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SoyCOM flight procedures

An overview of launch, inflight and landing procedures for a typical Soyuz mission as printed in the SoyCOM, as well as emergency procedures. As it is intended for trained crew, the extract is rather technical and assumes the reader knows Russian! See the SoyCOM glossary for Russian acronyms.

6. Nominal procedures

6.1. General flight program

The Soyuz manned spacecraft flight objective is:

  • 2-3 man crew and payload delivery to Mir station or ISS;
  • joint flight up to 180 days;
  • crew and payload return to the Earth;
  • return of the crew uncapable of using its nominal spacecraft from the orbital station to the ground.

The Soyuz spacecraft general flight program is shown in Fig. 1.

The Soyuz spacecraft is launched by Soyuz Launch Vehicle and injected into orbit the with the following parameters:

  • inclination: 51.6 degrees;
  • period of revolution: 88.,44 minutes;
  • maximal altitude of the orbit: 240 km;
  • minimal altitude of the orbit: 200 km.

After the spacecraft injection into orbit the module pressurization test is conducted. In the second revolution of the first flight day the following operations are accomplished: “Kurs” equipment test, ДК (Digital circuit) test, РУО (Rotation Hand Controller) test in АК (Analog circuit), accelerometer test, spacecraft solar pointing and Solar barbecue rotation.

In the third-fourth revolution two-impulse interorbital transfer maneuver is executed.

In the 17th revolution a single-impulse maneuver is executed with the test of the backup РУО Controller set in the БО Module.

In revolution 33-34 a three-impulse autonomous spacecraft approach to the orbital station is executed which ends with berthing and docking in revolution 34 at the illuminated part of the orbit.

The approach/docking procedure is mainly monitored by the ground control tracking aids.

After the spacecraft and the orbital complex are docked and the hooks are closed the joint flight is begun with the capability of executing dynamic operations using spacecraft СУД and КДУ systems including the docked cluster orbit correction, automatic and manual redocking from one docking node to another and СУД System tests.

3-4 days prior to the joint flight termination the pre-descent test of the CУД and the КДУ system is conducted. On the test results the decision is made on undocking and on descent mode selection. In revolution 15 of the pre-descent day the spacecraft/station undocking is executed with the spacecraft attitude hold so as to align its “+X” axis along the velocity vector.

In revolution 16 of the pre-descent day the nominal descent cyclogram is initiated and the Orbital Maneuver Engine retrofire impulse is executed.

The spacecraft landing in the preset area is accomplished with the descent in the first revolution of the landing day.

6.2. Preparation for launch

The pre-launch procedure starts with the Launch Vehicle installation with the spacecraft on the launch pad and ends with the launch.

Nominal preparation cycle at the launch complex is supposed to be completed in two days.

The following operations are executed at the launch complex:

  • spacecraft radio system test for the joint operation with the ground radio complex;
  • test of the onboard part of the command radio complex for the joint operation with the ground radio-command complex;
  • test of the Launch Escape Complex readiness for launch;
  • test of the onboard Launch Escape System as a part of the Launch Escape Complex;
  • all system transfer into the flight configuration;
  • spacecraft participation in the Launch Vehicle General Test.
  • monitoring telemetry parameters of the spacecraft onboard system status;
  • monitoring crew medical parameters after the spacecraft ingress;
  • БО Module oxygen pressurization up to differential pressure of 0.1 atm for its integrity test;
  • collection of launch readiness indications for the Launch Vehicle and the spacecraft;
  • entering the Launch Escape System settings according to the flight schedule;
  • Launch Vehicle/spacecraft lift off.

The spacecraft preparation for launch is conducted according to the launch complex technological plan. The crew ingress into the spacecraft at the launch pad is scheduled for 2.5 hours prior to launch (using the ingress hatch in the БО Module. After the ingress the crew:

  • conducts prelaunch inspection of the БО and СА equipment;
  • connects hoses and connectors Х3, Ш9 to the space suits;
  • switches on the suit ventilation;
  • checks up the fastening system;
  • establishes communication with the Launch Control;
  • takes the cap off the CA purification cartridge;
  • at T −2 hrs tests the СА/БО hatch door closing jointly with the launch team;
  • positions the БЧК Onboard clock, СИРТ Propellant meter and ИНК Indicator into initial status;
  • conducts checks and collection of all the equipment initial status;
  • checks the radio communication system;
  • switches on the ДСД Sensor/signalizer, checks its actuation and adjusts the indication pressure;
  • fastens itself in the seats;
  • conducts space suit pressurization test;
  • monitors system parameters, total and partial pressures air temperature and humidity in the modules;
  • writes down and transmits to the ground pressure and temperature in БО and СА.

