Orbital propulsion apparatus

Orbital propulsion apparatus which has a rotor drivable by an electric motor and upon which is mounted a plurality of mass members for movement radially of the axis of the rotor, each mass member having a rocket motor mounted thereon which, when fired, moves its associated mass member outwards against a compression spring mounted on the rotor so that at a predetermined angular velocity of rotor the mass members rotate in a common circular orbit, the rockets being controllable so that they can be fired through an arc of predetermined angularity so as to move each mass member radially outwards of its circular orbit to increase the centrifugal force of each mass member across the arc while the electric motor operates to maintain constant angular velocity of the rotor.

BACKGROUND OF THE INVENTION 
Field of the Invention 
This invention relates to propulsion apparatus particularly directed to but 
not limited to apparatus for propelling vehicles in airless regions. 
Propulsion apparatus for travel in airless regions, at the present date, is 
limited to chemically fueled reaction engines, namely rockets. Although 
this type of engine is efficient, weight and volume of rocket fuel 
necessarily limits the range and payload of vehicles propelled in this 
manner. 
Unless use can be made of energy developed by atomic reaction to afford a 
propulsive effect, space craft will only be able to travel a relatively 
short distance away from the earth. To date no reaction engine has been 
developed utilizing the energy released by atomic reaction. Engines, 
however, have been developed where an energy released by atomic reaction 
in the form of heat can be utilized to provide electrical energy. 
SUMMARY OF THE INVENTION 
The present invention provides propulsive apparatus wherein electrical 
energy developed through atomic or similar reactions can be utilized to 
effectively aid in propulsion of vehicles in airless regions. 
In the apparatus of the present invention orbital diameters or orbiting 
masses in balance are selectively shifted to provide increased centrifugal 
force in a selected direction and tendency of increased orbital diameter 
of the orbiting masses to result in a decrease in angular velocity is 
overcome by force applied by an electric motor the energy of which can be 
developed through atomic reaction. As atomic fuel has little mass relative 
to the energy available the vehicle propelled by the present invention can 
have a range much in excess of vehicles propelled solely by rocket fuels. 
A detailed description following related to the drawings gives 
exemplification of apparatus according to the invention which, however, is 
capable of expression in means other than those particularly described and 
illustrated.

