Docking and fuel transfer system provides an efficient method for transferring fuel from a tanker to another vehicle. With this system, no triggering operation is required prior to docking, the support system can be rigidized by simply locking the rams of shock absorbers, and no separate fuel line coupling action is required

West, A. M.

English

NASA Technical Reports Server

February 1968	 1	 Brief 68-10039 
NASA TECH BRIEF
xi 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Fuel Transfer System Permits Rapid Coupling 
The problem: 
To provide a simple, yet efficient, method for trans-
ferring fuel from a tanker to another vehicle. Original 
interest in this problem arose through a requirement 
to connect an orbiting fuel tanker to a receiving space-
craft for the transfer of fuel. Methods exist, but are 
complex and many sequences of events are required 
to accomplish the connection and transfer. 
The solution: 
A docking and fuel transfer system which has these 
advantages over existing systems: (1) no triggering 
operation is required prior to docking; (2) the support 
system can be rigidized by simply locking the rams of 
shock absorbers; and (3) no separate fuel line coupling 
action is required.
How it's done: 
The docking or connecting mechanism, shown in 
the figure, consists of a receiver cone mounted to the 
vehicle to be fueled, and a mating cone mounted on 
the tanker vehicle by shock absorbers. Six shock 
absorbers are arranged in sets of two, spaced 120° 
apart in a triangular pattern. The end connections of 
the shock absorbers are equipped with ball joints. 
The shock absorbers are two stage with a low spring 
rateover part of the stroke and a higher spring rate 
over the remainder of the stroke. One part of the fuel 
transfer connector is mounted on the receiver cone, 
the other section on the mating cone. A flexible fuel 
transfer line allows transfer of the fuel from one 
vehicle to the other.
(continued overteafl 
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The initial engagement of the mating cone with the 
receiving cone is permitted by the low spring portion 
of the shock absorber stroke and the multiplane free-
dom of motion allowed by the ball joints. The short 
cylindrical ends on the two cones provide for align-
ment of the parts of the fuel line connector just prior 
to their engagement. 
The major portion of the impact energy of the two 
vehicles is now absorbed in the higher spring rate 
portion of the shock absorber. The controlled re-
bound of the shock absorbers returns the ram to its 
original length with small energy return to the 
vehicle and tanker. The two are now axially aligned 
due to the symmetrical arrangement of the shock 
absorbers. Additional rigidity to the support system 
is achieved by locking the rams of the shock ab-
sorbers. 
The two vehicles are now docked and in position for 
fuel transfer. 
The fuel transfer connection consists of that part 
of the mating cone and that part of the receiving 
vehicle which unite for transferring the fuel. 
The receiving section is composed of the flange 
of the cone, the probe, and springs to permit align- 
ment of the probe. The tanker or mating section con-
sists of a collar (which is located to the left prior 
to engagement), a plunger, and locking balls. A ball 
screw jack is secured to the body, which is secured 
to the flange of the mating cone. A motor, mounted 
also on the flange, engages with the gear of the screw 
jack. Three pneumatic bellows are evenly spaced 
around the connector. A feed line is interconnected 
between the bellows to insure their even pressure.
During docking, as the mating cone enters the 
receiving cone, the probe enters the body. The springs 
keep the probe centered and permit self-alignment 
of the probe with the body. As the probe enters, it 
depresses the plunger, and releases the balls. This 
permits the collar to move to the right, thus trapping 
the balls and locking the two parts of the connector 
together. The motor then operates the screw jack, 
which attaches the mating and receiving cones more 
firmly together with the forces being transmitted 
through the balls. Fuel is then transferred. 
To release the two sections, the motor first releases 
the jacking forces. Pressure is then supplied to a 
bellows which moves the collar to the left, permitting 
the balls to disengage the probe. The cones, together 
with the connector, are now free to separate. 
Notes: 
1. This device could be adapted to fuel and liquid 
transfer applications in industry where large 
amounts of fuel must be transferred quickly. 
2. Inquiries concerning this innovation may be di-
rected to:
Technology Utilization Officer 
Marshall Space Flight Center 
Huntsville, Alabama 35812 
Reference: B68-10039 
Patent status: 
No patent action is contemplated by NASA. 
Source: Andrew M. West 
of Lockheed Missiles and Space Company 
under contract to 
Marshall Space Flight Center 
(M FS-91326)
Brief 68-10039	 Category 05


Fuel transfer system permits rapid coupling

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