6.3. Orbit injection

The injection to orbit phase starts with the spacecraft launch (the «Контакт подъема» – Lift Off Contact command issue) and ends with the nominal spacecraft separation from the Launch Vehicle («Контакт отделения» – Separation Contact command issue). The injection flight phase duration is 530 seconds. During the orbit injection phase all the constant operation system are switched on and also САС, СУС, КСС, and “Kvant” system are ready for operation (standby mode)in case of emergency flight abort. Apart from that in the injection phase the crew status and the spacecraft status are constantly monitored using the crew reports and telemetry data coming from the РТС system (direct transmission mode) and «Клест-М» system (TV transmission mode from the CA).

The Launch Vehicle status is monitored by means of:

  • visual status estimation within the visibility limits from the Launch Control shelter;
  • telemetry data from the Launch Vehicle;
  • crew flight procedure reports using the ПК СА display data and the Launch Vehicle control system indicators.
  • In the injection phase the crew must:
  • conduct TV transmission (Transfer to the CA TV-camera 2 at 110-130 s after Launch);
  • listen to the Launch Vehicle flight procedure data transmission;
  • monitor the ГО Aerodynamic Cap jettison;
  • monitor the KO command passing by the ИНК Indicator switching on and the indicator light status change;
  • at the acceleration termination and transfer to weightlessness switch on the wristwatch stop-Watch.

6.4. Orbital flight (maneuver)

The spacecraft orbital flight phase starts with the spacecraft separation from the Launch Vehicle Stage III (“Separation Contact” command) and ends with the initiation of the autonomous approach mode (to the orbital complex) in the “Chaika-3” СУД System.

The following operations are executed in the orbital flight phase:

  • post-injection spacecraft structure and system operability and crew status monitoring;
  • spacecraft system transfer to the initial position for approach and docking;
  • phasing orbit shaping.

After the spacecraft is separated from the Launch Vehicle on the marks of program № 4 АПВУ the radar system antennae and Solar battery panels are deployed, constant operation systems are switched on and program №1 АПВУ is started for the communication equipment control. During communication sessions the spacecraft structure and system status and operability is monitored, crew medical status monitoring is conducted, spacecraft orbit radio tracking is accomplished, flight settings are entered into the БЦВК, system operation is controlled and voice communication is conducted. The monitors the spacecraft/Launch Vehicle separation, onboard system status and operation by means of the ПК СА data and in 15-20 seconds after the separation switches off the СТД (Thermal Sensor System) isolating it from the actuation circuit.

During intervals between the dynamic operations the spacecraft is in passive rotation about “+Y” axis pointing to the Sun in order to charge up the СЭП System buffer batteries.

In the first revolution as a part of docking preparation the «ВИПШ» mode is executed (the docking mechanism rod is extended into the initial position). In the second revolution for the purpose of testing the operability of the СУД System automatic and manual control circuits as well as of the KДУ Propulsion System СУД System test № 1 is conducted, i.e. the СУД digital circuit test and РУО Attitude Hand Controller in РО АК mode. Tests are conducted on the second КДУ section. In the digital circuit test procedure the two sets of the “Kurs” equipment, the two ИКВ Sensors and a selected set of the БДУС-I Sensor Unit.

In the second revolution on the results of the module pressurization test (the oxygen supply being terminated for the test period) the crew opens the СА/БО hatch door, checks the СА + БО volume pressurization using the Vacuum Pressure Gauge, doffs the space suits, switches on the БОА unit in the БО and switches off the БОА unit in the СА, periodically pumps out condensate.

On the results of the ВИПШ mode execution, the СУД and КДУ test the decision is made about further flight program.

Phasing orbit shaping maneuvers are executed on the БЦВК double “flexible” cycles:

  • first maneuver (first and second impulses) – in revolutions 3 and 4;
  • second maneuver (third impulse) -in revolution 17.

