service module motion control and navigation system · 2013. 4. 20. · universal docking module,...

MOTION CONTROL AND NAVIGATION SYSTEM 1 E 25 Oct 99

SERVICE MODULEMOTION CONTROL and NAVIGATION SYSTEM

(��)

SM.0


Page Issue and Revision Log


TABLE OF CONTENTS

INTRODUCTION ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

1. GENERAL INSTRUCTIONS ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1—11.1. CREW RESPONSIBILITIES...................................................................................... 1—11.2. SAFETY PRECAUTIONS.......................................................................................... 1—1

�� . . . . . . . . . . . . . . . . . . . . . 2—1�� .................................................................................... 2—12.2 �� .......................................................................... 2—1

�� . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3—13.1. REBOOST................................................................................................................. 3—1�� ................................................................................. 3—1��

�� ACH AND ATTITUDE CONTROL THRUSTERS) ... 3—23.2. DOCKING, UNDOCKING, REDOCKING .................................................................. 3—3

3.2.1. SOYUZ DOCKING WITH SM............................................................................. 3—33.2.1.1. ESTABLISHING COMMUNICATION WITH SOYUZ................................... 3—33.2.1.2. PREPARATION FOR DOCKING................................................................ 3—43.2.1.3. RENDEZVOUS MONITORING .................................................................. 3—4

3.2.2. SOYUZ RENDEZVOUS AND DOCKING WITH FGB......................................... 3—71.1.1.1. ESTABLISHING COMMUNICATION WITH SOYUZ................................... 3—73.2.2.2. PREPARATION FOR DOCKING................................................................ 3—73.2.2.3. RENDEZVOUS MONITORING .................................................................. 3—8

3.2.3. PROGRESS RENDEZVOUS AND DOCKING WITH SM................................. 3—113.2.3.1. PREPARATION FOR DOCKING.............................................................. 3—113.2.3.2. RENDEZVOUS MONITORING ................................................................ 3—11

3.2.4. PROGRESS RENDEZVOUS AND DOCKING WITH FGB............................... 3—143.2.4.1. PREPARATION FOR DOCKING.............................................................. 3—143.2.4.2. RENDEZVOUS MONITORING ................................................................ 3—14

3.2.5. RENDEZVOUS AND DOCKING WITH ORBITER ........................................... 3—173.2.5.1. ESTABLISHING COMMUNICATION........................................................ 3—173.2.5.2. PREPARATION FOR DOCKING.............................................................. 3—173.2.5.3. RENDEZVOUS MONITORING ................................................................ 3—18

3.3. SPINNING UP GYRODINES................................................................................... 3—183.4. MODE TRANSITIONS............................................................................................. 3—18��!�� "#$%"�$�#

�# � ��N USING ATTITUDE CONTROL THRUSTERS) ... 3—183.4.2. INITIATING TRANSITION FROM RS LAPTOP ............................................... 3—18

3.5. MONITORING MODE EXECUTION........................................................................ 3—18

�� . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4—1!�� &�� ........................................ 4—1�� '�� (�� ................................... 4—1


5. VISUAL OPTICAL DEVICES ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5—1)�� *�� &� �+,-+� ................................................................ 5—1

5.1.1. TECHNICAL PARAMETERS ............................................................................. 5—15.1.2. EXTERNAL VIEW.............................................................................................. 5—25.1.3. INITIAL STATE.................................................................................................. 5—25.1.4. SETUP............................................................................................................... 5—25.1.5. VIEWING FIELDS.............................................................................................. 5—35.1.6. CLOSEOUT OPERATIONS............................................................................... 5—35.1.7. OFF-NOMINAL SITUATIONS............................................................................ 5—4

)�� &� �!.� �+�/��........................................................................................ 5—55.2.1. TECHNICAL PARAMETERS ............................................................................. 5—55.2.2. EXTERNAL VIEW.............................................................................................. 5—65.2.3. VIEWING FIELDS.............................................................................................. 5—75.2.4. SETUP............................................................................................................... 5—7)��)� �� 01�� (�� &�� ..... 5—85.2.6. CLOSEOUT OPERATIONS............................................................................... 5—85.2.7. OFF-NOMINAL SITUATIONS............................................................................ 5—9

5.3. PUMA PORTABLE ZOOM VIEWFINDER ............................................................... 5—105.3.1. TECHNICAL PARAMETERS ........................................................................... 5—105.3.2. EXTERNAL VIEW............................................................................................ 5—115.3.3. VIEWING FIELD .............................................................................................. 5—125.3.4. SETUP............................................................................................................. 5—12)��)� �� 01�� (�� ............... 5—135.3.6. CLOSEOUT OPERATIONS............................................................................. 5—135.3.7. OFF-NOMINAL SITUATIONS.......................................................................... 5—14

�� . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6—1

7. SM AND FGB PROPULSION SYSTEM .... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7—17.1. PURPOSE................................................................................................................. 7—17.2. TECHNICAL PARAMETERS..................................................................................... 7—12�� &�� .............................................................. 7—12�� ( �� &�� ............................................................... 7—2

2�� &�� &��.......................................................... 7—3

!� �� . . . . . . . . . . . . . . . . . . . . . . . 8—13�� ......................................................................................... 8—13�� ........................................................................................................... 8—1

8.2.1. PROPELLANT MONITORING UNIT DISPLAY.................................................. 8—38.2.2. MODES DISPLAY.............................................................................................. 8—3


9. DYNAMIC MODES ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9—14�� (� �� (� �� ......................................................... 9—14�� (� �� ( ��(�� ............................................................. 9—14�� (� �� ( ��(�� ............................................................. 9—24�� (� �� ............................................................. 9—34��!� �� (� �� ............... 9—44��)� �� (� �� ........................................................... 9—44��5� ��(� �� ..................................................... 9—54��2� ��(� �� ..................................................... 9—5

10. REFILLING ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10—1�.�� (�� 0% � �(�� ' �� 6 � ............................ 10—1�.�� (�� 0% � �� ............... 10—1�.�� (�� 0%� �� ................ 10—2�.�� (� �� 0%� (�� # �............... 10—2�.��!� �� (� �� 0%� (�� ( �� 7 � ......................... 10—3

�.�� (�� 0%� �(�� ' �� 6 � ............................. 10—4�.�� (�� 0%� �� ................ 10—4�.�� (�� 0%� �� ................ 10—5�.�� (� �� 0%� (�� # �............... 10—5�.��!� �� (� �� 0%� (�� ( �� 7 � ......................... 10—6

�.�� (�� 0 � ��8��9� ��' �� 6 � ..................... 10—7�.�� (�� 0 � �� ............... 10—7�.�� (�� 0 � �� ............... 10—8�.�� (� �� 0 � (�� # � .............. 10—8�.��!� �� (� �� 0 � (�� ( �� 7 � ........................ 10—9

�.�!� �(�� 0 � ��8��9� ��' �� 6 � ................... 10—10�.�!�� (�� 0 � �� ............. 10—10�.�!�� (�� 0 � �� ............. 10—11�.�!�� (� �� 0 � (�� # � ............ 10—11�.�!�!� �� (� �� 0 � (�� ( �� 7 � ...................... 10—12


INTRODUCTION

�:;<; �� crew procedures are based on preliminary inputs and will be updated as the system isfurther developed and initial documentation is released.

These crew procedures =>?@AB? �� >C;DA@B>? CD>=;EFD;< A?E D;G;D;?=; EA@A�

These �� crew procedures <FCC>D@ 0+� H 4 (software release 4) for stage 1R – 9A.

These crew procedures are intended for trained crew members who have completed the full trainingcourse and simulations.

These crew procedures may be updated pending ISS assembly, system modification and procedurevalidation at simulators and training facilities.

These crew procedures contain indications, required for monitoring. Crew can monitor otherparameters at their discretion.

