temporary /41

results are available.

AMCS Simulator

Bid requirements for preparing software for servicing

interfaces from the AMCD-simulator hardware and the simulation

computer were announced by GSOC to DS.

Development of the simulator system software was started.

A basis version is available in releasable form and was

delivered to RAL for interface tests between sensor simulation

software and the system software. RAL has problems getting

access to suitable computer systems.

The design of the "dynamics and sensor simulation software"

continues according to plan.

-32-
Test and Training

No activities to report.

Software

No activities to report.

11.0 Schedule /42

Planned Dates

The currently valid DS schedule dated May 7, 1985 quotes

October 30, 1987 as the takeoff date. This corresponds to the

contract's milestone plan.

The NASA schedule in the PIP planned September 30, 1987 as

the takeoff date (reference milestone: "ready for launch").

Taking into consideration the 4-week buffer before transport of

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

Actual EM-Status

In view of the valid schedule, the EM-integration is on

schedule.

Actual FM-Status

Preparation of the flight mirror system in the C/D contract

(milestone M7) is delayed. The extent of the delay and its

effect on the rest of the milestones (M8-M11) must be

determined. The FM-integration course is being revaluated for

this and other reasons.

-33-
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13.0 APPENDIX /62

13.1 Personnel utilization for DFVLR-PT and DFVLR-WT

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-
13.2 Key to Abbreviations 765

ABM

ADP

AKS

AIT

AMCD

AMCE

AMCS

BAT

ECU

Bit. Sync,

BMFT

CCD

CCL

C&DH

CEL

CFK

CFRP

CITE

Crnd

CMOS

C/0

CPP

CPU

CSA

CSS

CZ

Antenna Boom Mechanism

Acceptance Data Package

Ausricht-Kontroll-System

Assembly, Integration and Test

Attitude Measurement and Control Data Unit

Attitude Measurement and Control Interface

Electronics

Attitude Measurement and Control Subsystem

Battery

Battery Control Unit

Bit Synchronizer (Synchronization)

Bundesminister fur Forschung und Technoloigie

Charge Coupled Device

Charge Current Limiter

Command and Data Handling

Control Electronics

Carbon Fiber Reinforced Plastics Z

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

/(

/X//DhVLk

V BPT

RONTGENSATELLIT Status :

30.09.85
766

DC

DEC

DFVLR

DFVLR-PL

DHS

DMA

DMOD

DMEL

DPS

DS

ECS

EED

EEL

EGSE

EM

EMC

EOL

EORD

EPD

ESA

ETOL

EUV

FEM

FI

FLS

FM

FMECA

FWHM

A

s s s s Pipvl p

V B PT

Direct Current

Decoder

Deutsche Forschungs- und Versuchsanstalt fur

Luft- und Raumfahrt

DFVLR-Projektleitung

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

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

Finite Element Model

Focal Plane Instrumentation

Fiducial Light System

Flight Model

Failure Mode Criticallity Analysis

Full Width at Half Maximum

RONTGENSATELLIT Status:

30.09.85
767

r*

•5

/*?»

'M

GF

GSE

GSFC

GSOC

GVS

GYP

GYPE

GYPS

HC

HEAO-2

HIREL

HK

HP

HRT

ICD

INVAR

1ST

JSC

kbps

KSC

KW

LCL

LED

LHC

LI

LP

s fA s s P) F V 1 P

V BPT

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

Interface Control Document^

(Special steel alloying trademark)

Integrated System Test

Johnson Space Center

Kilobit per second (deutsch: kbit/s)

Kennedy Space Center

Kalenderwoche

Latching Current Limiter

Light Emitting Diode

Left-hand Circulation

Line Item

Low Power

RONTGENSATELLIT Status:

30.09.85
MA

MAC

Mbps

MC

MCC

MCP

MDM

MED

MES

M'GSE

MIP

ML I

MM

MM

MOU

MPE

MPG

MPSS

MRB

MSA

MSSL

MUC

MUDAS

MVL

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

Massenmodell

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 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

DFVLR

B PT

RBNTGENSATELLIT Status:

30.09.8 5

It 5
769

OBC

OGSE

OIB

OSR

PCB

PCU

PDU

PETS

PGHM

PHP

PIP

POCC

PPF

PRO

PSE

PSK

PS PC

PSS

PYB

QM

RAL

RE

RF

RfW

RMC

RMS

ROSAT

RS

Onboard Computer

Optical Ground Support Equipment

Orbiter Interface Box

Optical Surface Reflector

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

Payload Support Equipment

Phase-shift Keying

Position Sensitive Proportional Counter

Power Supply Subsystem

Pyrotechnics Electronic Box

Qualification Model

Rutherford Appleton Laboratory

Radiated Emission

Radio Frequency

Request for Waiver

Right-hand Circulation

Remote Manipulator System

Rontgensatellit

Radiated Susceptibility

DFVLR

B PT

RONTGENSATELLIT Status:

30.09.85
770

RSGF

RSS

RT

RW

RX

Rigidized Sensing Grapple Fixture

Rotating Service Structure

Real Time

Reaction Wheel

Receiver

S/C

SCOE

SERC

SEU

SIRD

S/L

SOC

SOS

SPF

SPL Code

SSM

SSM

ST

STC

STE

STM

STS

SURS

Spacecraft

Special Checkout Equipment

Science 6 Engineering Research Council

Single Event Upset

Support Interface Requirements Document

Serial Load

Science Operations Center

Silicon on Sapphire

Single Point Failure

Split Phase Level Code

Single Surface Mirror

Separation Switch Mechanism

Star Tracker

Star Tracker Camera

Star Tracker Electronics

Structural Thermal Model

Space Transportation System

Shuttle Umbilical Retraction System

TA

TC

T/C

TCE

TCS

TDM

Technical Instructions

Telecommand

Thermal Control

Thermal Conditioning Equipment

Telecommunication Subsystem

Telescope Door Mechanism

DFVLR

B PT

R5NTGENSATELLIT Status:

30.09.85
771

TM

TR

TT S C

TV

TX

US

VPHD

VPF

WDE

WFC

WFCC

WSA

XRT

ZERODUR

ZDE

Telemetry

Tape Recorder

Telemetry, Tracking and Command

Thermal-Vakuum

Transmitter

Subsystem

Vertical Payload Handling Device

Vertical Processing Facility

Wheel Drive Electronics

Wide Field Camera

WFC-Consortium

Weltraumsimulationsanlage

X-Ray Telescope

(Trademark for the glass-ceramic-substance'

for the mirror) i

Central Data Electronics

B P T

RONTGENSATELLIT Status:

30.09.85