Docking
PRELIMINARY GROUND RULES FOR DESIGN OF MULTIPLE DOCKING ADAPTER
'
GROUND RULES: 1.
The Multiple Docking Adapter (MDA) will have six ports, one of
which will be attached to the airlock module.
The remaining five
ports will be capable of receiving incoming spacecraft.
Ports 1, 2,
and 4 will contain the standard Apollo drogue and will duplicate the interfaces in the current lunar module docking ring.
Ports 3 and 5
will have the standard Apollo probe installed and will embody the same interfaces as those on the current Apollo CSM. 2.
(See enclosure 1).
The stan'd -off cross used for sighting while docking the CSM to
the lunar module will be duplicated on Ports 1, 2, and 4 to enable inline docking of the CSM and/or resupply module to these ports. 3.
An optical system will be installed on the MDA to permit passive
docking of a lunar module or LM/ ATM on Ports 3 and 5.
This optical
system should permit observation of a target on the lunar module to permit the astronauts in the CSM to "talk in" the astronaut in the lunar module.
The MDA will have windows to assist in the docking process.
Primary location to be considered for the windows will be in the pressure hatches. 4.
The multiple docking adapter will contain umbilicals and fluid lines
capable of transferring expendables and power fr_o m and to
th~
resupply
module to the CSM, lunar module, or orbital workshop. 5.
The multiple docking adapter must be capable of withstanding launch
loads, docking loads, maneuvering loads, and internal pressure loads during operational phases. 6.
The multiple docking adapter will have sufficient internal space for
astronaut turn-around and will provide internal supports and restraints '•
for ease of movement in and through the multiple docking adapter.
• '.
2
7.
The multiple docking adapter will have
s~fficient
room to carry
experiment hardware, etc. for the orbital workshop mission. 8.
Design and test ground rules and factors will be consistent with the
CSM/LMiRSM margins. 9.
Current Apollo configured hardware. q.nd procedures will be used
in docking p~ocesses (the current Apollo da;ogue support fittings and latches, spring-loaded docking latches, and hand operated latches will be used. ) 10.
The multiple docking adapter will have sufficient structural support
to restrain it during the boost phase and during the docking of additional spacecraft. 11.
The MDA will be structually supported independently of the Airlock
Module from the SLA attach points or the S-IVB forward skirt to minimize required structural redesign of the Airlock Module. 12.
A "clean" interface will be maintained between the Airlock Module
and the MDA. DOCKING SEQUENCE: (See Figures 1, 2, and 3 attached) 1.
The 209 CSM (docking Port No. 6) mates with docking Port No. 1
on the multiple docking adapter.
The astronaut removes and stows
the probe and drogue, depressurizes the CSM, and removes pressure hatch No. 1 prior to workshop activation (see Figure 1-II and 1-III). 2.
Upon completion of the orbital workshop mission; the astronauts
re-enter the CSM and reinstall the drogue and probe, leaving them in place for the revisit CSM 211 •
The multiple docking adapter i 's left
in the unpressurized condition. ~.
After launching of AS-211 CSM 211 is transposed and its docking
~ort (No. 9) is mated with docking Port No. 7 on the resupply module.
The probe and drogue are removed and stowed in the command module. (See Figures 1-IV and 1- V).
3 4.
Using an optical sighting device on the resupply module, the
astronauts dock the resupply module (Port No. tS) to the docking cross (Port No. 2).
One astronaut. enters the tunnel in the resupply module,
the CSM is depressurized, and , the probe and drogue are removed and stowed in the command module.
The astronaut then re-enters the CSM,
reinstalls the drogue at Port No. 7 of the resupply module, repressurizes the CSM, and releases the resupply module (see Figure 2- VI and 2-VII). 5.
Upon the launch of AS-212 the CSM 211 docks (Port No. 9) with the
lunar module ATM (Port No. 1 0).
The LM/ATM is then extracted from
AS-212 (see Figure 2-VIII and 2-IX). 6.
(Primary) One astronaut enters the lunar module.
