United States Patent [19] [11] Patent Number: 4,663,932 Cox [45] Date of Patent: May 12, 1987

[54] DIPOLAR FORCE FIELD PROPULSION Primary Examiner-Louis J. Casaregola SYSTEM Attorney, Agent, or Firm-—Daniel J. Meaney, Jr. [76] Inventor: James E. Cox, 5455 Romaine St., Los [57] ABSTRACT Angeles, Calif. 90038 A dipolar force ?eld propulsion system having a alter [21] Appl. No.: 401,526 nating electric ?eld source for producing electromotive lines of force which extend in a ?rst direction and [22] Filed: Jul. 26, 1982 which vary at a selected frequency and having an elec tric ?eld strength of a predetermined magnitude, a [51] Int. Cl.4 ...... F03H 5/00 source of an alternating magnetic ?eld having magnetic [52] US. Cl...... 60/200.1; 60/202; lines of force which extend in a second direction which 3l3/359.l; 315/5.4l is at a predetermined angle to the ?rst direction of the [58] Field of Search ...... 60/202, 203.1, 200.1; electromotive lines of force and which cross and inter 3l3/359.1, 361.1, 362.1; 3l5/lll.01, 5.41, 5.42 cept the electromotive line of force at a predetermined ‘ [56] References Cited location de?ning a force ?eld region and wherein the frequency of the alternating magnetic ?eld substantially U.S. PATENT DOCUMENTS equal to the frequency of the alternating electric ?eld 3,095,163 6/1963 Hill ...... 244/12 and at a selected in phase angle therewith and wherein 3,322,374 5/1967 King 244/62 the magnetic ?eld has a ?ux density which when multi 3,324,316 6/1967 Cann 310/11 plied times the selected frequency is less than a known 3,334,022 9/1967 Eckert ...... 313/63 characteristic ?eld ionization potential limit; a source of 3,353,354 11/1967 Friedman et al. 60/203.l neutral particles of matter having a selected dipole char 3,371,490 3/ 1968 Haslund ...... 60/202 3,505,550 4/1970 Levoy et a1. 313/63 acteristic and having a known characteristic ?eld ioni 3,527,055 9/1970 Rego ...... 60/224 zation potential limit which is greater than the magni 3,662,554 5/1972 Broqueville ...... 60/202 tude of the electric ?eld and wherein the dipoles of the 3,678,306 7/1972 Garnier et al. . 310/11 particles of matter are capable of being driven into 3,735,591 5/1973 Burkhart 60/202 cyclic rotation at the selected frequency by the electric 3,866,414 2/1975 Bahn ...... 60/202 ?eld to produce a reactive thrust, a vaporizing stage OTHER PUBLICATIONS which vaporizes said particles of matter into a gaseous state at a selected temperature, and a transporting sys Jahn, R. 6., Physics of Electric Propulsion, tem for transporting the vaporized particles of matter McGraw-Hill, 1968, pp. 196-198. into the force ?eld de?ned by the crossing electromo Cox, J. E., “Electromagnetic Propulsion without Ioni tive lines of force and the magnetic lines of force. zation”, ATAA/SAE/ASME 16th Joint Propulsion Conference Hartford, Conn., 1980. 21 Claims, 53 Drawing Figures

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560%“? a E j/é/l// 7274/; | 5:27‘??? ?/izv/r 1 15 4,663,932 1 2 are engines or propulsion systems use an electric arc to DIPOLAR FORCE FIELD PROPULSION SYSTEM I heat a propulsion gas which is then passed to a standard rocket nozzle to provide thrust. Electric arc propulsion BACKGROUND OF THE INVENTION systems are capable of generating considerable amounts 1. Field of the Invention of thrust and have speci?c impulse thrust greater than The present invention relates in general to a system those of chemical engines. However, the speci?c im and method for producing a reactive force on an aero pulse thrust levels of electric arc engines are lower than space vehicle to cause rotation or vibration of dipoles of the speci?c impulse thrust of electrostatic propulsion neutral particles having a selected electrical dipole systems. Typical electrothermal or electric arc propul characteristic and more particularly to a dipolar force 0 sion systems are disclosed in a book by Robert Jahn ?eld propulsion system for a aerospace vehicle utilizing entitled “Physics of Electric Propulsion” , McGraw Hill, a crossed electric E ?eld and a magnetic B ?eld for 1968. establishing a spatial force ?eld region wherein a con Another known type of spacecraft propulsion system trol means establishes a predetermined spatial and time is generally referred to as electromagnetic propulsion relationship between the alternating electric ?eld, alter systems which includes magnetohydrodynamic (MHD) nating magnetic ?eld and dipole rotation for a selected thruster or magnetoplasmadynamic (MPD) thruster. frequency to produce an reactive thrust. The MHD or MPD thrusters are capable of providing 2. Description of the Prior Art both high thrust density and high speci?c impulse. The In spacecraft propulsion