ANDROGYNOUS PERIPHERALDOCKING SYSTEM (APDS)

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THE SOYUZ-APOLLO ANDROGYNOUS PERIPHERAL DOCKING SYSTEM IS

CONSIDERED HERE. PRESENTED ARE THE OPERATIONAL PERFORMANCE

OP THE SYSTEM AND THE DOCKING SEQUENCE, THE DOCKING SPACE-

CRAFT CREW PROCEDURES FOR THE ELIMINATION OF SYSTEM MALFUNC-

TIONS ARE DEFINED,

AS AHDROGYNOUS PERIPHERAL DOCKING SYSTEM, furtueron referred to as "the docking system"»

ia intended for the Soyus and Apollo docking and undocking after termination of their joint

flight.

During docking, the system provides for attenuation, capture, alignment, spacecraft re-

traction, and interface sealing*

When undooking, it provides for separation and pushing apart of the spacecraft*

The system will ensure docking if the parameters at close approach do not exceed the

following figuress

- range rate 0.05 - 0.3 m/eee;

- longitudinal axis displacement-300 mm;

~ pitch, yaw and roll misalignment —7°;

- pitch, yaw and roll angular rates-*1°/see for the active spacecraft; 0»1°/seo for

the passive spacecraft;

- lateral relative rate 0*1 m/sec*

The docking system consists of a docking assembly, an automatic unit, controls and

displayE.

The docking mechanism of the docking assembly includess

- a riag with three guides;

- six rod interaction mechanisms motj&ted on the ring and

/3

- 2 -

- three capture latch electric drives;

- three body-mount latch electric drives.

The guide ring is mounted on six moving rods and is controlled by means of a differential

drive.

The body and structural ring make up the transfer tunnel which is closed from inside by

a hatch.

The structural ring mounts:

- an interface sealing;

-a guide pin and a socket providing for the spacecraft final alignment;

- spring thrustera;

- an interface electric connector fixture;

- undocking, contact, and seal sensors;

- latch mechanisms with active and passive hooks.

The ring mounts ring alignment sensors.

For passive docking, the ring is retracted. For active docking, the ring is extended to

the Initial position for docking.

When the rings are aligned, the capture latches engage body-mount latches. It results

in the ring capture.

!

- 3 -

After attenuation, the ring is retracted until the seals get in contact.

The rubber seal ia pressure-sealed with the help of the pressurization drive,

The electric drive closes, by means of cables, the active hooks of the latch mechanism

which engage passive hooka of the Apollo.

?or undooking, the hooks ef the capture latches or the body mount latches open* The

spacecraft are pushed apart by spring thrusters. At the same time, the Soyuz micro engines

are ignited for separation.

The docking assemblies of the Soyuc and Apollo spacecraft are similiar in design.

The Soyuz mounts ball screw actuators?as distinguished from the Apollo independent

hydraulic attenuators, and electric drive with cable rigging for ring retraction.

The Soyuz docking assembly is also characterized by electric drives of body mount and

capture latches and by the use of pyrotechnics applied to capture latches and hooks for back up

undocking.

The automatic unit and controls provide for automatic and manual docking.

In automatic operation, the automatic unit logic device generates control signals to

initiate subsequent operations if the previous operations have been carried out. The command/

signal device and instrument board display information of the status of system mechanisms and

the fulfilment of operations.

In the case of manual docking, the following commands can be carried out by tha crew with

- 4 -

the help of the command/signal device:

- DOCKING SYSTEM POWER SUPPLY

- LATCH CLOSING

- RETRACTION

- HOOK CLOSING

- UNDOCKING

- SYSTEM BLOCKING OFF

- RING EXTENSION

- LATCH OPENING

- HOOK OPENING

- CLEARANCE FOR BACKUP UNCOCKING

- BACKUP OPENING OF PASSIVE HOOKS.

If necessary, soae control commands can be issued to the spacecraft from the ground

through the command/aignal radio link.

The above-mentioned commands are accompanied by appropriate lights* The command/signal

device has also the following lights:

- TRANSFER HATCH CLOSED

- PASSIVE READINESS

- ACTIVE RBADIHESS

- RIHG ALIGNED - '

- CAPTURE

- INTERFACE ALIGKED

- IH?ER?ACE SEALED.

All these lights serve to inform the crew members?

- of the system status at .the given moment;

- of the beginning and progress of operation;

- of the result of operation.