The CSM/LM/ATM
transposes to the orbital workshop orbit and the lunar module is released from the command module after reinstallation of the appropriate docking fixtures.
The CSM 211 then performs the docking maneuver with
Port No. 1 of the multiple docking adapter while the lunar module briefly maintains its position.
The CSM is depressurized, docking fixtures at
Port No. 1 are removed, and the second astronaut enters the multiple docking adapter.
Using the optical system on the docking cross the re-
maining astronaut in the CSM acquires of its Port No. 10 to the NDA Port No. 3.
The astronaut in the multiple docking adapter performs the hand
latching operations, removes the probe, and removes the drogue for access to the lunar module.
The CSM 211, multiple docking adapter, and
lunar module, are then repressurized prior to completion to the connections of the resupply module and the orbital workshop (Figure 2-X and Figure 3). 6.
(Alternate) In the event that the
11
hard-docked" mode is not selec~d
for operation of the LM/ATM the docked CSM 211 /LM/ATM is maintai:hed in that position for · operation of the mission; or the
csM
attaches the
·. 4
lunar module to a tether affixed to the orbital workshop.
Docking Ports
No. 9 and 10 are spearated after installation of docking hardware in the CSM portion df the docking process in the primary
11
6i• above is then ,
accomplished. ·
'
,·l .
•
'· '
...
~·
I
BASE ICD' s for MDA DESIGN
I.
Docking_
II.
a.
MH0-1 05-048-116: CSM/LM Docking Umbillical Mechanical Interface.
b.
MH0-1 05-059-216: Umbillical Electrical Requirements.
c.
MH0-1 05-127-116: LM/Drogue Interface
d.
MH0-1 05-128-116: CM/LM Structural InteTface
e.
MH0-1 05-231-116: CM/LM Post Contact Maximum Excursion Envelope.
f.
MH0-1 05-541-424: LM withdrawal envelope.
Docking Loads & Interfaces:
III.
a.
MH0-105-050-414: CSM/LM Structural loads & Bending Moments
b.
MH0-105-071-414: CSM/LM Docking Thermal Interface.
c.
MH0-1 05-079-414: CSM/LM RCS Impingement
d.
MH0-1 05-085-414: CSM/LM ECS (Cabin Repressurization)
Docking Aids: a.
MH0-1 05-053-416: CSM/LM Docking Grounp. Rules
b.
MH0-105-057 -416: CSM/LM Crew Handling of Tunnel Hardware (Intra-Vehicular-Transfer)
c.
. MH0-1 05-305-116 Crew man Optical Alinement Site (LOAS)
d.
MH0-1 05-639-236: Crewman Optical Alinement Site (LOAS) Electrical Requirements.
e. IV.
MH0-105-638-136: . Crewman Optical Alinement Site (LOAS) Envelope.
Miscellaneous: a.
MH0-105-061-
CM/LM Emergency Crew Transfer . .
b.
MH0-105-132-
CM/LM Transferrable equipment.
• Rodney D. Stewart
ORBITAL WORKSHOP EXPERIMENTS FOR STOW AGE IN MDA · E~eriment
Title
No.
. Wt .(#)
. Vol (ft3f
M053
Human Vestibular Functions
. 67: 0
1-8; 20 -
T020
Jet Shoes
150. 0*
4 . 00
M487
Workshop Habitability
287.0
21. 00
M050
Metabolic Activities
44.0
.90
M052
Bone & Muscle Changes
12.0
1. 75
M051
Cartovascular Assessment
40.0
10.00
D019
Suit Donning
6.5
11.00
D018
Integrated Maintenance
D020
Alternate Restraints
M486
Astronaut EVA Equipment
M488
High Pc Gas Expulsion
38.0
. 54
M489
Heat E :xehanger Servicing
65.0
8.00
M479
Zero "G" Flammability
88.0
4.00
M493
Electron Beam Welding
100. 0
4.00
M492
Tube Joining
6.0
l. 50
M466
Suits & Lunar Hardware
306.0
25.60
M484
Workshop Artificial 11 G"
260.0
6. 30
Totals
165.0
40.00
7.0
2.00
128.0
1,468.5
The above is a ''first-cut' ' and we will update as required. related to stowage of the above experiments:
Remarks Chair (Spin-up) :+:Could use back-pack (experiment #M486) Collapsible Partitions, lights-etc. (Could require shock mounting) (26# Return Weight in C. M.)