ACRONYMS AND ABBREVIATIONS

0+� onboard computer system0� control unit1I�� integrated control panel�J� central post computerH�H multiplexer/demultiplexer, MDM $� random access memory, RAM�+� program timing device�$� read-only memory, ROM��0# onboard equipment control system-+H terminal computer�� matching unitJ� central post�IK$ Report to MCC�LM�$ �MCC$N� continuous sound$N� intermittent sound1I�� integrated control panel�N� light emitting diode, LEDOPKN pushbutton, pbOI pushbutton, pbLM�$ On MCC GO, per MCC instructionsQRS connectorTSU switch, sw


0PMO V��%0PMO V�� -�%# 0#0+�%0+� 0%0�0� 0%0� 0 0� �0%0� �0 0��%0�� 0 0��-0V%� %0V%� 0V�� %0V�� %� -0%-0 �� $�%$� ��%�� %�� H%�H1�H � 0� %� �+� �%� �� "� �+� �� #0%��#0 ��-H��V�

fuel tanks electropneumatic valvesoxidizer tanks electropneumatic valvesProgress cargo vehicleassembly compartmentNitrogen tankhigh-pressure fuel tankhigh-pressure oxidizer tankfuel tankcompressor unitfuel tanks pressurization unitoxidizer tanks pressurization unitauxiliary fuel tanks pressurization unitauxiliary oxidizer tanks pressurization unitlow-pressure fuel tanklow-pressure oxidizer tankoxidizer tankpropellant monitoring unitfuel section electrohydraulic valve unitoxidizer section electrohydraulic valve unitfuel tanks evacuation and pressurization electropneumatic valve unitoxidizer tanks evacuation and pressurization electropneumatic valve unitfuelSM attitude control thrusters (13.3 kg)FGB fuel tanksFGB oxidizer tanksroll thrusterspropulsion systemfuel refilling deviceoxidizer refilling deviceSM reboost engine (313 kg)fuel refilling valveoxidizer refilling valvefuel manifold valveoxidizer manifold valveSM reboost engine fuel line valvemagnetic pulse valveSM reboost engine oxidizer line valvetank cutoff valvefuel manifolds combining valvehigh-pressure compressors combining valvefuel line compressors opening valvelow-pressure compressors combining valveoxidizer line compressors opening valvebackup compressor opening valvehigh-pressure pressurization comb. valvelow-pressure pressurization combining valveoxidizer manifolds combining valverefilling lines purging valvefuel tank Nitrogen starting valveoxidizer tank Nitrogen starting valvemanifold pyrovalvepropellant componentsInternational Space Station, ISSlow pressureScience Power Platform, SPP


��%��#0%��#0 ��%�� -��+��%�� H��#��-0-��HW%0V%� � � %V%� � � V%�V%��V��V��

oxidizerintegrated propulsion systempneumo-hydraulic systemfuel tank Nitrogen pyrovalveoxidizer tank Nitrogen pyrovalvefuel tank starting pyrovalveoxidizer tank starting pyrovalvepropellant collection and transporthigh pressure pneumatic systempressure indicatorfuel pressure indicatorchamber pressure indicatoroxidizer pressure indicatorService Module, SMNitrogen supply systemtank bellows position indicatorpneumatic control systemcontrol systemmotion control systempropellant tankpropellant systemUniversal Docking Module, UDMFunctional Cargo Block, FGBfuel refilling system electrohydraulic valvesoxidizer refilling system electrohydraulic valveselectrohydraulic valvedual-position electrohydraulic valveelectropneumatic valvedual-position electropneumatic valve

SYMBOLS

� indicator illuminated (illuminates)� Indicator not illuminated (de-illuminates)� indicator blinking� indicator status changes momentarily when command is issued� rotate clockwise� rotate counterclockwise� rotate counterclockwise to stop� rotate clockwise to stop adjust by rotating disconnect, demate� connect, mate03:10:20 relative time (hours, minutes, seconds)� check, place the item into desired state if possible

MOTION CONTROL AND NAVIGATION SYSTEM 1—1 E 25 Oct 99

1. GENERAL INSTRUCTIONS

1.1. CREW RESPONSIBILITIES

While performing operations, the crew is responsible for the following actions:

1. Perform operations per these crew procedures and MCC instructions (comm passes or radiograms), inaccordance with the crew functional responsibilities and current status of the onboard systems.

2. Monitor systems operation per these crew procedures and MCC instructions.

3. Prior to operations, perform indicator checks on the control panels to be used.

4. Record actual time spent performing operations.

5. Report to MCC completed operations and any system problems at earliest available comm pass.

6. When there is a deviation from nominal systems operation, not documented in these crew procedures, crewis responsible for the following actions:

- record the time when the deviation (malfunction) was detected;- record the nature of the deviation (malfunction);

- Report to MCC at earliest available comm pass.

7. When working with hardware (panels, cables, etc.) equipped with protective caps and covers:- remove caps and covers before operations;- re-install caps and covers after operations.

1.2. SAFETY PRECAUTIONS

To ensure nominal systems operation and crew safety, the crew is responsible for the following actions:- when working with the system, use only hardware, tools, and protective devices designated by these crew

procedures or by MCC;- upon detection of an off-nominal situation, not documented in these crew procedures, the crew is

responsible for the following actions:- stop working with the system;- record time when the off-nominal situation was detected;- record the nature of the off-nominal situation;- report to MCC at earliest available comm pass.


2. �� RS LAPTOP

2.1. BRINGING UP �� MENU

�� summary menu can be brought up from any display that has systems navigation menu.

RS Laptop Homepage:SM

sel �� menu appears

�� standard menu icons

Icons to access �� subsystemsdisplays

Oval-shaped icons bring up systemcontrol windows (commands andprocedures)

Icons to bring up technical supportdisplays for the system(used only per MCC instructions)

2.2 NAVIGATION TO �� DISPLAYS

Menu icons are used to navigate to �� subsystem displays

�� main display;

– maneuver;

� ��

� ��

– GIVUS;

� �� (ORT-modified);

� ��

– stars;

– sun sensor;


–infrared horizon sensors;

– magnetometer;

– navigation;

� ��

–US CMG desaturation;

– KURS-P;

– structure.


3. ��

3.1. REBOOST

NOTE

Secure loose equipment prior to reboost.

3.1.1. Reboost using SM "�

Reboost process is monitored from SM:GNCP:Reboost display

RS Laptop 1. SM:GNCP:Reboost

�pulse – 10 min 2. � ‘�� ’ (In Attitude (�� general readiness))� !��"#$�%& "#$'"% ��(’ (SM reboost engine 1 cover open)� !)�� " �"*��(’ (Ready for ��( activation)

�pulse = TBD


3.1.2. Reboost using Progress "�� (Combined Propulsion System) �#� (Approachand Attitude Control Thrusters)

Reboost process is monitored from SM:GNCP:Reboost display

RS Laptop 1. SM:GNCP:Reboost

�pulse – 10 min 2. � ‘1st Manifold A55 Readiness’� ‘��’ (common)

�pulse = TBD


3.2. DOCKING, UNDOCKING, REDOCKING

3.2.1. Soyuz docking with SM

3.2.1.1. Establishing communication with Soyuz

RS Laptop SM:�&T:STTS1. cmd: U_ONUK2D(S)

� +�, ��+-.�� Execute

2. pb CHANNEL 3 � Press� � CHANNEL 3

3. Press and hold push-to-talk buttonComm Panel � XMIT 3

NOTE

1. Use push-to-talk button for VHF2 simplex, do not use pb XMIT 2. Press and hold push-to-talk button to transmit information

(� XMIT 3) 3. Release push-to-talk button to listen to information (� XMIT 3)

For communication from the modules

C A U T I O N

Select mode on Comm Panel-3 for comm on Channel 1and on Comm Panel-2 for comm on Channel 2

CommPanel 2(3) 4. pb CHANNEL 3� Press

� � CHANNEL 3

After end of communicationRS Laptop SM:�&T:STTS

1. cmd: U_OFUK2D(S)� � �, ��+-.��

ExecuteCommPanel(All) 2. pb CHANNEL 3� Release

� � CHANNEL 3 � � XMIT 3


3.2.1.2. Preparation for docking

1. � No foreign objects in �� / � � �� hatch areas

2. Secure loose objects

3. Ensure access to connectors for possible need to disconnect cables in the hatches

4. � RS Laptop — On

3.2.1.3. Rendezvous monitoring

NOTE

1. Rendezvous is automatically performed by +�

2. Rendezvous program is monitored fromSM:GNCP:Kurs-P:Details display

RS Laptop 1. SM:GNCP:Kurs-P:Details

On MCC GO:

T1 (Kurs-P On)

- �Full Operation Mode)

T3 (Kurs-P Off)

0 �Test Inhibit)

1 �Final Approach and Dock Enabled)

2 �Solar Array Initial Position 1)

T9 (Mechanical Capture)


RS Laptop SM:GNCP:Kurs-P� ‘��’ (In Attitude)