systems, the use of chemical MHD or MPD thrusters utilize a propellant gas which rocket engines which use combustion of chemical fuels is ionized to form a plasma which is accelerated by to produce a large amount of thrust necessary to lift magnetic and electric ?elds and is then passed through loads from the earth’s surface is known. The term an expansion nozzle to provide thrust. In a MHD “thrust” is de?ned to mean the amount of propulsive thruster or MPD thruster, the plasma is a body of gas force developed by a propulsion engine and is typically which comprises a substantial number of free electrons related to a rocket engine that is used for boosting a and ions, but has an overall neutral electrical charge space vehicle from the earth’s surface into orbit. The providing a plasma which is electrically conductive. known space propulsion systems must have suf?cient The known MHD or MPD thrusters utilize the interac thrust to raise the spacecraft from the earth's surface tion of magnetic ?elds produced by electrical currents and that thrust must be greater than the weight of the vehicle to be lifted from the earth’s surface and placed and conductors on the spacecraft with an electrically into orbit. conductive environment to produce a reaction thrust. Once the spacecraft has been boosted into space or Several typical MHD thrusters or MPD thrusters are orbit, the required spacecraft thrust is minimal com disclosed in U.S. Pat. No. 3,735,591; U.S. Pat. No. pared to the thrust required for lifting the vehicles from 3,662, 554; U.S. Pat. No. 3,535,586; U.S. Pat. No. the earth’s surface. 35 3,505,550; U.S. Pat. No. 3,371,490; U.S. Pat. No. When a spacecraft is in space or in orbit, it is desirable 3,527,055; U.S. Pat. No. 3,343,022 and U.S. Pat. No. to have the ratio of thrust produced to the rate of con 3,322,374. sumption of the fuel to be high as possible and this is It is also known in the art to combine a jet propulsion generally referred to as “speci?c impulse.” In space or power plant with a magnetoplasmadynamic generator - in orbit, a spacecraft propulsion system having a high 40 to produce a hybrid propulsion system. One such pro “speci?c impulse” capability is highly desirable. pulsion system is disclosed in U.S. Pat. No. 3,678,306. Thus, it is known in the art of space propulsion sys The use of a controlled fusion device which generates tems that the chemical rocket engines are capable of electrical energy utilizing an ionized gas plasma in a providing the requisite thrust necessary to lift large space propulsion system is disclosed in U.S. Pat. No. payloads from the earth’s surface into orbit. 45 3,324,316. Once the spacecraft and its payload is in orbit, it is The design of plasma propulsion systems having spe-' desirable for the spacecraft propulsion system to be able cial magnetic ?elds for controlling the speci?c impulse to change the orbit, speed and/or orbital position of the characteristics of the plasma propulsion device is dis spacecraft with a “speci?c impulse” propulsive force. closed in U.S. Pat. No. 3,191,092. A number of propulsion systems have the capacility 50 In addition to the above described space propulsion of providing “speci?c impulse” thrust for changing the systems, the inventor of the present application pub orbit, speed and/ or orbital position of a spacecraft. lished an article entitled “Electromagnetic Propulsion One such known propulsion engine is generally re Without Ionization” which appeared in the AIAA/SA ferred to as “electrostatic propulsion systems” wherein E/ASME 16th Joint Propulsion Conference which was the thrust is created by electrostatic acceleration of ions held on June 13, 1980 to July 2, 1980 in Hartford, Conn. created by an electron source in an electric ?eld. Elec The paper presented at the above-described 16th Joint trostatic propulsion systems have very high speci?c Propulsion Conference disclosed the concept of elec impulse but have limited thrust capacilities. Where an tromagnetic propulsion without ionization. Speci?cally, excessively large amount of thrust is required, the size the paper disclosed that when an alternating electric and weight of the electrostatic propulsion systems be ?eld is applied to a polarized or polarizable material, the come excessive. Examples of known electrostatic pro dipole of the material can be made to rotate at high pulsion systems are disclosed in U.S. Pat. No. 3,866,414; frequency. If an alternating and synchronized magnetic U.S. Pat. No. 3,537,266 and U.S. Pat. No. 3,095,163. ?eld is supplied at right angles to the electric ?eld, a Electrostatic propulsion systems include electrostatic Lorentz force is generated which propels the dielectric engines such as