Tools -
etc.~
11.60
...
Floo.r Segments ·- mi'Xn~e built into S-IVB
170.39 The following are some thoughts on ground rules
2
1.
Exact sizes and shapes for many of the above experiments have not been determined.
Stowage volume available may have some effect on stowed configuration.
2.
Some experiments can be broken down into several packages for convenience of stowage. ·
3.
Experiment hardware plus container should be small enough to be transported through
airlock.
4.
Stowage techniques should eliminate all sharp objects on interior of MDA.
5.
Br.ackets which hold hardware should be removable or fold back out of the way.
6.
Suggest soft restraints (pockets, flaps, etc. wit_!l zippers or velcro) for soft materials.
(Suits, partitions, etc.)
..
~
The above information is the latest available from Jack Waite's office - 11/16/66. •.
Ot"hital Workshop
I
AS-2.10~,
Drosu e: .
fj
~
P...-ohe .·
n 1If
CSM zoq
Orbital workshor AS-2.10
&,i{tnlS
Or-bital work shot':> AS :z_IO
CSM 2.09
•
CSl\1 Z. I I ·
AS z..tl ·.
CStv\
.
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Zll
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•
•
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.
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CSM
. ' ; ]Ill[
Z11
AS CSM
211 ,. ••
'
,I
•'
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r
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'
Z.l~
\.
Orb1to./ CSM
Work~hop
AS
~10
z ll
.
.
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. -
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.
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.
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' i . •' . J. •l
•
·•
,_
.
-----
Fi~K,..t 3
'
GROUND RULES: 1.
The Multiple Docking Adapter (MDA) will have six ports, one of
which will be attached to the airlock module.
The remaining five
ports will be capable of receiving incoming spacecraft.
Ports 1, 2,
and 4 will contain the standard Apollo drogue and will duplicate the interfaces in the current lunar module docking ring.
Ports 3 and 5
will have the standard Apollo probe installed and will embody the same interfaces as those on the current Apollo CSM. 2.
(See enclosure 1).
The stan'd -off cross used for sighting while docking the CSM to
the lunar module will be duplicated on Ports 1, 2, and 4 to enable inline docking of the CSM and/or resupply module to these ports. 3.
An optical system will be installed on the MDA to permit passive
docking of a lunar module or LM/ ATM on Ports 3 and 5.
This optical
system should permit observation of a target on the lunar module to permit the astronauts in the CSM to "talk in" the astronaut in the lunar module.
The MDA will have windows to assist in the docking process.
Primary location to be considered for the windows will be in the pressure hatches. 4.
The multiple docking adapter will contain umbilicals and fluid lines
capable of transferring expendables and power fr_o m and to
th~
resupply
module to the CSM, lunar module, or orbital workshop. 5.
The multiple docking adapter must be capable of withstanding launch
loads, docking loads, maneuvering loads, and internal pressure loads during operational phases. 6.
The multiple docking adapter will have sufficient internal space for
astronaut turn-around and will provide internal supports and restraints '•
for ease of movement in and through the multiple docking adapter.
• '.
2
7.
The multiple docking adapter will have
s~fficient
room to carry
experiment hardware, etc. for the orbital workshop mission. 8.
Design and test ground rules and factors will be consistent with the
CSM/LMiRSM margins. 9.
Current Apollo configured hardware. q.nd procedures will be used
in docking p~ocesses (the current Apollo da;ogue support fittings and latches, spring-loaded docking latches, and hand operated latches will be used. ) 10.
