0001
`
`Ossia, Inc.
`Exhibit 1011
`PGR2016-00023
`U.S. Patent No. 9,124,125
`
`

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`March 25, 1959 '
`
`w, c. BROWN ET AL
`
`3,434,578
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`MICROWAVE T0 DC CONVERTER
`
` Fi1ed May
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`1965
`
`Sheet
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`of 5
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` FIG. 7
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`0002
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`

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`Mafch 25, 1969
`
`w, c, BRowN ET AL
`
`MICROWAVE T0 DC CONVERTER
`
`Filed May 5. 1965
`
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`0003
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`0003
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`

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`United States Patent Oflice
`
`3,434,678
`Patented Mar. 25, 1969
`____________________________________________
`1
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`2
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`3,434,678
`MICROWAVE TO DC CONVERTER
`William C. Brown, Weston, Mass., Roscoe H. George,
`West Lafayette, Ind., and Neil I. Heenan, Needham,
`and Roger C. Wonson, Beverly, Mass., assignors to
`Raytheon Company, Lexington, Mass., a corporation
`of Delaware
`
`U.S. Cl. 244-1
`
`Filed May 5, 1965, Ser. No. 453,415
`Int. Cl. B64g J/00
`3 Claims
`
`ABSTRACT OF THE DISCLOSURE
`A combined antenna and conversion mechanism for re-
`ception of beamed high frequency electromagnetic energy
`in space including a large array of unidirectional current
`semiconductor rectifier devices. A self-supporting space
`vehicle utilizing the rectified DC electrical energy for pro-
`pulsion is disclosed in an illustrative embodiment.
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`readily adaptable to the convenient radiation of power
`to remote points without the utilization of wires. The pre-
`ferred wavelengths are of the order of 5 or 10 centimeters
`to provide eflicient focusing with existing transmitting
`antenna systems which may be maintained at a reasonable
`size. An illustrative device of the superpower high fre-
`quency microwave generators operative in the desired
`band is the so-called Amplitron which is an amplifier
`having a broad bandwidth and excellent performance
`characteristics for the focusing of the ‘beam. Such devices
`are capable of producing 15 or 20 kilowatts of average
`continuous wave power in the neighborhood of 10 centi-
`meters in wavelength with capabilities expected in the
`region of 500 kilowatts or more average power with 50
`megawatts peak power. A complete description of such
`devices may be had by referring to Patent No. 2,933,723
`issued Apr. 19, 1960 to William C. Brown and assigned
`to the assignee of the present invention.
`With microwave energy capable of being generated and
`directed over longer distances conversion of such high
`frequency electromagnetic energy is of paramount con-
`cern. One conversion mechanism in the prior art involves
`direct conversion of such energy into heat which may
`then be utilized directly or indirectly for propulsion or
`generation of flight-producing forces. Examples of such
`devices for heat energy exchange as Well -as space vehicles
`utilizing such energy may be noted in Patent No. 3,174,-
`705, issued Mar. 23, 1965, to D. Schiff et a1., as well as
`U.S. Letters Patent No. 3,083,528,
`issued Apr. 2, 196-3
`and No. 3,114,517, issued Dec. 17, 1963, to William C.
`Brown. The heat exchanger method of conversion of
`electromagnetic energy into useful power is limited by
`the overall efficiencies of approximately 25 percent in the
`conversion of heat into mechanical or electrical work. De-
`sirable, therefore, would be the direct rectification of the
`high frequency electromagnetic energy into low frequency
`electrical energy for the operation of many useful aero-
`space devices as well as systems.
`The present invention has for its primary object the
`conversion of high frequency electromagnetic energy in
`the microwave region directly into low frequency elec-
`trical energy.
`
`A further object of the present invention is the pro-
`vision of a combined nondirectional receiving antenna and
`microwave electromagnetic energy to low frequency elec-
`trical energy conversion means in a unitary structure.
`A still further object of the present invention is a pro-
`vision of a new and novel combined nondirectional re-
`ceiving antenna and microwave to DC energy converter
`for aerospace applications.
`Another object of the present invention is the provision
`of a new and novel nondirectional receiving antenna and
`microwave to DC energy converter having a high degree
`of efliciency.
`Still another object of the present invention is the pro-
`vision of a new and novel aerospace vehicle with non-
`directional receiving antenna and microwave to DC ener-
`gy converter means with said vehicle being capable of
`being supported by its own energy generation means at a
`distance spaced apart from the power generation means.
`In accordance with the teachings of the present inven-
`tion,
`the above and other objects are achieved by the
`employment of eflicient unidirectional microwave power
`rectifiers and dipole antenna means. Such rectifying de-
`vices, while being individually limited in power-handling
`capabilities, normally in the order of fractions of watts,
`have been found to be highly efficient means for the recti-
`fication of microwave power when assembled in large
`numbers in various arrays. -It is interesting to note that
`the observed collective efliciency was on the order of