( 00:00:00�

3�*4"�56*&"�(Half-Set)

�4#��3 1(Kurs-P 1)

��7&* ��(SM Port)

�� (AssemblyCompartment)

��&8%5 #��$ �66�#��4#$(Equipment Operation Mode)

&��(Test)

00:03:00 � �� (�� "�56*&"�� 4#�� (1st Kurs Set Ready)

�3#��&#"� �� #��%#��$9 6��&�:%�*(Full Operation Mode Test)

3#��&.&��(Done)

��&8%5 #��$ �66�#��4#$(Equipment Operation Mode)

�#4��9 6�%�"(Circular Search)


RS Laptop - SM:GNCP:Kurs-P� �&8%5 #��$ �66�#��4#$ ; �&"��#�$9 6�%�" (Equip. Op. Mode = Sector Search)� �&8%5 #��$ 3� 46#��*&�%� �66�#��4#�9 ; ��*%8&�%& �� 4#��3 �� (Equipment Control Software Operation Mode = Rendezvous by SM Kurs-P)� �&8%5 #��$ �66�#��4#$ ; �%��* ��*%<%� :&*% (Equipment Operation Mode = Target Acquired)Monitor:

��*�� ; (Range = )�"�#�� ; (Velocity = )

If range � 10000 m

Monitor �&8%5 #��$ �66�#��4#$ ; ��=�� (Equipment Operation Mode = Capture)Visually monitor activation of lights

T8 Locking � (Solar Arrays) in Initial Postion 1 (for docking)

RS Laptop SM:EPS:SOSB� ‘�&8%5’ = ‘��=(’ (Mode = Initial1)

On MCC GO:TV survey (per radiogram)

RS Laptop 1 SM:GNCP:Kurs-P� �&8%5 #��$ 3� 46#��*&�%� �66�#��4#�9 ;��7#&'&�%& 6#%<�*%��%� �� 4#��3 �� (Equipment Control Software Operation Mode =Final Approach and Dock by SM Kurs-P Enabled)

On MCC GO:Go to �� (Descent module)

RS Laptop 2 SM:GNCP:Kurs-P� �&8%5 #��$ 3� 46#��*&�%� �66�#��4#�9 ; �:&6"� (Equipment Control Software Operation Mode = Docking Mechanism Engaged)

RS Laptop SM:GNCP:Main

��&8%5 �� (RS �� Mode)

��.%"��#�$9 #&8%5(Indicator Mode)


3.2.2. Soyuz rendezvous and docking with FGB

3.2.2.1. Establishing communication with Soyuz

RS Laptop SM:�&T:STTS1. cmd: U_ONUK2D(S)

� +�, ��+-.�� Execute

2. pb CHANNEL 3� PressComm Panel � � CHANNEL 3�� 3. Press and hold push-to-talk buttonComm Panel � XMIT 3

NOTE

1. Use push-to-talk button for VHF2 simplex, do not use pb XMIT2. Press and hold push-to-talk button to transmit information

(�XMIT 3)3. Release push-to-talk button to listen to information (� XMIT 3)


C A U T I O N

Select mode on Comm Panel-3 for comm on Channel 1and on Comm Panel-2 for comm on Channel 2

CommPanel 2(3) 4. pb CHANNEL 3� Press

� � CHANNEL 3

After end of communicationRS Laptop SM:�&T:STTS

1. cmd: U_OFUK2D(S)� � �, ��+-.��

ExecuteCommPanel(All) 2. pb CHANNEL 3� Release



5. � No foreign objects in 3#� � �/ � � �� hatch areas






NOTE


2. Rendezvous program is monitored fromSM:GNCP:Kurs-P:Details display


On MCC GO:

T1. (SM Kurs-P On)

T1. (FGB Kurs-P On)


T3. (Kurs-P Off)

0 �Test Inhibit)





RS Laptop SM:GNCP:Kurs-P� ‘��’

( 00:00:00 � 3�*4"�56*&"� (Half-Set) = �4#��3( (Kurs-P1)� �7&* �� (SM Port) = �& �$�#�� (Not selected)� �&8%5 #��$ �66�#��4#$ ; &�� (Equipment Operation Mode = Test)

00:03:00 � ‘�� (�� "�56*&"�� 4#��’ (1st Kurs Set Ready)� 3#��&#"� �� #��%#��$9 6��&�:%�* = 3#��&.&�� (Full Operation ModeTest = Complete)� �&8%5 #��$ �66�#��4#$ ; �#4��9 6�%�" (Equipment Operation Mode = Circular Search)

RS Laptop - SM:GNCP:Kurs-P� �&8%5 #��$ �66�#��4#$ ; �&"��#�$9 6�%�" (Equipment Operation Mode = SectorSearch)� �&8%5 #��$ 3� 46#��*&�%� �66�#��4#�9 ; ��*%8&�%& �� 4#��3 �� (Equipment Control Software Operation Mode = Rendezvous by SM Kurs-P)� �&8%5 #��$ �66�#��4#$ ; �%��* ��*%<%� :&*% (Equipment Operation Mode = Target Acquired)Monitor:

��*�� ; (Range = )�"�#�� ; (Velocity = )





RS Laptop SM:EPS:SOSB� ‘Mode’ = ‘Init. Pos. 1’

RS Laptop 1 SM:GNCP:Kurs-P� �&8%5 #��$ 3� 46#��*&�%� �66�#��4#�9 ;

��7#&'&�%& 6#%<�*%��%� �� 4#��3 �� (Equipment Control Software Operation Mode = Final Approach and Dock by SM Kurs-P Enabled)



��&8%5 �� (RS GNC Mode)

��.%"��#�$9 #&8%5(Indicator Mode)


3.2.3. Progress rendezvous and docking with SM


1. � No foreign objects in �� / � � �� hatch areas





NOTE


2. Rendezvous program is monitored fromSM:GNCP:Kurs-P:Details


On MCC GO:

T1�� (SM Kurs-P On)


T3. (Kurs-P Off)

0 �Test Inhibit)






( 00:00:00 � 3�*4"�56*&"� ; �4#��3( (Half-Set = Kurs-P1)� �7&* �� ; �� (SM Port = Assembly Compartment)� �&8%5 #��$ �66�#��4#$ ; &�� (Equipment Operation Mode = Test)

00:03:00 � ‘�� (�� "�56*&"�� 4#��’ (1st Kurs Set Ready)� 3#��&#"� �� #��%#��$9 6��&�:%�* = 3#��&.&�� (Full Operation ModeTest = Complete)� �&8%5 #��$ �66�#��4#$ ; �#4��9 6�%�" (Equipment Operation Mode = Circular Search)


��*�� ; (Range = )�"�#�� ; (Velocity = )





RS Laptop SM:EPS:SOSB� ‘Mode’ = ‘Init. Ps. 1’



On MCC GO:Proceed to TORU operationsOperate per TORU procedures

On MCC GO:Go to �� (Descent Module)



��&8%5 �� RS GNC Mode

��.%"��#�$9 #&8%5(Indicator Mode)


3.2.4. Progress rendezvous and docking with FGB


1. � No foreign objects in 3#� � �/ � � �� hatch areas





NOTE


2. Rendezvous program is monitored fromSM:GNCP:Kurs-P:Details


On MCC GO:

T1 (SM Kurs-P On)

T1 (FGB Kurs-P On)


T3. (Kurs-P Off)

0 �Test Inhibit)






( 00:00:00 � 3�*4"�56*&"� ; �4#��3( (Half-Set = Kurs-P1)� �7&* �� ; �� (SM Port = Assembly Compartment)� �&8%5 #��$ �66�#��4#$ ; &�� (Equipment Operation Mode = Test)

00:03:00 � ‘�� (�� "�56*&"�� 4#��’ (1st Kurs Set Ready)� 3#��&#"� �� #��%#��$9 6��&�:%�* = 3#��&.&�� (Full Operation ModeTest = Done)� �&8%5 #��$ �66�#��4#$ ; �#4��9 6�%�" (Equipment Operation Mode = Circular Search)


��*�� ; (Range = )�"�#�� ; (Velocity = )





RS Laptop SM:EPS:SOSB� ‘Mode’ = ‘Init. Pos. 1’



On MCC GO:Proceed to TORU operationsOperate per TORU procedures

On MCC GO:Go to �� (Descent Module)



��&8%5 �� RS GNC Mode

��.%"��#�$9 #&8%5(Indicator Mode)