The multiple docking adapter will have sufficient structural support
to restrain it during the boost phase and during the docking of additional spacecraft. 11.
The MDA will be structually supported independently of the Airlock
Module from the SLA attach points or the S-IVB forward skirt to minimize required structural redesign of the Airlock Module. 12.
A "clean" interface will be maintained between the Airlock Module
and the MDA. DOCKING SEQUENCE: (See Figures 1, 2, and 3 attached) 1.
The 209 CSM (docking Port No. 6) mates with docking Port No. 1
on the multiple docking adapter.
The astronaut removes and stows
the probe and drogue, depressurizes the CSM, and removes pressure hatch No. 1 prior to workshop activation (see Figure 1-II and 1-III). 2.
Upon completion of the orbital workshop mission; the astronauts
re-enter the CSM and reinstall the drogue and probe, leaving them in place for the revisit CSM 211 •
The multiple docking adapter i 's left
in the unpressurized condition. ~.
After launching of AS-211 CSM 211 is transposed and its docking
~ort (No. 9) is mated with docking Port No. 7 on the resupply module.
The probe and drogue are removed and stowed in the command module. (See Figures 1-IV and 1- V).
3 4.
Using an optical sighting device on the resupply module, the
astronauts dock the resupply module (Port No. tS) to the docking cross (Port No. 2).
One astronaut. enters the tunnel in the resupply module,
the CSM is depressurized, and , the probe and drogue are removed and stowed in the command module.
The astronaut then re-enters the CSM,
reinstalls the drogue at Port No. 7 of the resupply module, repressurizes the CSM, and releases the resupply module (see Figure 2- VI and 2-VII). 5.
Upon the launch of AS-212 the CSM 211 docks (Port No. 9) with the
lunar module ATM (Port No. 1 0).
The LM/ATM is then extracted from
AS-212 (see Figure 2-VIII and 2-IX). 6.
(Primary) One astronaut enters the lunar module.
The CSM/LM/ATM
transposes to the orbital workshop orbit and the lunar module is released from the command module after reinstallation of the appropriate docking fixtures.
The CSM 211 then performs the docking maneuver with
Port No. 1 of the multiple docking adapter while the lunar module briefly maintains its position.
The CSM is depressurized, docking fixtures at
Port No. 1 are removed, and the second astronaut enters the multiple docking adapter.
Using the optical system on the docking cross the re-
maining astronaut in the CSM acquires of its Port No. 10 to the NDA Port No. 3.
The astronaut in the multiple docking adapter performs the hand
latching operations, removes the probe, and removes the drogue for access to the lunar module.
The CSM 211, multiple docking adapter, and
lunar module, are then repressurized prior to completion to the connections of the resupply module and the orbital workshop (Figure 2-X and Figure 3). 6.
(Alternate) In the event that the
11
hard-docked" mode is not selec~d
for operation of the LM/ATM the docked CSM 211 /LM/ATM is maintai:hed in that position for · operation of the mission; or the
csM
attaches the
·. 4
lunar module to a tether affixed to the orbital workshop.
Docking Ports
No. 9 and 10 are spearated after installation of docking hardware in the CSM portion df the docking process in the primary
11
6i• above is then ,
accomplished. ·
'
,·l .
•
'· '
...
~·
I
BASE ICD' s for MDA DESIGN
I.
Docking_
II.
a.
MH0-1 05-048-116: CSM/LM Docking Umbillical Mechanical Interface.
b.
MH0-1 05-059-216: Umbillical Electrical Requirements.
c.
MH0-1 05-127-116: LM/Drogue Interface
d.
MH0-1 05-128-116: CM/LM Structural InteTface
e.
MH0-1 05-231-116: CM/LM Post Contact Maximum Excursion Envelope.
f.
MH0-1 05-541-424: LM withdrawal envelope.
Docking Loads & Interfaces:
III.
a.
MH0-105-050-414: CSM/LM Structural loads & Bending Moments
b.
MH0-105-071-414: CSM/LM Docking Thermal Interface.
c.