When ready for passive docking, the guide ring ia retracted, the active hooks of the

structural latches are fully open, the body mount latches are closed (ready for docking),

the PASSIVE HEADIHESS light of the command/signal device ie 05.

Now let's consider the operations sequence of the system.

When the DOCKING SYSTEM POWER SUPPLY command ia given, the DOCKING SYSTEM POWER SUPPLY

light of the command/signal device goes OS*

The active Apollo spacecraft approaches the Soyuz. When the spacecraft get in contact

the ring alignment sensors trip, the CAPTURE LIGHT goes on.

After attenuation, alignment of the spacecraft and retraction by the Apollo hook drive,

3

- 6 _

the seal senaors operate. The IHTEKFAGB ALIGNED light of the command/signal device goeo on.

As the Apollo hooka close, the interface seal sensors, switch on the INTERFACE SEALED light

on the command/signal derice. The .power supply of the system is turned off and all the lights

go off except for^the PASSIVE READINESS light.

For undocking, the crew give the commands DOCKING SYSTEM POWER SUPPLY* The lights

DOCKIHG SYSTEM POWER SUPPLY, INTERFACE SEALED, INTERFACE ALIGNED, CAPTURE will go on.

Aa the Apollo hooka open, the seal sensors are first released, the INTERFACE SEALED light

goes off, then the seal contact'sensors trip and the INTERFACE ALIGNED, light goes off.

As the rings separate, the ring alignment sensors are released and the CAPTURE light

go«s off. The system power supply is turned off and the DOCKING SYSTEM POWER SUPPLY light

gofts off, The PASSIVE READINESS light is on. '

. ~ .Before. " the- Soynz . ana Apollo -test docking-' the - - Soyuz brings its docking

system to active readiness* The ring la extended to its initial position (six minutes), the

RIS& EXTEHSIOS light is 05. The capture latches are ready for docking. Active hooks, are open.*The ACTIVE READIESTS light ia OS, ' .

The DOCKING SYSTEM POWER SUPPLY command switches on the lights DOCKING SYSTEM POWER

SUPPLY and RING ALIGNED.

After contact of the Soyus and Apollo the RX2JG ALIGNED light goes OFF, The ring alignment

- 7 —

sensors trip* The CAPTURE light of the command/signal device ie OH. Then the spacecraft are

attenuated and aligned during not more than five monutes* The rod misalignment sensors again

awitch on the RIKG ALIGNED light* Eight seconds after the spacecraft alignment, the ring re-

traction begins. It continues not longer than six minutes. The beginning of the retraction is

monitored by means of the RETRACTION and ACTIVE READINESS lights.

After the contact of the interface rubber seale, the interface sealing drive begins to

operate. It is monitored with th« help of the HOOKS CLOSING .- light and the ITOEB̂ ACE ALIGNED

light. . .

In .15 seconds, the drive of the docking mechanism is turaed off. When the riag is fully

retracted, the RETRACTION light goes off. It takes not more than five minutes for the active

hooks to close- The signal of the hook closing aensora switches on the INTERFACE SEALED light

and switches off all other lights. The light SYSTEM MODE OPERATION ACCOMPLISHED is ON,

After turning on the DOCKIIG SYSTEM POWER SUPPLY, the following lights will be ON:

- DOCKING SYSTEM POWER SUPPLY- CAPTURE

- INTERFACE ALIGNED

- INTERFACE SEALED,

After the UKDOCKHJG command, the ring extends for 5 see in order to unload the latches.

The extension of the ring is monitored by means of the RING EXTENSION light which at first

goea OH and then OFF, •i

The INTERFACE SEALED light goes OFF*

When the ring fully extends, the latches and hooks begin opening, This ia monitored by

means of the LATCH OPENING light which is ON for 5 sec.

The hook: opening continues not longer than five minutes. After the release of the seal

contact sensors, the INTERFACE ALIGNED light goes OFF; after the release of the capture

sensors/the CAPTURE light is also OFF,-

At the same time, the spring thrusters push the spacecraft apart and the micro engines

operate for 8 sec to separate the Soyuz,

When the hooks fully opcm, the sensors switch on the light: SYSTEM MODE OPERATION

ACCOMPLISHED, oth«r lights go OFF* The system ptswer supply is cut off.

So the undocking.mode is accomplished.

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T-794757 3aK. 813