3.2.5. Rendezvous and docking with Orbiter

3.2.5.1. Establishing communication

RS Laptop SM:C&T:STTS1. cmd: U_ONUK2D

� +�, ��+-.Execute

2. pb CHANNEL 3� Press� � CHANNEL 3

�� 3. Press and hold push-to-talk buttonComm Panel � XMIT 3

NOTE

1. Use push-to-talk button for VHF2 simplex, do not use pb XMIT2. Press and hold push-to-talk button to transmit information (�

XMIT 3)3. Release push-to-talk button to listen to information (� XMIT 3)


C A U T I O N

Select mode on Comm Panel-3 for comm on Channel andon Comm Panel-2 for comm on Channel 2

Comm Panel 2(3)4. pb CHANNEL 3� Press� � CHANNEL 3

After end of communicationRS Laptop SM:C&T:STTS

1. cmd: U_OFUK2D(S)� � �, ��+-.��

ExecuteAll Comm Panels 2. pb CHANNEL 3� Release



Verify no foreign objects in � � �� hatch areaSecure loose objectsEnsure access to connectors for possible need to disconnect cables in the hatchesVerify �+� (Pressure Equalization Valve)



Ti = _________

-B - 01:20:00 = _________ range ~ 76 km

Expect call from Orbiter

* If comm not established before -B X!) min: ** go to �YZ�-+1[ �"1 -�#$Y "#�1 �+[$1 (COMM FAILURE RESPONSE) ** (go to p. 3-5 step 3.1) *

Monitoring lightsLocking �0 in InitialVerify attitudeMonitor gyrodine desaturationVideo survey (if needed)Monitor Indicator Mode

3.3. SPINNING UP GYRODINES

TBD

3.4. MODE TRANSITIONS

TBD

3.4.1. Transitioning to mode �� (Desaturation using attitude controlthrusters)

TBD

3.4.2. Initiating transition from RS Laptop

TBD

3.5. MONITORING MODE EXECUTION

TBD


4. ��

4.1. RS �� ATTITUDE CONTROL HANDOVER TO USOS

TBD

4.2. RS �� ATTITUDE CONTROL TAKEOVER FROM USOS

TBD


5. VISUAL OPTICAL DEVICES

5.1. WIDE ANGLE VERTICAL SIGHT �� !

This device is used for the observation of space within the hemisphere, attitude monitoring (yaw, pitch, roll),visual search for set reference points, and observation of stars of up to +1.0 magnitude.

5.1.1. TECHNICAL PARAMETERS

Screen channel viewing field, degs 185-190Screen diameter, mm 144Eyepiece channel viewing field, degs 185-190Eyepiece channel magnification, times 0.55-0.65Exact vertical viewing field:

in radial direction, degs 20in tangential direction, degs 5

Vertical build error (instrumentation):in screen channel, degs �1in eyepiece channel, min �10in exact vertical system, min �3

Yaw build error (instrumentation):in screen channel, degs �2in screen channel, min �10

Angular dimensions of grid concentric circles:+> +��(?�(/ @ABC 140, 150, 160+> +��(?�-/ @ABC 140, 160

Voltage, V 23-34Power consumption, W �12

NOTE

When working with an attitude of small angular dimensions,DECFGHH +> +��(I Spares kit magnifier into the mountingsocket on screen frame.


5.1.2. EXTERNAL VIEW

5.1.3. INITIAL STATE

JK 3��+) �) �� LGMN KGONHDBPF �+Q�, �RSS

CT U��,V� �COMAAE�AWAJDAOA �U�� XOMAAE

CT 3��+) >��,Q �� (yaw scale backlight) �+Q�, �RSS

CT ++��+Q+�� Y��Z +)� ��,� �A[GOF \AMFDOGH DEJ]F�^]FJ]F �+Q+�� R]FJ]F

Screen rotation locking screw �_��`�V (Lock)aGLJ 3��+) �) �� LGMN KGONHHDBPF H^ONDEB COMATProtective cover screw

5.1.4. SETUP

Remove COMAT SM^L CT U��,V� �COMAAE�AWAJDAOA / place into hole near screw 20 (once during activaiton)Install required screen

33��-( CT +> + (wide angle sight) � On+> + CT 3��+) >��,Q �� (yaw scale backlight) � +�, �RE

� 3��+) >��,Q �� (yaw scale backlight)IEJ]F �� (yaw angle) (per radiogram)Lock screen into position with locking screw

��

��

��

�

�

�

�

�

�

�

�

�

��

��

��

��

��

��

��

��

1 - Replaceable screens:+> +��(?�(/ +> +��(?�-/+> +��(?�?/ +> +��(?�I

2 - Screen yaw scale? � CT 3��+) >��,Q �� Yaw

Scale Backlight)4 - backup CT 3��+) >��,Q

��5 - Screen rotation locking screw6 - Eyepiece1 � CT U��,V� �COMAAE�eyepiece)8 - Eyepiece yaw setting knobb � CT ++��+Q+�� Y��Z

+)� ��,� �c[GOF \AMFDOGH DEJ]F�output)

(d � aGLJ 3��+) >��,Q �� Yaw

Scale Backlight) holder(( GE@ (2 � JK 3��+) �) �� LGMN

backlight)12 – Protective cover screw13 and 17 – control knob 3��+)

�) �� LGMN KGONHDBPF (I � aGLJ H^ONDEB COMAT 3��+)

�) �� LGMN KGONHDBPF 15 – Mark movement knob16 – Screw with chain19 – Lamps from ��3 (Spares kit)20 - Screw


CT U��,V� �COMAAE�AWAJDAOA � ��,V� �AWAJDAOA �to use eyepiece)CT ++��+Q+�� Y��Z +)� ��,� �A[GOF \AMFDOGH DEJ]F�^]FJ]F � ++�� eEJ]F (to use exact vertical)JK 3��+) �) �� LGMN KGONHDBPF � ON (to use mark)

5.1.5. VIEWING FIELDS

5.1.6. CLOSEOUT OPERATIONS

+> + (wide angle sight) � ��f �eEDFDGH

33��-( CT +> + � Off

ORBITAL ATTITUDE-Y axis towards the Earthcenter- X axis towards flightvector�� (yaw angle) - 0

�� (yaw angle) – 210

-Z axis towards the Earthcenter-X axis towards flightvector

+Z axis towards the Earthcenter-X axis towards flight

�

��

��

� ��

��

�

� ��

��

�

��

��


5.1.7. OFF-NOMINAL SITUATIONS

1. NO SCALE IMAGE UPON SCALE BACKLIGHT ACTIVATION� Heading scale

backup CT 3��+) >��,Q �� (yaw scale backlight) � +�, �RE � yaw scale

* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *� Yaw scale

Replace lamp with a new one from Spares kit* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *

2. NO MARK IMAGE UPON PUSHBUTTON 3��+) �) �� (MARK BACKLIGHT) ACTIVATION� Mark

aGLJ 3��+) �) �� LGMN KGONHDBPF H^ONDEB COMAT � into other secured position� mark

* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *� Mark

Replace lamp frame with a new one from Spares kit* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *


5.2. PILOT SIGHT ��$" �%#&�

Pilot sight is designed to determine direction to observed reference points relative to the station coordinatesystem for the following purposes:- geographical reference of observed terrestrial objects;- to determine direction vector to controlled and uncontrolled objects and measure their angular sizes.


Sight viewing field, degs 20Line of sight pitch and roll rotation angle, degs �30Grid rotation angle range, degs 0-360Grid circular scale graduation, degs 2Rotation counter scale graduation, degs 1Moving scale graduation, degs 5Resolution, sec 5Optical transmission factor 0.7Attenuator filters, times 10 and 100Power consumption, W 15

Sight continuous operation time is 5 hours with subsequent 30 min interval.

Pilot sight is a collimator type sight.

Components:optical unit;backlight lamp holder;housing.

The sight is rotated 30 degrees by hand around �� pitch) and �+ �roll) axes.�+ restraint �� restraint) is used to lock the instrument into position if rotated about �+ �� axis.To rotate grid, turn grid adjustment ringReadings are taken according to grid scaleAttenuator filters are used to observe bright objects.Install filters into guide grooves, holding them by knurled surface.