In the first maneuver the second КДУ section propellant is used, and in the second maneuver the first КДУ section propellant is utilized.

Nominally revolutions 6-11 (22-27) are scheduled for the crew resting. In revolution 31 the crew dons the space suits, transfers to the СА, closes the СА/БО hatch door, leaves the atmosphere purification units in the БО in on position, connects hoses and connectors Х3, Ш9 of the space suits, switches on the space suit ventilation (the space suit pressurization is not tested), fastens themselves in the seats and conducts preparation for the approach to the orbital complex.

In revolution 33 on the БЦВК setting data command the autonomous approach mode is switched on.

6.5. Approach and docking

The autonomous approach phase starts in revolution 33 and ends with the spacecraft station keeping at the range of 150 m from the orbital complex.

While executing the autonomous approach mode the crew is in the СА, in space suit donned and fastened to seats. The СА/БО hatch door is closed, the КСС is in standby mode.

At the range of 400 km the “Kurs” radar rendezvous system is switched on and the system performance test is conducted.

The approach and station keeping procedure is monitored by the ГОГУ Control Group (MCC) and by the crew:

  • ГОГУ – by means of telemetry, TV and display data;
  • crew – by means of TV and display data, ВСК-4 image and the КСП and ТСЭ indicator light data.

In the radio communication zone of revolution 34 basing on the results of the approach procedure monitoring the ГОГУ gives “GO” to the crew for transfer to the berthing mode.

Nominally the spacecraft berthing is executed in automatic mode. While berthing the crew monitors visually the berthing parameters by means of TV and display data on the ВКУ device, ПК СА indications and the orbital complex image in the ВСК-4.

The crew uses the target on the orbital complex outer surface for monitoring visually the angular errors between the spacecraft and the orbital complex looking through the ВСК-4 visor.

The docking procedure starts with the contact of the rod head and the receiving cone and ends with the rod retraction up to the final position. The docking procedure is aimed at establishing rigid hermetically sealed interface and forming electrical and hydraulic communications between the spacecraft and the orbital complex.

The crew in space suits donned is in the CA and monitors the system status and the mode schedule execution.

6.6. Operations in docked configuration

The joint flight phase starts with the moment of the docking procedure termination and ends with the undocking command issue.

The following operations are accomplished in the joint flight phase:

  • spacecraft and docking interface integrity check;
  • transfer hatch opening;
  • spacecraft preservation;
  • spacecraft system monitoring in cluster (docked configuration);
  • spacecraft depreservation;
  • transfer hatch closing;
  • preparation for undocking.

6.6.1. Spacecraft and docking interface integrity check

This operation is executed after the spacecraft/orbital complex docking or after the spacecraft redocking from one docking node to another.

The crew monitors pressure in minor and greater volumes by means of the Vacuum Pressure Gauge and pressure in the CA and БО by means of the КЭИ indicator and using the ККТ, ККС and КВД БО/СУ valves on the СКГС panel. On the monitoring time interval (45-60 minutes) expiration the crew equalizes pressure between the spacecraft and station volumes using the ККТ, КВД БО/СУ and КВД СУ/ОБ valves.

6.6.2. Transfer hatch opening

The hatches are opened after the integrity (pressurization) check of the docking interface between the spacecraft and station.

The hatches in the spacecraft and in the station are opened manually. For opening the БО/СУ and СУ/ОБ hatch doors a special handle with a stopper. The stopper is controlled by means of the lever which has two positions: operational and emergency. Prior to transfer to the station the crew sets a special plug onto the КСД СУ valve.

After the transfer hatches are opened the crew transfers to the station.

6.6.3. Spacecraft preservation

The spacecraft preservation is executed in 1-2 revolutions after the hatch opening and the crew transfer to the station. The purpose of this operation is the service life saving of the spacecraft systems which are not planned to be used in the joint flight phase.

The crew executes the following main preservation operations:

  • opens or closes appropriate valves of the СКГС, СПГС, and СОГС system;
  • switches off the purification units in the БО and СА Modules;
  • organizes air circulation in the spacecraft volume by means of the ВБО and ВСА fans and the ХСА СА and ХСА БО fans;
  • lays supplementary air hoses through the open hatches for the air flow circulation from the station to the spacecraft;
  • pumps out the condensate and executes the СОТР System preservation;
  • executes the СЭП System transfer to the combined power supply mode (on the MCC instruction).

