US3110154A - Compound propulsion system - Google Patents

Compound propulsion system Download PDF

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US3110154A
US3110154A US87394A US8739461A US3110154A US 3110154 A US3110154 A US 3110154A US 87394 A US87394 A US 87394A US 8739461 A US8739461 A US 8739461A US 3110154 A US3110154 A US 3110154A
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rocket
ingredients
energy
propulsion
electrical
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US87394A
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Theodore N Edelbaum
Edward A Pinsley
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RTX Corp
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United Aircraft Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0037—Electrostatic ion thrusters
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S376/00—Induced nuclear reactions: processes, systems, and elements
    • Y10S376/90—Particular material or material shapes for fission reactors
    • Y10S376/904—Moderator, reflector, or coolant materials
    • Y10S376/906—Metal

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  • This invention relates to a compound propulsion system and more particularly to a propulsion device having interrelated propulsion units with ⁇ one of the units being a high-thrust, short-duration device and the other of the units being a low-thrust, high-specific impulse, long-duration device.
  • lt is, therefore, a primary object of this invention to combine an electrical propulsion device with a chemical rocket, with the chemical rocket being utilized for short duration, high-thrust maneuvering purposes.
  • a fuel storage tank containing, for example, lithium is indicated at ld.
  • the lithium is used as a common fuel in both the rocket propulsion unit l2 and the electric propulsion unit le.
  • the electrical propulsion unit ld eventually obtains its power through a suitable generator (referred t lhereinafter at 54) which generator in turn receives power from a combined primary power circuit lo and a secondary power circuit l.
  • the propulsion unit 14 is illustrated by example as a bombardment ion engine out may readily take the form of an arc jet (which may accelerate hydrogen received from the rocket source), a magneto-hydrodynamic accelerator or other ion engine.
  • the lithium from the storage tank lill is pumped by one or more pumping units Ztl and 22 into the primary circuit lo through a suitable nuclear reactor Zfi.
  • the nuclear reactor which may be of any well-known type, adds heat to the liquid lithium and discharges the heated lithium from a line 26.
  • Suitable valves 28 and Sli control the llow of lithium into a heat exchanger coil 34- so that the lithium, in fact, circulates from the nuclear reactor 2d to the heat exchanger coil 34 and then back to the reactor for added heating.
  • the heat exchanger receives flow of a suitable working liquid (for example, a liquid metal) from a pump to and an inlet line 32. This liquid flows in the secondary circuit l.
  • a suitable working liquid for example, a liquid metal
  • the liquid picks up heat in the heat exchanger and discharges the heated working iluid into a line 4d and a suitable turbine 46. Exhaust from the turbine i6 passes to a suitable radiator 48 for the release of excess heat energy. The exhaust from the radiator passes through a line Sil and back to the pump dll.
  • the working liquid is vaporized in the heat exchanger, and after passing through the turbine tle is again condensed in the radiator d8.
  • the turbine 46 drives an electric generator 5d which in turn provides the electrical energy for the electrical propulsion unit ld.
  • the propulsion particles which are accelerated rice out of the exhaust of the propulsion unit 14 by electrical means, comprise lithium ions which are supplied via the line 6l?.
  • a valve 62 leading from the primary circuit 16 expands a very minute portion of lithium and directs it to the electrical propulsion unit le, which for example, may be a bombardment ion engine.
  • the lithium is ionized in the ion engine ld and the lithium ions are accelerated in the ion engine ld, thus providing specific impulses in the range from 2,000 to 20,000 seconds.
  • the tripropellant rocket gives a very high, specific impulse.
  • the chemical propellants would dl be pre-heated before being introduced into the rocket combustion chamber.
  • both high-thrust and lowthrust operation is readily achieved.
  • the ⁇ fuel inventory for ferrying operations is substantially reduced.
  • less cryogenic tanlsage is required than for an ordinary hydrogen-lluorine propellant system.
  • a portion of the chemical rocket propellant, formerly charged off to payload may now be used as electrical propulsion fuel.
  • the continual replenishment of lithium in the closed-loop primary circuit will alleviate the problem of poisoning of the reactor coolant.
  • lithium has a low-neutron absorptive quality which makes it acceptable to nuclear heating without contamination.
  • very high speciiic impulse is achieved in the chemical rocket, particularly if the nuclear reactor temperatures are such that the lithium is introduced in the vapor state.
  • a compound propulsion unit including a rocket, means for supplying a plurality of propulsion ingredients to said rocket, an electrical propulsion device and means for conducting one of said ingredients to said electrical propulsion device for acceleration therein.