5.2.3. VIEWING FIELDS

5.2.4. SETUP

1. Install sight on window #8Secure with fastening screws

2. ConnectoM f2Idg(d ^S cable (1��1dg 2-1d��I12d �|� connectoM f2Idg?d +3�-

ConnectoM f2I0g(d ^S cable (1��(dg 2-(d��I12d �|� connectoM f2I0g(dof cable (1��(dg 2-(d��?h(d �F^ 33�-21)

ConnectoM f-0(g?d ^S cable (1��?dg 2-?d��b?d �|� connectoM f-0(gI( +3�-

ConnectoM f-0dg?d ^S cable (1��?dg 2-?d��b?d �|� connectoM f-0dg?d��--�(

3. Install light filters (if required)

��

��

��

��

�

� �

�

� �

� �

� �


5.2.5. INSTRUMENT �"�� #$�� CORRECTION FROM PILOT SIGHT)

1. Select 2 stars on MCC GO

2. Input star coordinates in RS Laptop (TBD)

3. eEDFDGFA �� correction mode from Pilot Sight (TBD)

33��-( 4. sw +�� 3�,� � � On

+3�- 5. sw � On� grid backlight

Choose optimal grid brightness by rotating brightness control knob�� MACFMGDEF i pull and �+ MACFMGDEF i pull and

6. Locate set reference point (1st star) by rotating the sightAlign reference point with the sight axis of the instrument

+��( pb Pilot Sight measurement � Press

7. Locate set reference point (2nd star) by rotating the sightAlign reference point with the sight axis of the instrument

+��( pb Pilot Sight measurement� Press

8. Monitor �� correction from Pilot Sight via RS Laptop (TBD)


1. XAO]MA �� MACFMGDEFXAO]MA �+ MACFMGDEF

+3�- sw � Off� grid backlight

33��-( 2. sw +�� 3�,� � � Off

3. Remove light filters (if installed)

On MCC GO 4. ConnectoM f2Idg(d ^S Oable (1��1dg 2-1d��I12d �|� from connectoM f2Idg?d +3�-

ConnectoM f2I0g(d ^S Oable (1��(dg 2-(d��I12d �|� from connectoM f2I0g(dof cable (1��(dg 2-(d��?h(d �SM^L 33�-21)

ConnectoM f-0(g?d ^S Oable (1��?dg 2-?d��b?d �|� from connector f-0(gI( +3�-

ConnectoM f-0dg?d ^S Oable (1��?dg 2-?d��b?d �|� from connectoM f-0dg?d��--�(


5. Remove sight from window # 8Stow into nominal location


1. No grid backlight

33��-( 1. � sw +�� 3�,� � � On+3�- � sw � On

� grid backlight lamp

+3�- 2. sw � OffUnscrew lamp holder by holding and pressing the restraint control

Screw in the new lamp holder by holding and pressing the restraint control (from Spares kit)

+3�- 3. sw � On� � grid backlight


5.3. PUMA PORTABLE ZOOM VIEWFINDER

The Puma Portable Zoom Viewfinder is used to view remote objects and determine their angular position in theSM coordinate system in order to:- provide geographical reference of observed terrestrial objects;- determine target vector in a specified coordinate system.


Magnification range, times 1.5---15Viewing field size at 1.5 times magnification, degs 40Viewing field size at 15 times magnification, degs 4Dioptric adjustment range, diopters � 4Optical transmission factor 0.35Resolution in viewing field center at =(.5 times magnification, sec 30Goniometrical grid rotation angles (yaw), degs 0---90Grid rotation (yaw) scale graduation, degs 2Instrument roll and pitch rotation angle range, degs � 22Roll and pitch scales graduation, degs 2Sight length, mm 320

Puma Portable Zoom Viewfinder is a monocular spyglass which includes:- lens;- eyepiece;- quick removal fixture.

A soft damper protects the window from damage.Goniometrical grid adjustment ring is used to rotate goniometrical grid.Roll and pitch rotation locking screws are used to lock the device in required roll (pitch) angular position.Readings are taken using roll and pitch rotation scales.Magnification control is used for smooth magnification adjustment ().Eyepiece dioptric adjustment ring () is used to improve the image sharpness for a specific operator.



1. Goniometrical grid backlight brightness control knob2. Window mounting guide3. ��O^EEAOF^M �>- 4. Quick removal fixture5. Angular coordinates ��CAEC^MC P^]CDEB6. Eye-shade7, 16. Eyepiece8. Backlight lamp protective cap9. Polyamide thread10, 20. Lens11.Removable soft damper12.Lens cover


13.Grid backlight activation switch14.j^TAM OÊEAOF^M �>( 15.Roll rotation locking screw17.Pitch rotation locking screw18.Magnification adjustment knob19.Magnification scale21.Eyepiece dioptric adjustment ring22.Goniometrical grid rotation ring with scale (yaw)23.Pitch rotation scale24. Roll rotation scale

5.3.3. VIEWING FIELD

Viewing field (degs)For each ring zone

Magni-fication,times

View-finder 1 2 3

1.5 40 30 20 103 20 15 10 56 10 7.5 5 2.512 5 4 2.5 ~1.315 4 3 2 1

5.3.4. SETUP

1. Install Puma onto window #6Secure device with fastening screws

2. kÊEAOF^M f2Idg(d ^S OGKHA(1��1dg 2-1d��I12d� OÊEAOF^M >( 3+3 PumakÊEAOF^M f2I0g(d ^S OGKHA (1��(dg 2-(d��I12d� OÊEAOF^M f2I0g(d of cable(1��(dg 2-(d��?h(d �to 33�-21)CÊEAOF^M f-0(g?d ^S OGKHA (1��?dg 2-?d��b?d� OÊEAOF^M >- 3+3 PumaCÊEAOF^M f-0dg?d ^S OGKHA (1��?dg 2-?d��b?d� OÊEAOF^M f-0dg?d of ��--�(

�

�

�

��


5.3.5. INSTRUMENT OPERATION (#$�� CORRECTION FROM PUMA)

1. Select two stars per MCC instructions

2. Input star coordinates in RS Laptop (TBD)

3. Initiate �� correction from Puma mode (TBD)

Puma 4. sw � On� 3��+) �) �� BMD@ KGONHDBPF Select optimal grid backlight brightness by rotating control knobRotation locking screws � (released)Adjust grid sharpness by rotating eyepiece dioptric adjustment ringSet optimal magnification

5. Locate required reference point (1st star) by rotating viewfinder Align reference point with instrument line of sight

+��( pb ��)�)��) 3�� (Puma measurement) � Press

6. Locate required reference point (2nd star) by rotating viewfinder Align reference point with instrument line of sight

+��( pb ��)�)��) 3��(Puma measurement) � Press

RS Laptop 7. Monitor execution of �� correction from Puma via RS Laptop (TBD)


1. Pitch and roll locking screws � (tight)Puma sw � Off

� � grid backlight

On MCC GO 2. connector f2Idg(d of cable (1��1dg 2-1d��I12d connector >( 3+3 Pumaconnector f2I0g(d of cable (1��(dg 2-(d��I12d connector f2I0g(d of cable

(1��(dg 2-(d��?h(d �from 33�-21)connector f-0(g?d of cable (1��?dg 2-?d��b?d connector >- 3+3 Pumaconnector f-0dg?d of cable (1��?dg 2-?d��b?d� connector f-0dg?d of ��--�(

3. Remove viewfinder from window #6Stow in nominal location



1. NO GRID BACKLIGHT

PUMA 1. � sw � On� grid backlight lamp

PUMA 2. sw � OffReplace lamp with spare from Spares kit

PUMA 3. sw � On� � grid backlight


6. INTEGRATED PROPULSION SYSTEM ��!

Propulsion system valves abbreviations

Low pressure electropneumatic valves

Hardware name Hardware ID

Low-pressure oxidizer tank pressurization electropneumatic valve U��(

Low-pressure oxidizer tank pressurization electropneumatic valve U��-

Low-pressure fuel tank pressurization electropneumatic valve U��(

Low-pressure fuel tank pressurization electropneumatic valve U��-

High-pressure oxidizer tank pressurization electropneumatic valve U��+�(

High-pressure oxidizer tank pressurization electropneumatic valve U��+�-

High-pressure fuel tank pressurization electropneumatic valve U��+�(

High-pressure fuel tank pressurization electropneumatic valve U��+�-

Fuel pressurization and evacuation system electropneumatic valve (backup) U��+�-

Oxidizer pressurization and evacuation system electropneumatic valve (backup) U��+�-

Backup compressor fuel pressurization and evacuation system electropneumaticvalve

U��+�

Backup compressor oxidizer pressurization and evacuation systemelectropneumatic valve

U��+�

FGB fuel tanks pressurization and evacuation system electropneumatic valve U�� (

FGB fuel tanks pressurization and evacuation system electropneumatic valve U�� -

FGB oxidizer tanks pressurization and evacuation system electropneumatic valve U�� (

FGB oxidizer tanks pressurization and evacuation system electropneumatic valve U�� -

High pressure electropneumatic valves


Fuel spherical tank ramp separation electropneumatic valve U��>�

Oxidizer spherical tank ramp separation electropneumatic valve U��>�

High pressure fuel pressurization and evacuation system electropneumatic valve U��+�(

High pressure oxidizer pressurization and evacuation system electropneumaticvalve

U��+�(

Electrohydraulic valves



Low-pressure fuel tank 1 electrohydraulic valve U��(

Low-pressure fuel tank 2 electrohydraulic valve U��-

Low-pressure fuel tank 3 electrohydraulic valve U��?