To conclude the preservation procedure the crew checks the status of indicator lights on the ТСЭ and КСП and switches off the panel and the CA illumination.

6.6.4. Spacecraft system monitoring in docked configuration

While flying in the spacecraft/station docked cluster the crew acting on the MCC instruction executes operations for the autonomous or combined power supply mode transfer, for charging the buffer and the back up battery.

The spacecraft system monitoring is accomplished either independently or on the MCC instruction. When the spacecraft system monitoring is accomplished in the cluster flight configuration the crew executes the following operations:

  • switches on the CA illumination and the panel;
  • checks up the light integrity on the ТСЭ and КСП;
  • fills in the Ф.03ТК form comparing actual parameters with their nominal values;
  • checks up the light status on the ТСЭ and КСП.

If any parameter deviates from its nominal value or if the light configuration differs from the FDF-indicated status the crew reports to the MCC.

6.6.5. Spacecraft depreservation

The spacecraft depreservation is necessary to prepare it for undocking and descent or for redocking. When preparing for undocking prior to nominal descent the depreservation is executed by the crew in the revolution 12 of the flight day.

The following depreservation operations are accomplished by the crew:

  • switching on illumination and the panel in the CA;
  • switching on the purification units in the БО and СА Modules;
  • opening/closing appropriate valves of the СКГС, СПГС, and СОГС system;
  • organizing nominal air circulation in the spacecraft volume by means of the ВБО and ВСА fans and the ХСА СА and ХСА БО fans;
  • taking away supplementary air hoses and transferring them from the spacecraft to the the station;
  • executing the СОТР System preservation and pumping out the condensate;
  • executing the СЭП System transfer to the autonomous power supply mode (on the MCC instruction);
  • checking the light status on the ТСЭ and КСП;
  • executing the БЧК Clock and the ИНК Indicator correction.

If any parameter deviates from its nominal value or if the light configuration differs from the FDF-indicated status the crew reports to the MCC.

6.6.6. Transfer hatch closing

When preparing for undocking the crew executes the transfer hatch closing in revolution 13 of the flight day. As a rule this operation is accomplished in the MCC-indicated time during communication session. In preparing for the ОБ/СУ and СУ/БО hatch door closing the crew switches on communication aids for MCC and intermodule communication and takes off the special plug from the КСД СУ valve.

There are two methods for the transfer hatch closing:

  1. Automatic closing of the ОБ/СУ hatch door and manual closing of the БО/СУ hatch door (when there is no crew onboard the station).
  2. Manual closing of the ОБ/СУ and the СУ/БО hatch doors (when there is a crew onboard the station).

To close the СУ/БО hatch door the crew checks up the rubber sealing and manually closes the ОБ/СУ hatch door until the stopper actuates. After that the crew executes manual closing of the ОБ/СУ hatch door and then closing of the БО/СУ hatch door using a special handle which is a part of the ССВП System instrument set.

When the two hatch doors are closed the crew checks up actuation of the hatch closing sensors. After the spacecraft/station hatches are closed and prior to undocking in revolution 13 the pre-undocking transfer hatch pressurization test is conducted. The crew using the ПК СА opens the КСД СУ valve and monitors pressure in the СА, БО and ОБ Modules by means of the КЭИ Indicator. When the monitor time period (30 minutes) expires the crew starts preparation for undocking.

6.6.7. Preparation for undocking

This operation is executed in revolution 14 of the flight day after the transfer hatch closing and their pressurization test.

Before the preparation for undocking the crew completes packing of the returnable equipment and dons the medical belts and the space suits.

When preparing for undocking the crew:

  • switches off the ventilator and purification units in the БО Module;
  • closes or opens appropriate valves of the СКГС, СПГС, СОГС Systems;
  • manually pumps out the condensate;
  • closes the БО protective grid;
  • switches on the air purification unit in the СА Module;
  • closes the СА/БО hatch door;
  • connects hoses and connectors of the space suits, switches on their ventilation.

The conclusive operations of the preparation for docking procedure are the space suit and the СА/БО hatch pressurization tests.

When testing the СА/БО hatch pressurization the crew closes the РПВ-1 cock and issues command for opening the КСД БО valve, then relives the БО pressure by 150 mm Hg. After that the crew monitors pressure in the СА and БО Modules for the time period of 25 minutes. If the СА pressure change is not more than for 25 mm Hg the crew opens the РПВ-1 and РПВ-2 cocks.