ion engines as evidenced by the above 65 ?uid without the necessity for ionization and the conse described United States patents. quential energy losses arising from the ionization pro Another type of known space propulsion systems are cess. The thrust so generated is proportional to the generally referred to as “electric arc” engines. Electric polarization, the frequency of the dipole rotation and 4,663,932 3 4 the magnetic ?eld strength. The propellant selected for aggregate weight of the propellant is twenty to thirty use as the polarizable material is characterized by hav times the aggregate weight of payload to be lifted from ing a high permanent molecular dipole movement-to the earth’s surface and to be placed into orbit. mass ratio and is accelerated by Lorentz forces to useful The known electrostatic propulsion systems or ion exit velocities. A spacecraft having the induced dipole propulsion systems and the electric arc propulsion sys electromagnetic propulsion system is accelerated by tems are limited to operation in the vacuum of space and Newton’s Third Law of Motion, or the reactive thrust provide satisfactory high “speci?c impulse” thrust but principal. are unsatisfactory for providing a substantial amount of thrust as required for liftoff of a spacecraft. In order to SUMMARY OF THE INVENTION generate suf?cient thrust for lifting of a payload from The present invention relates to a novel, unique and the earth’s surface into orbit, the size, weight and com improved dipolar force ?eld propulsion system. In the plexity of the spacecraft propulsion systems limit the prefered embodiment of the present invention, the dipo desirability of using the same in such a spacecraft and to lar force ?eld propulsion system includes means for provide the necessary “speci?c impulse” thrust re generating an alternating electric ?eld having its elec quired for changing orbital speed, direction and/or tromotive lines of force extending in a selected direc position. tion. The alternating electric ?eld varies at a selected In the known MHD or MPD propulsion systems, it is frequency and has an electric ?eld strength of a prede necessary to provide suf?cient energy in order to ionize termined magnitude. A means for generating a rotating the propellant. The energy required to ionize the pro or alternating current magnetic ?eld is provided with 20 pellant, which is typically easily ionizable gas, reduces the electromagnetic lines of force extending in a direc the overall ef?ciency of the propulsion systems and tion which is at a selected angle relative to the selected requires substantial cooling systems in order to obtain direction of the electromotive lines of force. The elec the proper operating conditions to increase the reliabil tromagnetic lines of force cross and intercept the elec ity and lifetime of such propulsion systems. tromotive lines of force at a predetermined location to 25 In the known MHD propulsion systems, it is neces de?ne a spatial force ?eld region. The frequency of the sary to include a seeding propellant which is injected alternating magnetic ?eld is substantially equal to the into the hot gases wherein the seeding material is gener selected frequency of the alternating electric ?eld and ally a low ionization potential compound such as, for has a predetermined phase angle therebetween. The example, potassium or cesium. magnetic ?eld has relatively high flux densities in the The present invention overcomes the inherent limita order of a fraction of one tesla or more. The propellant tions and problems associated with the known space material is a source of neutral particles of matter having stabilized, electrically induced or permanent dipoles craft propulsion systems. having preselected internal breakdown characteristic One advantage of the present invention is that a which is greater than the magnitude of the applied elec unique, novel and improved dipolar force ?eld propul tric ?eld. The dipoles of the matter are capable of being sion system utilizes a propellant in the form of a vapor driven into controlled rotation at the selected frequency ized gaseous matter which is in an unionized state. The by the alternating electric ?eld and crossing the alter reactive thrust can be developed by controlling the nating electromagnetic ?eld. A means for vaporizing operating characteristics of the crossed alternating elec the matter into a gaseous state yet below the thermal 40 tric ?eld and alternating current magnetic ?eld which ionizational level thereof and for transporting the va de?nes the spatial force ?eld region adapted to have the porized material in the gaseous state into the spatial vaporized polarizable material, which is not ionized, force ?eld region which is de?ned by the crossed elec transported thereto. tromotive lines of force and electromagnetic lines of Another advantage of the present invention is that force. The alternating cross ?eld formed by the electro 45 the electronic excitation level of the polarizable dipole motive lines of force and the electromagnetic lines of material can be increased either prior to or after the force cause the dipoles to rotate at the selected fre vaporization thereof into a gaseous state to improve the quency and to produce an acceleration force which is operating ef?ciency of the dipole force ?eld propulsion substantially normal to the plane of the electromotive system. and the electromagnetic lines of force to produce a A yet further advantage of the present invention is reactive thrust. A control means which is operatively that a means are provided for generating a reactive coupled to the means for generating the alternating thrust which is adapted for propelling a spacecraft from electric ?eld and to the means for generating an alter the earth’s surface, into orbit and subsequently into nating magnetic ?eld and which is responsive to the space wherein the initial thrust and speci?c impulse can dielectric properties of the vaporized matter located in be provided which are equal to or greater than those the spatial force ?eld region having a well-de?ned rela provided by the known spacecraft propulsion systems. tion between the electric ?eld, electromagnetic ?eld A still yet further advantage of the present invention and dipole orientation for any selected frequency. is that a unique and novel method for propelling a The known prior art space propulsion systems have spacecraft with a reactive thrust derived from using a inherent limitations in terms of providing suf?cient propellant comprising neutral particles of matter having thrust based upon the mass and weight of a propulsion an electric dipole characteristic and a breakdown char system on the earth’s surface in order to lift a spacecraft acteristic which is greater than the magnitude of an from the earth’s surface and to place the same into orbit applied electric ?eld. or space. The primary limitation can be characterized A still yet further advantage of the present invention speci?cally by the mass of propellant required, by 65 is that the phase angle between the alternating electric weight, to the mass of payload to be placed into space. ?eld and the alternating magnetic ?eld can be varied so Known spacecraft propulsion systems utilizing a chemi as to control the magnitude of the reactive thrust pro cal engine generally require propellants wherein the duced by the rotation of the dipoles of material. 4,663,932 5 6 A still yet further advantage of the present invention A still yet further advantage of the present invention is that a unique and novel spacecraft having a “X-wing” is that the dipolar force ?eld propulsion system pro con?guration which includes means for exciting the vides a method for accelerating neutral particles of energy level of the polarizable or dipole material to an matter without the creation of an ionized or plasma excited level wherein the excited atoms of material state. As a result, a force density can be established in a when used as a propellant is capable of rendering both gas over a large distance without the restriction of skin thrust and speci?c impulses of thrust at controlled lev depth or Debye lengths. This property, in addition to els which is directly proportional to the excited state of the recycling of excitation radiation and rebounding the gaseous material. collision processes, offers the potential for the creation A stillryet further advantage of the present invention of a class of more ef?cient propulsion systems for aero is that the propulsion ef?ciency of the inductive dipolar space vehicles. force ?eld propulsion system increases as a function of A still yet further advantage of the present invention mass ratio and can approach acceptable operating ef? is that the dipolar force ?eld propulsion system operates ciencies. at lower jet velocities at large volumetric mass flow A still yet further advantage of the present invention rates. Therefore, greatly reduced noise levels are possi is that the excitation power can be a microwave source ble. The ?eld extends beyond the structure of the aero having a selected frequency which can be located either space vehicle itself to move the mass and thereby per internal or external to the spacecraft. Under certain mits operation in more rari?ed environments, such as idealized conditions, the frequency of the microwave higher altitudes, where pressures and temperatures are radiation source can be