Low-pressure oxidizer tank 1 electrohydraulic valve U��(

Low-pressure oxidizer tank 2 electrohydraulic valve U��-

Low-pressure oxidizer tank 3 electrohydraulic valve U��?

High-pressure fuel tank electrohydraulic valve U��+

High-pressure oxidizer tank electrohydraulic valve U��+

Oxidizer refilling system electrohydraulic valve U��(

Oxidizer refilling system electrohydraulic valve U��-

Oxidizer refilling system electrohydraulic valve U��?

Oxidizer refilling system electrohydraulic valve U��I

Oxidizer refilling system electrohydraulic valve U��h

Oxidizer refilling system electrohydraulic valve U��0



Fuel refilling system electrohydraulic valve U��(

Fuel refilling system electrohydraulic valve U��-

Fuel refilling system electrohydraulic valve U��?

Fuel refilling system electrohydraulic valve U��I

Fuel refilling system electrohydraulic valve U��h

Fuel refilling system electrohydraulic valve U��0



FGB fuel tanks 2, 3 refilling system electrohydraulic valve U�� (

FGB oxidizer tanks 2, 3 refilling system electrohydraulic valve U�� (

FGB fuel tanks 1, 4 refilling system electrohydraulic valve U�� -

FGB oxidizer tanks 1, 4 refilling system electrohydraulic valve U�� -


7. SM AND FGB PROPULSION SYSTEM

7.1. PURPOSE

�� DC JGMF ^S the Russian Segment motion control engines system and is used for the Russian Segment andISS reboost, to create control moments relative to the Russian Segment and ISS centers of mass and tocreate moments using High-pressure oxidizer tanks and UDM roll thrusters.

7.2. TECHNICAL PARAMETERS

7.2.1. �� %&'()*'+, -+.+/&%&.0

nominal internal tank volume, L ....................................................................................... 260fluid cavity volume, L........................................................................................................ 218volume of filled component in the tank, L ........................................................................ 190 --- 194volume of filled component when Tank bellows position indicator triggers, L ................ 189 --- 191total volume of filled fuel, kg:

fuel .............................................................................................................................. 304oxidizer........................................................................................................................ 556

refill amount, max, kg:fuel ............................................................................................................................. 280oxidizer........................................................................................................................ 520

Nitrogen tank internal volume (nominal), L ...................................................................... 20quantity of Nitrogen tanks ................................................................................................ 8Nitrogen working pressure, = (at t = 30� � / NBSlOL

2 ........................................................ � 230pressurization system Nitrogen margin

(at t = 15� � GE@ � refill = 205 - 210 kgf/cm2 ), kg......................................................... 37fuel supply system working pressure (nominal), kgf/cm2................................................. 19 --- 23refilling pressure in the lines, kgf/cm2, ............................................................................. 2 --- 22oxidizer and fuel input pressure, kgf/cm2:

In �� mAK^^CF AEBDEA /.............................................................................................. 13.5 --- 24.5In �� nFFDF]A OÊFM^H FPM]CFAMC / ................................................................................. 12 --- 23

components input pressure differential, kgf/cm2:In ��/........................................................................................................................... � 2In ��/ .......................................................................................................................... � 3

specific impulse, kgf/kg:��................................................................................................................................ 290.7 --- 296.7�� OÊFDE]^]C L^@A ................................................................................................ 230�� J]HCA L^@A ......................................................................................................... 180

continuous operation time, max, sec:��................................................................................................................................ 400�� ............................................................................................................................... 300

total operation time, sec:��................................................................................................................................ 2700�� ............................................................................................................................... 5000

DEFAM\GH KAFTAAE �� GOFD\GFDÊC/ LDE/ CAO........................................................................ 10


propellant components ratio in initial operation conditions:S^M �� DS � input = 17.5 atm and t = 15� � ......................................................................... 1.77 --- 1.93S^M �� DS � input = 18 atm and t = 15� �

in continuous mode..................................................................................................... 1.5 --- 2.3in pulse mode.............................................................................................................. 1.4 --- 2.3

absolute pressure in gas cavitiesOxidizer tanks and Fuel tanks during Nitrogen evacuation ........................................ > 2

�� AHAOFM^JEA]LGFDO \GH\A driving gas pressure ............................................................. 19 --- 23pressure differential, max, kgf/cm2:

between gas and fluid cavities of Oxidizer tanks and Fuel tanks ............................... � 5between fluid and gas cavities of Oxidizer tanks and Fuel tanks ............................... � 0.8

7.2.2. ��1 �� %&'()*'+, -+.+/&%&.0

Mass of filled propellant, max, kg: ................................................................................... 6120fuel (including propellant lines) ................................................................................... 3952oxidizer (including propellant lines)............................................................................. 2168

mass of pressurization system Nitrogen(at t = 15° � GE@ �refill = 235 kgf/cm2), kg.................................................................... 145

one time refill propellant volume, Lfrom SM ...................................................................................................................... 100 --- 1500to SM........................................................................................................................... 5 --- 400

quantity of intake-output cycles ...................................................................................... 30mass of guaranteed usable propellant margin, kg........................................................... 5760working pressure in Low-pressure tank, kgf/cm2 ............................................................. 23propellant components pressure during intake and output kgs/cm2................................ 5---20max propellant intake volume, L

for High-pressure tanks and Low-pressure tanks....................................................... 370for Auxiliary propellant tanks....................................................................................... 303


7.3. �� "��2�� SCHEMATIC


8. �� RS LAPTOP

8.1. CALLING �" ��

�� C]LLGMW LAE] OGE KA KM^]BPF ]J SM^L GEW @DCJHGW FPGF PGC CWCFALC K]FF^E JGEAH

RS Laptop Home page SM

sel �� LAE] GJJAGMC

Display access button

Oval-shaped icon to bring up system control window(commands)

Icons to bring up technical support displays for the system(used only per MCC instructions)

8.2. ��

RS Laptop ��o��

sel �� @DCJHGW GJJAGMC


Display elements

KMDEBC ]J �� jM^JAHHGEF L^EDF^MDEB ]EDF @DCJHGW ��o��o��

KMDEBC ]J �� L^@A @DCJHGW ��o��o�&8%5$

Nitrogen line

fuel line

oxidizer line

compressor

tank bellows position indicator

valve (when selected, valve command window appears)

Display elements status change

compressor is not powered up, Off

compressor is powered up, On

indicator is powered up, Off

indicator is powered up, On

valve is not powered up

valve is powered up, closed

valve is powered up, open

valve failed (Caution)

power problem

static data

invalid data

valve failed (Warning)


8.2.1. Propellant monitoring unit display


sel

��o��o�� @DCJHGW GJJAGMC(Propellant monitoring unit power and propellant amount in tanks checkout)

RS Laptop ��o��o��

sel�� jM^JAHHGEF LÊDF^MDEB ]EDF �O^LLGE@C OÊFM^H TDE@^T GJJAGMC

8.2.2. Modes display


sel�� L^@AC LÊDF^MDEB TDE@^T GJJAGMC


9. DYNAMIC MODES

9.1. �� 2� ��

C A U T I O N

Oxidizer line compressors opening valve, Fuel linecompressors opening valve, Backup compressoropening valve, p]AH MASDHHDEB \GH\A (/ ��? �p]AHMASDHHDEB \GH\A ? / ��I �p]AH MASDHHDEB \GH\A I / ��(�R[D@DqAM MASeHHDEB \GH\A ( /��? �R[D@DqAM MASeHHDEB\GH\A ? / ��I �R[D@DqAM MASeHHDEB \GH\A I \GH\ACDEDFDGH J^CDFD^E i ��"#$�$ (open)