6.7. Undocking

The pre-descent undocking is scheduled for revolution 15 of the flight day. As a rule it is executed by the crew on the MCC instruction and under the MCC control during a communication session. Prior to undocking the crew prepares for operation the РУО Controller, the ВСК-4 Visual System switches on the tape recorder and the floodlight (when undocking in shadow) and switches on the ССВП System power. At the preset Т.РАССТЫК (T. Undock.) the crew issues command for undocking. In 3-4 minutes the crew monitors actual spacecraft/station undocking and moving from each other at the velocity of 0.12-0.15 m/s.

When concluding the post-undocking operations the crew switches off the ССВП System power.

6.8. Descent

6.8.1. Preparation for descent

When preparing for the nominal descent the crew monitors (or enters when necessary) the control setting data for the descent execution. Nominally these data are entered into the БЦВК and into the СУС System via the КРЛ Uplink. Both the MCC and the crew monitor the correctness of the data entering procedure. The crew is authorized to change the setting data only on the MCC instruction.

6.8.2. Nominal descent from orbit

The nominal descent version is the descent with the use of the single flexible cycle – descent № 1 (ГЦ + СКД + БО).

The nominal descent procedure can be subdivided into two parts:

  • descent before the module separation;
  • descent after the module separation.
6.8.2.1. Descent before module separation

From the undocking moment the spacecraft autonomous flight phase is started. In the autonomous flight phase the crew must:

  • monitor correctness of the descent setting data entering (БЦВК, СУС);
  • maintain radio communication with the ГОГУ Group;
  • monitor the onboard system performance.

When executing the nominal descent the descent program starts with the ОСК attitude establishment and ends with the СА landing in preset site within the nominal landing area.

When descending before the module separation the crew:

  • executes pre-descent system performance and status monitoring;
  • monitors automatic initiation of the descent program and automatic orbital attitude establishment;
  • checks the КДУ Propulsion System main parameters prior to the СКД Engine retrofire for the descent;
  • monitors the СКД burn and its fulfilling the retrofire impulse;
  • monitors the spacecraft main parameters after the СКД shut off;
  • monitors pressure relief from the БО by means of the КЭИ Indicator;
  • monitors preparation of the СУС System units;
  • monitors spacecraft module separation in preset time.
6.8.2.2. Descent after module separation

When executing descent after the spacecraft module separation the crew:

  • gives the “T.c.” command at the CA preset atmosphere entry time;
  • monitors the АУС automatic descent control circuit performance using «ТВ РУС» format of the ВКУ;
  • monitors deployment of the ОСП primary parachute system at the altitude of 10 km;
  • monitors the bottom shield jettison, oxygen relief from the СА stowage tank and the СА Module/environment pressure equalization;
  • monitors the ОСП parachute rope rearrangement and arming of the seat shock absorbers;
  • monitors the СА parachuting until the landing contact;

The descent trajectory after the module separation can be subdivided in three parts:

  • Extra-atmosphere part which starts at the moment of separation Т.разд. (H=145 km) and ends with formation of the “lost” velocity value V.s=25.6 m/s (H=80 km) in the СУС System automatics. Formation of this value is considered the “atmosphere reentry” moment which is accompanied by the «ПЕРЕГРУЗКА» (overload, acceleration) light illumination on the ТСЭ-2.
  • Atmosphere part which starts at the atmosphere reentry moment (V.s=25.6 m/s, H=80 km) and ends with the Primary parachute system deployment (H=10 km) which is accompanied by the «BBОД ОСП» (“Input Deploy Prime Parachute”) light illumination on the ТСЭ-5.
  • Parachuting part starting with the primary parachute system deployment (H=10 km) and ending with the landing contact when the «ПОСАДКА» (Landing) light illuminates on the ТСЭ-4.

6.9. Post-landing operations

After landing onto solid ground the crew will first of all make sure the landing has taken place and only after that jettison the parachute. Then the crew checks the position of the breathing ventilation shutters – they must be open to ensure air passage into the CA Module.

After that the crew switches on the radio and light beacons to facilitate the operations of the Search/Rescue Service teams.