  • a compound propulsion unit including a rocket, means for supplying a plurality of propulsion ingredients to said rocket, an electrical propulsion device including means for accelerating propellant therein, and means for conducting one of said ingredients to said electrical propulsion device for supplying the propellant to be accelerated.
  • a compound propulsion unit including a rocket, a plurality of propulsion ingredients including a source of lithium, means for supplying said ingredients to said rocket, an electrical propulsion device, and means for conducting lithium from said source to said electrical propulsion device for acceleration therein.
  • a compound propulsion unit comprising a rocket device and an electrical propulsion device, and means for supplying at least one ingredient as a common propulsive ingredient to both said devices.
  • a compound propulsion device including a rocket, sources of three propulsive ingredients, means for conducting said ingredients to said rocket for reaction therein, a nuclear heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of one of said ingredients to said electrical propulsion device for acceleration therein.
  • a compound propulsion device including a rocket, sources of a plurality of propulsive ingredients including an element which is readily ionized, means for conducting said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an ion propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of said element to said ion propulsion device for ionization and subsequent acceleration.
  • a compound propulsion device including a rocket, a plurality of sources of different propulsive ingredients, means for conducting said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conductin'J a relatively small portion of one of said ingredients to said propulsion device for use as a propellant.
  • a compound propulsion device including a rocket, a plurality of sources of different propulsive ingredients, means for conducting selective amounts of said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of one of said ingredients to said electrical propulsion device for acceleration therein.
  • a compound propulsion system comprising a first cycle, said cycle having a first working fluid, a first path for circulating said first working fluid, a source or" heat for adding energy to said Working fluid, a heat exchange unit receiving said working fluid, a second cycle including a second working fluid, means connecting said second cycle to said heat exchanger means to extract energy therefrom, means in said second cycle for converting the energy from said second worldng fluid into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, means for conducting Working fluid from said first cycle to said electrical propulsion device, and a rocket receiving a portion of said first Working fluid for use as thrust producing material.
  • a compound propulsion system comprising a first cycle, said cycle having a first working fluid which is readily ionized, a first path for circulating said first Working fluid, a source of heat for adding energy to said worL ing fluid, a heat exchange unit receiving said Working fluid, a second cycle including a second Working fluid, means connecting said second cycle to said heat exchange means to extract energy therefrom, means in said second cycle for converting the energy from said second Working fluid into electrical energy, an ion propulsion device receiving electrical energy from said converting means, means for conducting Working fluid from said first cycle to said ion propulsion device for supplying the ions to be i accelerated, a rocket power plant, a plurality of sources of propulsive ingredients for said rocket and means for conducting at least a portion of said first Working fluid to said rocket for reaction with said ingredients.
  • a compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source heat in said first cycle for heating said one ingredient, means for extracting heat energy from said one ingredient, a second cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, a propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device to provide a propellant therefor.
  • a compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source of nuclear heat in said first cycle for heating said one ingredient,
  • a second closed cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said iluid into electrical energy, an ion propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device for acceleration therein.
  • a compound propulsion system including a rocket, sources of propulsion ingredients comprising hydrogen, iluorine and lithium, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of lithium from one of said sources, a source of nuclear heat in said first cycle for heating said lithium, means for extracting heat energy from said heated lithium, a second cycle including a working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, a bombardment ion propulsion device receiving electrical energy from said converting means, and means conducting a portion of said lithium to said propulsion device for acceleration therein.
  • a compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source heat in said first cycle for heating said one ingredient, means for extracting heat energy from said one ingredient, a second closed cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device for providing a thrustproducing material for said device.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Description