9.1.1. �'()*+,-*(+ �� ') �.(*)'/0 1

C A U T I O N

This mode is incompatible with Fuel tank 1 andOxidizer tank 1 refill mode

On MCC GO verify the following valves are open and Propellant monitoring unit is powered up:without Fuel tank 1 and Oxidizer tank 1

pressurizationwith Fuel tank 1 and Oxidizer tank 1 pressurization

RS Laptop SM:MCSvlv U��(vlv U��( vlv ��(vlv ��(

RS Laptop SrorkXo+��

RS Laptop SM:MCSvlv U3��(

vlv U3��Ivlv �3��(vlv �3��(vlv U��(vlv U��(vlv ��(vlv ��(


On MCC GO when combining Manifolds 1 and 2, verify the following valves are open:RS Laptop SM:MCS

vlv ��(vlv ��-vlv ��(vlv ��-

3%��%& �� ((Fuel tank 1 Propellantmonitoring unit power)

+"* (On)

3%��%& �� ((Oxidizer tank 1 Prop.monitoring unit power)

+"* (On)


+"* (On)

3%��%& �� ((Oxidizer tank 1Propellant monitoringunit power)

+"* (On)


9.1.2. �3)4*56.*)5 �� 34 �+)*43,7 8

C A U T I O N

This mode is incompatible with Fuel tank 2 andOxidizer tank 2 refill mode

On MCC GO verify the following valves are open and Propellant monitoring unit is powered up:without Fuel tank 2 and Oxidizer tank 2

pressurizationwith Fuel tank 2 and Oxidizer tank 2 pressurization

RS Laptop SM:MCSvlv U��-vlv U��-vlv ��-vlv ��-


RS Laptop SM:MCSvlv U3��-vlv U3��?vlv �3��-vlv �3��-vlv U��-vlv U��-vlv ��-vlv ��-


On MCC GO when combining manifolds 1 and 2 verify the following valves are open:RS Laptop SM:MCS


3%��%& �� -(Fuel tank 2 Propellantmonitoring unit power)

+"* (On)

3%��%& �� -(Oxidizer tank 2 Prop.monitoring unit power)

+"* (On)


+"*(On)

3%��%& �� -(Oxidizer tank 2Propellant monitoringunit power)

+"*(On)


9.1.3. �+)'&,,*)5 �� '3)4*56.+%*3)

On MCC GO verify the following valves are closed and Propellant monitoring unit is powered down:Manifold 1 Manifold 2

RS Laptop SM:MCSvlv U3��(vlv U3��Ivlv �3��(vlv �3��(vlv U��(vlv U��(vlv ��(vlv ��(


RS Laptop SM:MCSvlv U3��-vlv U3��?vlv �3��-vlv �3��-vlv U��-vlv U��-vlv ��-vlv ��-


On MCC GO with combined Manifolds 1 and 2, verify the following valves are closed:RS Laptop SM:MCS


3%��%& �� 2(Fuel tank 2 Propellantmonitoring unit power)

��"*(Off)

3%��%& �� -(Oxidizer tank 2 Prop.

��"*(Off)


R�"*(Off)

3%��%& �� ((Oxidizer tank 1Propellant monitoring

��"*(Off)


9.1.4. Preparation 43. ��9 �� &:330% &)5*)& 1) activation

C A U T I O N

This mode is incompatible with refill modes ofapproptiate tanks

On MCC GO verify the following \GH\AC GE@ ��1 cover are open:

Selected Fuel tank 1 and Oxidizer tank 1 Selected Fuel tank 2 and Oxidizer tank 2RS Laptop SM:MCS

vlv ��(vlv ��(

RS Laptop SM:GNCP:Reboost

RS Laptop SM:MCS\H\ ��(vlv ��(


9.1.5. Preparation 43. ��8 +'%*;+%*3)

C A U T I O N

This mode is incompatible with refill modes ofapproptiate tanks

On MCC GO verify the following \GH\AC GE@ ��2 cover are open:


vlv ��-vlv ��-


RS Laptop SM:MCSvlv ��-vlv ��-


��"#$�%& "#$'"% ��-��- O^\AM ^JAE

��"#$�%& "#$'"% ��-��- O^\AM ^JAE

��"#$�%& "#$'"% ��(��( O^\AM ^JAE

��"#$�%& "#$'"% ��(��( O^\AM ^JAE


9.1.6. �3)4*56.*)5 ��9 %3 *)*%*+, -30*%*3)

On MCC GO verify the following \GH\AC GE@ ��1 cover are closed:

Selected Fuel tank 1 and Oxidizer tank 1 Selected Fuel tank 2 and Oxidizer tank 2

RS Laptop SM:MCS00:00 vlv ��(

vlv ��(

RS Laptop 00:11 SM:GNCP:Reboost

RS Laptop SM:MCS00:00 vlv ��(

vlv ��(

RS Laptop 00:11: SM:GNCP:Reboost

9.1.7. �3)4*56.*)5 ��8 %3 *)*%*+, -30*%*3)

On MCC GO verify the following \GH\AC GE@ ��- cover are closed:


00:00 vlv ��-vlv ��-


RS Laptop SM:MCS00:00 vlv ��-

vlv ��-


��"#$�%& "#$'"% ��-��- O^\AM OH^CA@

��"#$�%& "#$'"% ��-��- O^\AM OH^CA@

��"#$�%& "#$'"% ��(��( O^\AM OH^CA@

��"#$�%& "#$'"% ��(��( O^\AM OH^CA@


10. REFILLING

C A U T I O N

Oxidizer tank 1, Oxidizer tank 2, Fuel tank 1, Fueltank 2 refill modes are mutually incompatible

10.1. REFILLING 23 1 �� 4 1 USING COMPRESSOR 1, 3

C A U T I O N

This mode is incompatible with modesskÊSDB]MDEB �� Ê rGEDS^H@ (t/ sPreparation for��( nOFD\GFDÊt/ sj]MBDEB p]AH aDEACt

10.1.1. Nitrogen evacuation 4.3/ #� 9 using Compressor 1

On MCC GO verify:RS Laptop SrorkXo+��


+"*(On)

RS Laptop SM:MCSvlv U3��( — Closedvlv ��( — Closedvlv ��- — Closedvlv ��( — Closedvlv ��- — Closedvlv ��- — Closedvlv ��+- — Closedvlv �� — Openvlv ��( — Openvlv �3��( — Openvlv ��+( — Open

�3� �( —

�( —

Report to MCC ��( ; kgf/cm2


10.1.2. Nitrogen evacuation 4.3/ #�9 using Compressor 3

NOTE

This mode is used if Compressor 1 fails



+"*(On)

RS Laptop SM:MCS"* U3��( —Closed"* ��( —Closed"* ��- —Closed"* ��- —Closed"* ��( —Closed"* ��- —Closed"* ��+- —Closed"* ��+- —Closed"* �3��( —Open"* ��( —Open"* ��( —Open"* �� —Open"* ��+( —Open"* ��+( —Open

�3� �( —

�? — Report to MCC ��( ; kgf/cm2

10.1.3. Propellant transfer to 231from Progress (via 5�

RS Laptop SM:MCSReport to MCC ��( ; kgf/cm2

On MCC GO verify the following valves are open:RS Laptop SM:MCS

vlv U��( vlv ��( vlv ��-( vlv ��--


Reportto MCC

��*%<&�� 6*%�� ((propellant amount in Fuel tank 1)

"� �NB


After propellant transfer to Fuel tank 1 on MCC GO verify:RS Laptop SM:MCS

\H\ U��( — Closedvlv ��( — Closedvlv ��-( — Closedvlv ��-- — Closedvlv ��( — Closedvlv ��+( — Closedvlv ��( — Closedvlv �3��( — Closedvlv ��+( — Closed

�3� �( — ( — if tank is full)



��"*(Off)

RS Laptop SM:MCS

�( —-

�? —- Report to MCC ��( ; kgf/cm2

10.1.4. Propellant transfer to #�9 from FGB (via <=�!



vlv U��(vlv ��(vlv ��((vlv ��(-


Reportto MCC

��*%<&�� 6*%�� ((propellant amount in Fuel tank 1)