Besides, after the landing the crew must switch off the CA fan, the XCA CA fan and the tape recorder. When splashing down onto water surface the crew closes the air breathing shutters and switches on the KBO Water cooling loop pump.

The crew must constantly try to establish radio contact with the ПСС Search/Rescue Service.

7. Off-nominal situations

7.1. Off-nominal situation major terms

The off-nominal (emergency) situation is a spacecraft equipment failure or an operative (non-operative) system parameter value deviation of its nominal status that could result in the nominal flight plan reconfiguration or in resorting to back up modes.

Envisaged Off-Nominal situation is a situation which results from the equipment failure described in the FDF.

Non-envisaged off-nominal situation is a situation which results from the equipment failure not described in the FDF.

7.2. Emergency and caution/warning indication

For presenting emergency and caution/warning indication to the crew the ТСЭ Electroluminescent Indicator Displays located on the ПК СА Panel are used:

  • The ТСЭ-4 contains yellow lights and is designed for the caution/warning indication display to the crew. Any ТСЭ-4 light illumination is accompanied by a continuous audio signal;
  • The ТСЭ-3 contains red lights and is designed for the emergency indication display to the crew. When any of these red lights goes on an intermittent audio signal sounds and a special red color «ЦЕНТРАЛЬНЫЙ ОГОНЬ» (Central Light) (ЦО) blinks.

The ТСЭ lights give information to the crew on the modes currently executed and on onboard system parameter deviations beyond threshold limits, the indication signals being generated by system automatics.

When a caution/warning or emergency indication appears the audio signal is switched off by pressing the «ОТКЛ ЗВУКА» (ПК-21) key. When the audio signal is switched off the ЦО Central Light goes off. The lights go off after the cause of their illumination is eliminated, except the lights: «ВЫЗОВ НА СВЯЗЬ» (Communication Call), «АВАРИЯ БЦВК» (БЦВК Failure) (ТСЭ-4) and «АВАРИЯ ДК» (Digital Circuit Failure) (ТСЭ-3) which are put off by pressing the «СБРОС АВАР. СИГНАЛА» (Emergency Indication Reset) (ПК-9) key. When an emergency or a caution/warning signal is generated again the appropriate indication actuates again.

If when the audio signal is continuous an emergency signal appears the audio signals transfers to intermittent mode.

For checking up the ТСЭ lights one of the «КОНТР.ТСЭ» (ТСЭ Check) keys on the ПК СА (ПК-11 or ПК- 23) should be pressed. For the time of this key is pressed all the ТСЭ lights are constantly illuminated The check mode is accompanied by an intermittent audio signal and the ЦО blinking.

The ТСЭ Check mode duration must not exceed 30 seconds.

When the «КОНТР. ТСЭ» (ПК-11 or ПК-23) key is released the ЦО goes off, the audio signal stops sounding and the ТСЭ lights resume their previous status.

7.3. Depressurization

In this section off-nominal situations associated with the СА, БО and ПО module depressurization as well as the crew activities in these situations are treated conformably to the following flight phases:

  • orbit injection and the initial part of the autonomous flight;
  • autonomous flight.

The “Available Time” term is used to denote the actual time at the crew’s disposal for the survival operation execution in case of depressurization.

The lowest rated pressure level in habitable modules is assumed to be 400 mm Hg (i.e. the actuation pressure of the KCC System’s “Argus” Sensor).

The following aids for depressurization detection and for the pressure fall rate measurement are used:

  • the pressure sensors in the СА, БО and ПО Modules which send their information to the ВКУ Display;
  • the MB Vacuum Pressure Gauge for measuring pressure in the БО or in the СА + БО Volume (when the СА/БО hatch is open);
  • the ДСД Pressure Caution/Warning Sensor;
  • the КСС System’s “Argus” pressure sensor.

In the orbit injection phase and in the initial part of the autonomous flight the crew is in the СА, the СА/БО hatch is closed, the КСС System is in the ready-to-operation mode (the space suits are donned, the helmet glasses are lowered, the gloves donned, the КСС Automatic Equipment is armed), the РПВ-1, -2 cocks are open, hoses connected to the space suits, the space suits fans are on, the ПБК toggle switch is in OFF position.

In case of the СА depressurization the crew estimates the available time judging by the pressure fall rate, switches the ПБК toggle switch into the ON position and executes descent in the second revolution.