MH0-1 05-079-414: CSM/LM RCS Impingement
d.
MH0-1 05-085-414: CSM/LM ECS (Cabin Repressurization)
Docking Aids: a.
MH0-1 05-053-416: CSM/LM Docking Grounp. Rules
b.
MH0-105-057 -416: CSM/LM Crew Handling of Tunnel Hardware (Intra-Vehicular-Transfer)
c.
. MH0-1 05-305-116 Crew man Optical Alinement Site (LOAS)
d.
MH0-1 05-639-236: Crewman Optical Alinement Site (LOAS) Electrical Requirements.
e. IV.
MH0-105-638-136: . Crewman Optical Alinement Site (LOAS) Envelope.
Miscellaneous: a.
MH0-105-061-
CM/LM Emergency Crew Transfer . .
b.
MH0-105-132-
CM/LM Transferrable equipment.
• Rodney D. Stewart
ORBITAL WORKSHOP EXPERIMENTS FOR STOW AGE IN MDA · E~eriment
Title
No.
. Wt .(#)
. Vol (ft3f
M053
Human Vestibular Functions
. 67: 0
1-8; 20 -
T020
Jet Shoes
150. 0*
4 . 00
M487
Workshop Habitability
287.0
21. 00
M050
Metabolic Activities
44.0
.90
M052
Bone & Muscle Changes
12.0
1. 75
M051
Cartovascular Assessment
40.0
10.00
D019
Suit Donning
6.5
11.00
D018
Integrated Maintenance
D020
Alternate Restraints
M486
Astronaut EVA Equipment
M488
High Pc Gas Expulsion
38.0
. 54
M489
Heat E :xehanger Servicing
65.0
8.00
M479
Zero "G" Flammability
88.0
4.00
M493
Electron Beam Welding
100. 0
4.00
M492
Tube Joining
6.0
l. 50
M466
Suits & Lunar Hardware
306.0
25.60
M484
Workshop Artificial 11 G"
260.0
6. 30
Totals
165.0
40.00
7.0
2.00
128.0
1,468.5
The above is a ''first-cut' ' and we will update as required. related to stowage of the above experiments:
Remarks Chair (Spin-up) :+:Could use back-pack (experiment #M486) Collapsible Partitions, lights-etc. (Could require shock mounting) (26# Return Weight in C. M.)
Tools -
etc.~
11.60
...
Floo.r Segments ·- mi'Xn~e built into S-IVB
170.39 The following are some thoughts on ground rules
2
1.
Exact sizes and shapes for many of the above experiments have not been determined.
Stowage volume available may have some effect on stowed configuration.
2.
Some experiments can be broken down into several packages for convenience of stowage. ·
3.
Experiment hardware plus container should be small enough to be transported through
airlock.
4.
Stowage techniques should eliminate all sharp objects on interior of MDA.
5.
Br.ackets which hold hardware should be removable or fold back out of the way.
6.
Suggest soft restraints (pockets, flaps, etc. wit_!l zippers or velcro) for soft materials.
(Suits, partitions, etc.)
..
~
The above information is the latest available from Jack Waite's office - 11/16/66. •.
Ot"hital Workshop
I
AS-2.10~,
Drosu e: .
fj
~
P...-ohe .·
n 1If
CSM zoq
Orbital workshor AS-2.10
&,i{tnlS
Or-bital work shot':> AS :z_IO
CSM 2.09
•
CSl\1 Z. I I ·
AS z..tl ·.
CStv\
.
'
Zll
• J
•
•
'
• .'
.
•,
.
.
.
.
'
'
'
CSM
. ' ; ]Ill[
Z11
AS CSM
211 ,. ••
'
,I
•'
'
r
'
'
Z.l~
\.
Orb1to./ CSM
Work~hop
AS
~10
z ll
.
.
\
. -
',
.
.
.
..
'
.
-I
.
!
'
.
'
...
' ·' '
' i . •' . J. •l
•
·•
,_
.
-----
Fi~K,..t 3