precisely selected relative to the lower, permitting high Rydberg excitation states to frequency of rotation or absorption characteristics of exist. the dipole material such that substantially all of the A still yet further advantage of the present invention microwave radiation transmitted to the spacecraft from is that the aerospace vehicle’s structure can be designed an external source can be fully absorbed without re?ect such that electronic control of thrust direction can be 25 ing any part thereof. achieved which can be changed instantly with’ the flick A still yet further advantage of the present invention of a switch. The use of electronic switching can provide is that a MHD electric power generator can be utilized increased maneuverability and faster response reaction on board of the spacecraft to generate the electrical times. Further, electric power can be provided to the energy required to produce the electric and magnetic aerospace vehicle by super conductive radio frequency ?eld which is utilized to establish the spatial force ?eld generators or by the process of magnetohydrodynam area for producing the reactive thrust from the interac ics, or by beamed power from ground or orbiting power tion of the crossed electric ?eld and magnetic ?eld on stations. The existance of an excited gas ?eld around the the induced dipole material occupying this region. vehicle can be used in absorbing offending external A still yet further advantage of the present invention microwave beams as well. is that cryogenic cooling of superconductive magnets A still yet further advantage of the present invention can produce extremely high, dense magnetic ?elds in is that it appears that the ejection of electromagnetic the order of one tesla or more. By controlling this ?eld momentum will provide for some capability of produc strength as well as the switching rate or frequency of ing a small thrust in the vacuum of space itself. the magnetic ?elds, both the ef?ciency of the dipole A still yet further advantage is that the apparatus and propulsion system and the amount of thrust produced method disclosed herein can be used for accelerating can thereby be determined. particles of matter and have wide potential applications A still yet further advantage of the present invention for isotope separations, particle beam devices, chemical is that a electromagnetic propulsion system utilizing the accelerators, nuclear devices, molecular beam devices teachings of this invention can produce in the order of 45 and the like. 106 pounds of thrust level using known or anticipated power sources and known superconductive magnetic BRIEF DESCRIPTION OF THE DRAWINGS materials. ' These and other objects and advantages of the inven A still yet further advantage of the present invention tion, together with the various features and advantages, is that a shuttle aircraft can be designed utilizing a hy 50 can be readily understood from the following more brid propulsion system wherein the lift and thrust are detailed description of the prefered embodiment taken accomplished by aerodynamic, electromagnetic and in conjunction with the accompanying drawing in chemical rocket propulsion systems so as to exploit the which: characteristics of each system at an optimum time dur FIG. 1 is a diagramatic representation of electrodes ing trajectory of spacecraft travel. 55 for establishing an alternating electric ?eld in the pres A still yet further advantage of the present invention ence of a alternating magnetic ?eld to de?ne a spatial is that the spacecraft propulsion system disclosed herein force ?eld region for inducing rotation of a dipole to is capable of utilizing the earth’s atmosphere as a propel produce a reactive thrust; lant having an appropriate excitation level required in FIG. 2 is a vector diagram of the Lorentz forces order to initiate the polarization dipole reactive thrust acting on each charge at the end of a dipole; generation for purposes of lifting a spacecraft from the FIG. 3a is a diagramatic representation of the ellipti earth’s surface into orbit. Once the spacecraft has been cal orbit generated by an electron relative to its nucleus propelled into orbit and then into deep space, the dipole showing the aphelion point and the perihelion point of force ?eld propulsion system is capable of utilizing the orbits; matter in interstellar space as a propellant without the 65 FIG. 3b is a graph of the charge density of the atom necessity of ionizing the same in order to develop the plotted as a function of electron distance in Bohr radii reactive thrust necessary to propel a spacecraft into (R0) depicting the variance in charge density as a func deep space. ' tion of radius of the orbit;