In case of the БО depressurization the crew executes the descent ahead of time in revolution 3 or 17-19 with the БО separation.

In case of the ПО depressurization the descent ahead of time is executed in revolution 2 or 3.

In the autonomous flight the СА/БО hatch is open, the crew may be in any of the habitable modules (СА or БО), the КСС System is in the standby mode, the КСС automatic equipment is not armed, the ПБК toggle switch is in OFF position. The crew periodically checks the module pressurization using the ВКУ display and the МВ Vacuum Pressure Gauge.

In case of the united module volume (СА + БО) depressurization the crew dons the space suits, transfers to the СА, closes the СА/БО hatch, connects the space suit hoses and connectors, dons the gloves, closes the helmets, switches on the space suit ventilation, arms the АКСС automatic equipment (by issuing the «АВТОМАТ КСС» (Automat Survival Aid Complex) command from the КСП-П (Ф-3), opens the РПВ-1, -2 cocks and determines which of the two modules is not integer:

  • if the СА is depressurized the crew switches the ПБК toggle switch to ON and executes the descent ahead of time;
  • if the БО is depressurized the crew executes the descent ahead of time;
  • if the ПО is depressurized the crew executes either the descent ahead of time or the urgent descent.

In the autonomous approach, berthing and docking phase the СА/БО hatch is closed. The crew is seated in the СА with the suits donned, the КСС System is in the standby mode (the helmet glasses are lifted, the gloves are donned).

In case of the СА or the ПО depressurization the crew terminates the approach mode, transfers the КСС System to the ready-for-operation mode, determines the available time and executes either the descent ahead of time or the urgent descent.

In case of the БО depressurization the crew terminates the approach mode and executes the descent ahead of time.

7.4. Fire

The following are the fire indications:

  • burning odour;
  • smoke;
  • flame.

Fire on launch pad

If the crew detects a fire indication in the СА after the ingress into the spacecraft at the launch pad the crew immediately reports to the Launch Control and closes the space suit helmets. The launch is canceled. The ground personnel switches off the spacecraft power, the БО pressure is relieved (after the БО is oxygen-pressurized), the crew transfers to the БО, opens the БО ingress hatch jointly with the ground personnel and leaves the spacecraft.

In case of fire in the БО the spacecraft power is switched off. The launch is canceled. The crew stays in the СА and is stanby for the Launch Control instructions (The САС Launch Escape System actuation is possible).

In case of fire indication detection in the СА in the injection active part the crew reports to the ground immediately. Using the КРЛ System the «Спасение» (Rescue) command is issued and the САС System is actuated.

In case of fire in the БО the crew after the injection switches off the equipment operating in the БО, on the ground instruction relieves the БО pressure and executes the descent ahead of time.

Fire in autonomous flight

If the fire indications are detected during the autonomous flight the crew switches off the onboard equipment in order to localize the fire source and finds out the fire module and spot. If the detected fire source is in the БО Module and the crew fails to extinguish it by switching off the equipment, then the crew transfers to the СА, switches on the СА atmosphere purification units, dons the space suits, transfers the КСС System to the Ready-for-operation mode (by issuing the «АВТОМАТ КСС» command from the КСП-П Ф -3), closes the СА/БО hatch door, depressurizes and separates the БО Module.

In case of the СА overfilling with smoke the crew after the space suit pressurization test depending on how it feels is authorized to make a decision on the urgent descent with the СА compulsory depressurization.

If the fire source is detected in the СА and the crew fails to extinguish it by switching off the equipment, then the crew dons the space suits in the БО, transfers to the СА, checks the space suit pressurization and transfers the КСС System to the Ready-for-operation mode (by issuing the «АВТОМАТ КСС» command from the КСП-П Ф-3). To kill the fire the crew depressurizes the СА. Then depending on the time available the descent ahead of time or the urgent descent is executed.

7.5. Emergency descent from orbit

In the Soyuz spacecraft 4 urgent descent types are described:

1. «ДК + Пр.5 + АУС» Descent

The «ДК + Пр.5 + АУС» Descent is described in the Nominal Modes book (page 47). This descent is executed after the spacecraft injection into orbit in case of the СА or the ПО depressurization. In this case the urgent descent cyclogram is initiated either in revolution 1 with landing in revolution 2 or in revolution 2 with landing in revolution 3.