Nov. 12, 1963 T. N. EDELBAUM ETAL 3,110,154
COMPOUND PRoPuLsIoN SYSTEM Filed Feb. 6. 1961 /NvE/vToRs THEoDoD/s /v. EDEL BAUM EDWARD APM/SLU United States Patent O 3,110,154 CMPUND PRPULSEN SYSTEM Theodore N. l'ldelhaum, Windsor, Conn., and Edward A.
linsley, Cambridge, Mass., designers to United Aircraft Gorporation, )East Hartford, Sonn., a corporation of Delaware File-d lFeb. 6, will, Ser. No. 87,394 i4- Claims. (Cl. oil-35.6)
This invention relates to a compound propulsion system and more particularly to a propulsion device having interrelated propulsion units with `one of the units being a high-thrust, short-duration device and the other of the units being a low-thrust, high-specific impulse, long-duration device.
ln certain space missions it is desirable to obtain shortduration impulsive thrust for rapid maneuvering. It is also desirable to have relatively long-duration low thrust available for efficient long-range operation. Electric propulsion systems serve the latter purpose but are not adequate for maneuvering, since the weight of the required electrical generating system would be prohibitive.
lt is, therefore, a primary object of this invention to combine an electrical propulsion device with a chemical rocket, with the chemical rocket being utilized for short duration, high-thrust maneuvering purposes.
It is a further object of this invention to provide a combined chemical and electrical propulsion device with one or more of the fuels for the chemical rocket being utilized jointly in 'both propulsion devices.
These and other objects of this invention will bec me readily apparent from the following detailed description of the drawing which illustrates a schematic arrangement of a type of compound propulsion system of this invention.
Referring to the FIGURE, a fuel storage tank containing, for example, lithium, is indicated at ld. The lithium is used as a common fuel in both the rocket propulsion unit l2 and the electric propulsion unit le. The electrical propulsion unit ld eventually obtains its power through a suitable generator (referred t lhereinafter at 54) which generator in turn receives power from a combined primary power circuit lo and a secondary power circuit l. The propulsion unit 14 is illustrated by example as a bombardment ion engine out may readily take the form of an arc jet (which may accelerate hydrogen received from the rocket source), a magneto-hydrodynamic accelerator or other ion engine. The lithium from the storage tank lill is pumped by one or more pumping units Ztl and 22 into the primary circuit lo through a suitable nuclear reactor Zfi. The nuclear reactor, which may be of any well-known type, adds heat to the liquid lithium and discharges the heated lithium from a line 26. Suitable valves 28 and Sli control the llow of lithium into a heat exchanger coil 34- so that the lithium, in fact, circulates from the nuclear reactor 2d to the heat exchanger coil 34 and then back to the reactor for added heating. The heat exchanger receives flow of a suitable working liquid (for example, a liquid metal) from a pump to and an inlet line 32. This liquid flows in the secondary circuit l. The liquid picks up heat in the heat exchanger and discharges the heated working iluid into a line 4d and a suitable turbine 46. Exhaust from the turbine i6 passes to a suitable radiator 48 for the release of excess heat energy. The exhaust from the radiator passes through a line Sil and back to the pump dll.
It should be noted that the working liquid is vaporized in the heat exchanger, and after passing through the turbine tle is again condensed in the radiator d8. The turbine 46 drives an electric generator 5d which in turn provides the electrical energy for the electrical propulsion unit ld. The propulsion particles, which are accelerated rice out of the exhaust of the propulsion unit 14 by electrical means, comprise lithium ions which are supplied via the line 6l?. A valve 62 leading from the primary circuit 16 expands a very minute portion of lithium and directs it to the electrical propulsion unit le, which for example, may be a bombardment ion engine. The lithium is ionized in the ion engine ld and the lithium ions are accelerated in the ion engine ld, thus providing specific impulses in the range from 2,000 to 20,000 seconds. The major portion of the lithium lremains in the primary circuit.
When short-duration impulsive thrust is desired, a relatively large amount of lithium can be `directed from the primary circuit lo through the valve .ltl leading to the line 72. The line 72 leads to the combustion chamber of the chemical rocket l2. The chemical rocket when in loperation is also fed fuel and oxidizer (for example, hydrogen and fluorine) from respective containers or tanks '74 and 76. A suitable pump 73 and valve S0 are provided for the hydrogen which is fed through the line 32, while .a pump @d and valve S6 conduct the ow rof fluorine to the line Each of the lines '72, E2, and d4 conducts one of the three propellants which comprise the combustion products for the rocket l2.
Thus, for very high thrust of short duration, the tripropellant rocket gives a very high, specific impulse. If further energy is desired, it may be feasible to connect the hydrogen and fluorine `tanks in any suitable manner to the nuclear reactor, as schematically illustrated lby the dotted lines and 92. Thus, the chemical propellants would dl be pre-heated before being introduced into the rocket combustion chamber.
As a result of this invention, both high-thrust and lowthrust operation is readily achieved. The `fuel inventory for ferrying operations is substantially reduced. ln addition, less cryogenic tanlsage is required than for an ordinary hydrogen-lluorine propellant system. Of further importance is the fact that a portion of the chemical rocket propellant, formerly charged off to payload, may now be used as electrical propulsion fuel. Furthermore, the continual replenishment of lithium in the closed-loop primary circuit will alleviate the problem of poisoning of the reactor coolant. ln addition, lithium has a low-neutron absorptive quality which makes it acceptable to nuclear heating without contamination. Finally, very high speciiic impulse is achieved in the chemical rocket, particularly if the nuclear reactor temperatures are such that the lithium is introduced in the vapor state.
Although one embodiment of this invention has been illustrated and described herein, it Will be apparent that various changes may he made in the construction and arrangement of the various parts without departing from the scope of the novel concept.
What it is desired by Letters Patent is:
l. A compound propulsion unit including a rocket, means for supplying a plurality of propulsion ingredients to said rocket, an electrical propulsion device and means for conducting one of said ingredients to said electrical propulsion device for acceleration therein.
2. A compound propulsion unit including a rocket, means for supplying a plurality of propulsion ingredients to said rocket, an electrical propulsion device including means for accelerating propellant therein, and means for conducting one of said ingredients to said electrical propulsion device for supplying the propellant to be accelerated.
3. A compound propulsion unit including a rocket, a plurality of propulsion ingredients including a source of lithium, means for supplying said ingredients to said rocket, an electrical propulsion device, and means for conducting lithium from said source to said electrical propulsion device for acceleration therein.
4. A compound propulsion unit comprising a rocket device and an electrical propulsion device, and means for supplying at least one ingredient as a common propulsive ingredient to both said devices.
5. A compound propulsion device including a rocket, sources of three propulsive ingredients, means for conducting said ingredients to said rocket for reaction therein, a nuclear heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of one of said ingredients to said electrical propulsion device for acceleration therein.
6. A compound propulsion device including a rocket, sources of a plurality of propulsive ingredients including an element which is readily ionized, means for conducting said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an ion propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of said element to said ion propulsion device for ionization and subsequent acceleration.
7. A compound propulsion device including a rocket, a plurality of sources of different propulsive ingredients, means for conducting said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conductin'J a relatively small portion of one of said ingredients to said propulsion device for use as a propellant.
8. A compound propulsion device including a rocket, a plurality of sources of different propulsive ingredients, means for conducting selective amounts of said ingredients to said rocket for reaction therein, a heat source, means for converting heat energy from said source into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a relatively small portion of one of said ingredients to said electrical propulsion device for acceleration therein.
9. A compound propulsion system comprising a first cycle, said cycle having a first working fluid, a first path for circulating said first working fluid, a source or" heat for adding energy to said Working fluid, a heat exchange unit receiving said working fluid, a second cycle including a second working fluid, means connecting said second cycle to said heat exchanger means to extract energy therefrom, means in said second cycle for converting the energy from said second worldng fluid into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, means for conducting Working fluid from said first cycle to said electrical propulsion device, and a rocket receiving a portion of said first Working fluid for use as thrust producing material.
10. A compound propulsion system comprising a first cycle, said cycle having a first working fluid which is readily ionized, a first path for circulating said first Working fluid, a source of heat for adding energy to said worL ing fluid, a heat exchange unit receiving said Working fluid, a second cycle including a second Working fluid, means connecting said second cycle to said heat exchange means to extract energy therefrom, means in said second cycle for converting the energy from said second Working fluid into electrical energy, an ion propulsion device receiving electrical energy from said converting means, means for conducting Working fluid from said first cycle to said ion propulsion device for supplying the ions to be i accelerated, a rocket power plant, a plurality of sources of propulsive ingredients for said rocket and means for conducting at least a portion of said first Working fluid to said rocket for reaction with said ingredients.
1l. A compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source heat in said first cycle for heating said one ingredient, means for extracting heat energy from said one ingredient, a second cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, a propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device to provide a propellant therefor.
l2. A compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source of nuclear heat in said first cycle for heating said one ingredient,
leans for extracting heat energy from said one ingredient,
a second closed cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said iluid into electrical energy, an ion propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device for acceleration therein.
f3. A compound propulsion system including a rocket, sources of propulsion ingredients comprising hydrogen, iluorine and lithium, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of lithium from one of said sources, a source of nuclear heat in said first cycle for heating said lithium, means for extracting heat energy from said heated lithium, a second cycle including a working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, a bombardment ion propulsion device receiving electrical energy from said converting means, and means conducting a portion of said lithium to said propulsion device for acceleration therein.
14. A compound propulsion system including a rocket, sources of three ingredients, means for conducting said ingredients for reaction in said rocket, a first cycle receiving flow of one of said ingredients, a source heat in said first cycle for heating said one ingredient, means for extracting heat energy from said one ingredient, a second closed cycle including a Working fluid receiving energy from said extracting means, means for converting energy in said fluid into electrical energy, an electrical propulsion device receiving electrical energy from said converting means, and means conducting a portion of said one ingredient to said propulsion device for providing a thrustproducing material for said device.
References Cited in the file of this patent The lon Rocket Engine-a Likely Power Source for That Trip to Mars, by Donald L. Eschner, SAE Journal, August 1958, pages 30 to 32,
Dynamic Analysis of a Nuclear Rocket Engine System, by Bernard R. Felix and Richard J. Bohl, ARS Journal, November 1959, No. 11, vol. 29, pages 853 to 862.
Space/Aeronautics, March 1960, pages -54.