DETAILED DESCRIPTION 
Referring to the drawings and particularly to FIGS. 1 and 2 one embodiment 
8 propulsion apparatus in accordance with the invention has a rotor, 
generally 9, having a hub 10 suitably mounted for rotation on the vehicle, 
not shown, to be propelled, the hub being connected through an overriding 
clutch 11 to an electric motor 12. The clutch permits the motor to drive 
the hub uni-directionally, shown by the arrow 13. 
Electric power for driving the electric motor is provided, preferably, by a 
nuclear reactor and attendent generating components which, for example, 
can be the type now in use for driving atomic powered submarines and the 
like. The electrical generating equipment is, of course, carried in the 
craft to be propelled. 
Three rods 15, 16 and 17 extend radially from the hub and terminate in 
stops 19, 20 and 21. The rods which are of equal length are symmetrically 
disposed about the hub. 
Rocket motors and mass members 23, 24 and 25 are mounted on the rods 15, 16 
and 17 respectively for slideable movement longitudinally of the rods. 
Compression springs 26, 27 and 28 are mounted over the rods between the 
mass members thereon and the stops. The rocket motors which carry their 
own fuel are arranged so that when fired the rockets exert a thrust 
radially outwards. The rockets are all of the same weight and the springs 
are identical. The rockets are of a type which can be fired 
intermittently, control of period and location of firing being obtained by 
suitable controls within the vehicle. 
OPERATION 
In operation, the rotor is driven by operation of the electric motor until 
the rotor reaches a predetermined angular velocity. The rockets and mass 
members, through centrifugal action are moved outwards against the springs 
compressing the latter slightly to rotate in a common circular orbit. As 
the weight of the rocket and mass members and strength of the springs are 
the same, centrifugal forces balance each other so that the apparatus is 
in a state of equilibrium. 
In order to achieve movement of the propulsion apparatus and with it the 
vehicle in a direction indicated by the arrow 31 each of the rockets is 
fired, in turn, as it passes through an arc S of its orbit the extent of 
which is defined by lines of radius R1 and R2 which subtend an arc of 
about 20.degree. bisected by the line 31 representing the direction of 
proposed travel. Thrust generated by each rocket, as it is fired, moves 
each associated mass member from its normal position, as shown in solid 
outline in FIG. 3, radially outwardly along its rod to an extended 
position shown in broken outline in FIG. 3, thus increasing its orbital 
radius, the extended orbit being defined by the broken line 33. Normally, 
with inertia constant, increase in orbital radius of each rocket and mass 
member, will result in a decrease of angular velocity, however, constant 
angular velocity is maintained through operation of the electric motor 
during the period in which the firing rocket passes through the orbital 
arc S. When each rocket ceases firing as it leaves arc S the spring will 
again return the rocket and mass member to its normal orbit. 
Propulsive effect, it is seen, is gained, not only from the thrust of each 
rocket but also from increased centrifugal force of the rocket and mass 
members due to the increased orbital speed of each rocket as it passes 
through the arc S. The increased centrifugal force along line 31 is equal 
to the energy output of the electric motor during the passage of each 
rocket and a mass member through the arc S. 
Operational effectiveness is largely dependent upon synchronous 
relationship of its many parts, however, for optimum effectiveness, 
angular velocity, angle of orbital arc S, natural frequency of the springs 
and periodic operation of the electric motor should be so related so as to 
take advantage of cumulative effect of cooperating parts operating at 
resonant frequencies. 
Another embodiment 50 of the invention is shown in FIGS. 4 through 8. 
Referring to FIGS. 4 and 5 a pair of orbital propulsion motors 51 and 52 
are shown mounted in a craft 53 on parallel axes 55 and 56. The craft as 
shown has a control area 57 and fuel areas 58 and 59 at ends of the craft. 
The motor 51 has a hub 61 to which is secured three symmetrically arranged 
radial arms 63, 64 and 65. Rocket engines 66, 67 and 68 which are 
identical in structure and weight are mounted on the arms 63, 64 and 65, 
respectively. 
FIGS. 6 and 7 show, in detail, one of the arms 63 together with rocket 
engine 66 of the propulsion motor 51 mounted for rotation between a pair 
of spaced brace members 71 and 72 extending from the hull of the craft. 
The hub of the motor 51 comprises a pair of hollow axles 73 and 74 mounted 
for rotation in bearings 76 secured to the brace members 71 and 72. The 
arm 63 is formed of a pair of spaced outwardly converging struts 77, one 
of the struts having a rigid connection to the axle 73 and the other strut 
having a rigid connection to the axle 74 and are connected at their outer 
ends by a bridging piece 78. 
A pair of parallel rails 79 -- 79 are secured to the struts near the outer 
ends thereof and slideably support the rocket engine for radial movement. 
A compression spring 81 fits between the rocket engine 66 and the bridging 
piece 78. Rocket fuel is delivered from the fuel tanks in the craft to the 
rocket engine 66 through a conduit 83.1 which is connected to a swivel 
83.2 at one end of the axle 74 thence through a conduit 84 which extends 
through the axle and outwardly along the arm 63 and thence by flexible 
conduits 85 to the rocket engine. Electrical power to the rocket engine 66 
is fed through lines 86 which are connected to a rotary connector 87 on 
the axle 73 thence through lines 86.1 extending through the axle 73 and 
along the arm 63 to the rocket engine. The arms 64 and 65 and the rocket 
engines thereon together with fuel and electrical lines are as described 
with reference to the arm 63. 
Blast from the rocket engines it is seen passes between the axles 73 and 74 
while thrust of the rocket engines is radially outward against their 
respective compression springs. 
The axles of the motors 51 and 52 are connected for driving engagement to 
electric motor 88 mounted in the craft. The motor 52 is identical to motor 
51 and, consequently, it is not considered a detailed description thereof 
is required. Period of operation of the electric motors, delivery of fuel 
to the rockets and fuel ignition can be controlled by controls within the 
craft such that the rocket engines can be fired through any desired arc as 
the rotors rotate. 
Operation of embodiment 50 is the same as described with reference to 
embodiment 8. In embodiment 50, however, provision of the motors provides 
balance control of the craft for operation thereof in any direction about 
an axis parallel to the axes of the rotors. Control of attitude of the 
craft so as to alter its direction of travel can be effected by operation 
of control rockets fed by the same fuel as used by the rocket motors 51 
and 52. These control rockets are not shown as such devices are of common 
knowledge.