The descent is executed in the reduced descent program – Пр. №5 and:

  • the crew initiates the reduced program by issuing the РУС-2 «ПР.5» command using the РУС Handle at the Т.Пр.5 moment (Form 14);
  • the ОСК orbital attitude is established using the digital circuit (БЦВК) and the ИКВ Sensor;
  • the crew uses the ПК СА for the БО separation;
  • the СКД Engine is configured for ignition by the Пр. №5 program marks;
  • the СКД Engine is ignited automatically in 33 minutes after the Пр.№5 program initiation;
  • the СКД Engine is shut off automatically when the retrofire impulse value of 89,6 m/s is reached;
  • the module separation is executed by command of the Пр. №11 separation program;
  • the atmosphere descent is the automatically controlled descent (АУС).

2. «ДК + Пр.5 + БС (Т.СКД/Ф14/>:33)» Descent

The «ДК + Пр.5 + БС (Т.СКД/Ф14/>:33)» Descent is described in the Off-Nominal Situations book (page 75).

This descent is executed using data in Form 14 when the time available before the СКД Engine fire is more than 33 minutes.

The descent is executed in the reduced descent program – Пр. №5 and:

  • the ОСК orbital attitude is established using the digital circuit (БЦВК) and the ИКВ Sensor;
  • the crew uses the ПК СА for the БО separation;
  • the СКД Engine is configured for ignition by the Пр. №5 program marks;
  • the СКД Engine is ignited automatically in 33 minutes after the Пр.№5 program initiation;
  • the СКД Engine is shut off automatically when the retrofire impulse value of 89.6 m/s (before revolution 3) or 115.2 m/s (after revolution 3 and for the rest of the flight time);
  • the module separation is executed by command of the Пр. №11 separation program;
  • the atmosphere descent is the ballistic descent (БС).

3. «РОАК + БС» Descent

The «РОАК + БС» Descent is described in the Off-Nominal Situations book (page 79). This descent is executed using data in Form 14 when the time available before the СКД Engine fire is not less than 18 minutes.

This descent features the following:

  • the orbital attitude establishment is executed by the crew manually using analog circuit (РО АК);
  • the crew uses the ПК СА Panel for the БО separation;
  • the СКД Engine is prepared for ignition and ignited manually using the ПК СА Panel;
  • the СКД Engine is shut off automatically when the retrofire impulse value reaches 89.6 m/s (before revolution 3) or 115.2 m/s (after revolution 3 and for the rest of the flight time);
  • the spacecraft module separation is executed on the СTД thermal sensor command;
  • the atmosphere descent is the ballistic descent (БС).

4. «ДК + ВКЛ.СКД С ПК + БС» (Т.СКД/Ф14/<:33) Descent

The «ДК + ВКЛ.СКД С ПК + БС» (Т.СКД/Ф14/<:33) Descent is described in the Off-Nominal Situations book (page 83).

This descent is executed if the necessity of the urgent descent arises after the time scheduled in this revolution for the Пр.№5 program initiation and the crew cannot wait for the Пр.№5 initiation time scheduled for the next revolution.

This descent is executed using data in Form 14 when the time available before the СКД Engine fire is less than 33 minutes.

This descent features the following:

  • the crew executes the initiation of the reduced program by the РУС-2 «ПР.5» command from the РУС Handle at any moment after the urgent descent decision is made;
  • the Пр.№5 program is used for recording the urgent descent setting data from the ДЗУ Memory into the БЦВК and also for selecting the thruster types and the instruments to be used for the attitude establishment. Having completed these operation the crew initiates the Пр.№3 program thus inhibiting the Пр.№5 program;
  • the ОСК orbital attitude is established using the digital circuit (БЦВК) and the ИКВ Sensor;
  • the crew uses the ПК СА Panel for the БО separation;
  • the СКД Engine is prepared for ignition manually;
  • the СКД Engine is ignited manually in the time moment prescribed by Form 14;
  • the СКД Engine is shut off automatically when the retrofire impulse value reaches 89.6 m/s (before revolution 3) or 115.2 m/s (after revolution 3 and for the rest of the flight time);
  • the spacecraft module separation is executed on the СTД thermal sensor command;
  • the atmosphere descent is the ballistic descent (БС).
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