Claims (1)

1. A COMPOUND PROPULSION UNIT INCLUDING A ROCKET, MEANS FOR SUPPLYING A PLURALITY OF PROPULSION INGREDIENTS
US87394A 1961-02-06 1961-02-06 Compound propulsion system Expired - Lifetime US3110154A (en)

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3246466A (en) * 1962-02-09 1966-04-19 Gen Motors Corp Solid-liquid propellant rocket
US3528245A (en) * 1968-05-27 1970-09-15 Lawrence R Sitney Combined radioisotope power and propulsion system
US5636512A (en) * 1994-10-14 1997-06-10 Aerojet General Corporation Nuclear rocket feed system incorporating an auxiliary power cycle
US6457306B1 (en) * 1998-06-15 2002-10-01 Lockheed Martin Corporation Electrical drive system for rocket engine propellant pumps
US6876714B2 (en) * 2000-09-28 2005-04-05 Carlo Rubbia Device for heating gas from a thin layer of nuclear fuel, and space engine incorporating such device

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3246466A (en) * 1962-02-09 1966-04-19 Gen Motors Corp Solid-liquid propellant rocket
US3528245A (en) * 1968-05-27 1970-09-15 Lawrence R Sitney Combined radioisotope power and propulsion system
US5636512A (en) * 1994-10-14 1997-06-10 Aerojet General Corporation Nuclear rocket feed system incorporating an auxiliary power cycle
US6457306B1 (en) * 1998-06-15 2002-10-01 Lockheed Martin Corporation Electrical drive system for rocket engine propellant pumps
US6876714B2 (en) * 2000-09-28 2005-04-05 Carlo Rubbia Device for heating gas from a thin layer of nuclear fuel, and space engine incorporating such device

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