"� �NB

After propellant transfer to �( �p]AH FGEN ( on MCC GO verify:RS Laptop SM:MCS

\H\ U��1 —Closedvlv ��( —Closedvlv ��(( —Closedvlv ��(- —Closedvlv ��( —Closedvlv ��( —Closedvlv ��+( —Closedvlv ��( —Closedvlv ��+( —Closed


vlv �3��( —Closed




R�"*(Off)

RS Laptop SM:MCS

�( —-

�? —- Report to MCC ��( ; kgf/cm2

10.2. REFILLING #�8 �FUEL TANK 2) USING COMPRESSOR 1, 3

C A U T I O N

This mode is incompatible with modesskÊSDB]MDEB �� Ê rGEDS^H@ -t / sPreparationS^M ��- nOFD\GFDÊt/ sj]MBDEB p]AH aDEACt

10.2.1. Nitrogen evacuation )-'6 23�using Compressor 1



+"*(On)

RS Laptop SM:MCSvlv U3��- —Closedvlv ��( —Closedvlv ��- —Closedvlv ��( —Closedvlv ��( —Closedvlv ��- —Closedvlv ��+( —Closedvlv �� —Openvlv ��- —Openvlv �3��- —Openvlv ��+- —Open

�3� �( —

�( —

Report to MCC ��2 = kgf/cm2



NOTE

The mode is used if Compressor 1 fails



+"*(On)

RS Laptop SM:MCSvlv U3��- —Closed\H\ ��( —Closed\H\ ��- —Closed\H\ ��( —Closed\H\ ��( —Closed\H\ ��- —Closed\H\ ��- —Closed\H\ ��+- —Closed\H\ ��+( —Closed\H\ �3��- —Open\H\ ��( —Open\H\ ��2 —Open\H\ �� —Open\H\ ��+( —Open\H\ ��+- —Open

�3� �- —

�? —

Report to MCC ��- ; kgf/cm2

10.2.3. Propellant transfer to 23�from Progress (via 5�

RS Laptop SM:MCSReport to MCC ��- ; kgf/cm2


vlv U��-vlv ��-\H\ ��-(vlv ��--


Reportto MCC

��*%<&�� 6*%�� -(propellant amount in Fuel tank 2)

"� �NB



\H\ U��- —Closedvlv ��- —Closedvlv ��-( —Closedvlv ��-- —Closedvlv ��- —Closedvlv ��+- —Closedvlv ��( —Closedvlv ��+( —Closedvlv �3��2 —Closed

�3� �- —- ( — if tank is full)



��"*(Off)

RS Laptop SM:MCS

�( —-

�? —-


10.2.4. Propellant transfer to #�8 from FGB (via <=�!



vlv U��-vlv ��-vlv ��((vlv ��(-


Reportto MCC

��*%<&�� 6*%�� -(propellant amount in Fuel tank 2)

"� �NB


\H\ U��- —Closedvlv ��(( —Closedvlv ��(- —Closedvlv ��- —Closedvlv ��- —Closed


vlv ��+- —Closedvlv ��( —Closedvlv ��+( —Closedvlv �3��- —Closed

�3� �- —- ( — if tank is full)



��"*(Off)

RS Laptop SM:MCS

�( —-

�? —- Report to MCC ��- ; kgf/cm2

10.3. REFILLING #�9 ��>�?�� @ 9! USING COMPRESSOR 2, 3

C A U T I O N

This mode is incompatible with modesskÊSDB]MDEB �� Ê rGEDS^H@ (t/ sPreparation for��( nOFD\GFDÊt/ sj]MBDEB Oxidizer Lines»




+"*(On)

RS Laptop SM:MCSvlv U3��4 —Closedvlv ��( —Closedvlv ��- —Closedvlv ��? —Closedvlv ��( —Closedvlv ��- —Closedvlv ��+? —Closedvlv �3��( — Openvlv ��I —Openvlv �� —Openvlv ��+I —Open

�3� �( —

�( —



10.3.2. Nitrogen evacuation )-'6 2�1 using Compressor 3

NOTE




+"*(On)

RS Laptop SM:MCSvlv U3��4) —Closedvlv ��( —Closed\H\ ��- —Closedvlv ��? —Closedvlv ��( —Closedvlv ��- —Closedvlv ��( —Closedvlv ��+( —Closedvlv ��+? —Closedvlv �3��( —Openvlv ��I —Openvlv ��- —Openvlv �� —Openvlv ��+- —Openvlv ��+I —Open

�3� �( —

�? —


10.3.3. Propellant transfer to 2�1from Progress (via 5�



vlv U��(vlv ��(vlv ��-(vlv ��--


Reportto MCC

��*%<&�� 6*%�� -(propellant amount in Oxidizer tank 2)

"� �NB


After propellant transfer to Oxidizer tank 2 on MCC GO verify:RS Laptop SM:MCS

vlv U��( —Closedvlv ��( —Closedvlv ��-( —Closedvlv ��-- —Closedvlv ��I —Closedvlv ��+I —Closedvlv ��- —Closedvlv ��+- —Closed�vlv �3��( —Closed




��"*(Off)

RS Laptop SM:MCS

�- —

�? —


10.3.4. Propellant transfer to #�9 from FGB (via #7�



vlv U��(vlv ��(vlv ��((vlv ��(-


Reportto MCC

��*%<&�� 6*%�� ((propellant amount in Oxidizer tank 1)

"� �NB


vlvU��( —Closedvlv ��(( —Closedvlv ��(- —Closedvlv ��( —Closedvlv ��I —Closedvlv ��+I —Closed


vlv ��- —Closedvlv ��+- —Closedvlv �3��( —Closed




��"*(Off)

RS Laptop SM:MCS

�- —

�? — Report to MCC ��( ; kgf/cm2

10.4. REFILLING #�8 �OXIDIZER TANK 2) USING COMPRESSOR 2, 3

C A U T I O N

This mode is incompatible with modesskÊSDB]MDEB �� Ê rGEDS^H@ -t/ sPreparation for��( nOFD\GFDÊt/ sj]MBDEB Oxidizer Lines»

10.4.1. Nitrogen evacuation from #�8 using Compressor 2



+"*(On)

RS Laptop SM:MCSvlv U3��3 — Closedvlv ��( — Closedvlv ��- —Closedvlv ��I —Closedvlv ��( —Closedvlv ��- —Closedvlv ��+I —Closedvlv �3��- —Openvlv ��? —Openvlv �� —Openvlv ��+? —Open

�3� �- —

�( —



10.4.2. Nitrogen evacuation from #�8 using Compressor 3

NOTE




+"*(On)

RS Laptop SM:MCSvlv U3��3 —Closedvlv ��( —Closedvlv ��- —Closedvlv ��I —Closedvlv ��( —Closedvlv ��- —Closedvlv ��( —Closedvlv ��+( —Closedvlv ��+I —Closedvlv �3��- —Openvlv ��- —Openvlv ��? —Openvlv �� —Openvlv ��+- —Openvlv ��+? —Open

�3� �- —

�? — Report to MCC ��- ; kgf/cm2

10.4.3. Propellant transfer to #�8from Progress (via 5�



vlv U��-vlv ��-vlv ��-(vlv ��--


Reportto MCC


"� �NB


After propellant transfer to Oxidizer tank 2 On MCC GO verify:RS Laptop SM:MCS

\H\ U��- —Closed\H\ ��- —Closedvlv ��-( —Closedvlv ��-- —Closedvlv ��? —Closedvlv ��+? —Closedvlv ��- —Closedvlv ��+- —Closedvlv �3��- —Closed

�� 0 � — ( — if tank is full)


3%��%& �� 2(Oxidizer tank 2Propellant monitoringunit power)

��"*(Off)

RS Laptop SM:MCS

�- —


10.4.4. Propellant transfer to #�8 from FGB (via #7�



vlv U��-vlv ��-vlv ��((vlv ��(-


Reportto MCC


"� �NB



vlvU��- — Closedvlv ��(( — Closedvlv ��(- — Closedvlv ��- — Closedvlv ��? — Closedvlv ��+? — Closedvlv ��- — Closedvlv ��+- — Closedvlv �3��- — Closed

�3� �- — ( — if tank is full)



��"*(Off)

RS Laptop SM:MCS

�- —


service module motion control and navigation system · 2013. 4. 20. · universal docking module,...

Documents