`40 to 70 percent. In an illustrative embodiment, point-
`0004
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`The present invention relates in general to the transfer
`of energy by means of an electromagnetic wave beam and
`more particularly to interception and rectification of such
`energy into low frequency electrical DC energy with a
`high degree of efiiciency.
`Improved technology in the field of microwave energy
`generation at superpower levels has resulted in the realiza-
`tion of electrical energy transmission over considerable dis-
`tances for remote energization of devices or vehicles with-
`out the aid of wires. The transmission of microwave elec-
`tromagnetic energy into space has been commonly em-
`ployed in the radar pulse echo systems for the detection
`and orientation of desired objects within a predetermined
`scanning range of a transmitting antenna. Beams of a
`similar nature may now be employed for other useful
`purposes and the advantages attendant the utilization of
`electromagnetic energy in the microwave region in con-
`trast with other wavelengths may now be enumerated.
`Microwaves have been generally defined as high fre-
`quency radio waves whose wavelength is less than 30
`centimeters, with a lower wavelength limit on the order
`of 1 millimeter sometimes being applied to what is com-
`monly referred to as the “microwave region.” The superi-
`ority of high frequency microwaves is due in part to the
`fact-that it is generally desirable to focus the transmitted
`energy so as to achieve a high power density at a remote
`point or area with respect to a given power source. In
`accordance with the laws of optics, the sharpness of the
`microwave beam produced by a transmitting antenna
`varies as the ratio of antenna dimensions to the Wavelength
`of the transmitted energy. Therefore, for a given or de-
`sired power density or beam sharpness, a decrease in the
`wavelength of the transmitted energy permits a corre-
`sponding decrease in the dimensions of the antenna. From
`the standpoint of mechanical considerations, it is desir-
`able to employ small antennas and other components, and
`it
`is therefore advantageous to employ high frequency
`energy of very short wavelength. In addition, the difi‘icul-
`ties encountered in long wave transmission as a result of
`natural and man—made interference or noise do not occur
`with any appreciable significance at microwave frequen-
`cies. Further, in aerospace applications with considerable
`distances separating the transmitter at an earth or mother
`planet location and the employment of shorter wavelength
`beamed energy is preferred since longer wave signals will
`generallly be reflected at certain altitudes by reflecting lay-
`ers in the atmosphere.
`In view of certain losses due to absorption which may
`occur in the atmosphere, microwaves in the region having
`the approximate bounds of 2 and 30 centimeters are
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`3,434,678
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`contact semiconductor diodes were arranged in four arm
`bridge connected networks with the networks intercon-
`nected in various configurations such as series, parallel
`and series-parallel.
`In discussing aerospace applications, an additional prob-
`lem is encountered in the beaming of microwave energy
`to a remote point and the interception and utilization of
`such electrical energy. In such applications the advantages
`of a vehicle which may be maintained in space for inde-
`terminate periods of time without employing a local -fuel
`source are readily apparent. Such devices could readily
`provide communication networks, surveillance functions
`using radar techniques along with numerous other func-
`tions. The acapture of the beamed high frequency elec-
`tromagnetic energy raises the need for an efficient an-
`tenna means capable of intersecting the beam at high
`altitudes. Conventional
`techniques employed in micro-
`wave radar usage such as receiving antenna horns are
`capable of intersecting only a small portion of the beam
`energy and add considerable weight in applications in-
`volving heavier-than-air vehicles. In an exemplary em-
`bodiment of the invention a space vehicle, namely a heli-
`copter, is disclosed for either moving flight or a stationary
`location with self-supporting electrically operative propul-
`sion means. The semi-conductor diode rectifier arrays have
`been demonstrated to fulfill the receiving antenna func-
`tions as well as the electrical energy rectification means in
`a highly efficient manner. Such combined antenna and rec-
`tifier means has also assisted in reduction of the weight
`problem in airborne devices. Further, it has provided a
`nondirectional means for the interception of the micro-
`wave energy to thereby reduce the problems of focusing
`inherent in prior art directional horn type receiving an-
`tennas.
`With the above features, advantages and objects in mind
`the invention will now be described by reference to the
`following detailed description together with the accom-
`panying drawings in which:
`FIG. 1 is a perspective view of an illustrative diode
`rectifier;
`FIG. 2 is a schematic circuit diagram of a bridge con-
`nected diode network with dipole antenna means;
`FIG. 3 is a schematic circuit diagram of a plurality of
`bridge connected networks arranged in series;
`0
`FIG. 4 is a schematic circuit diagram of a parallel
`bridge connected network array;
`FIG. 5 is a perspective view of an illustrative embodi-
`ment of a combined antenna and rectifier array in a folded
`or rolled up configuration;
`FIG. 6 is a schematic circuit diagram illustrating the
`bridge connected diode array incorporated in the aero-
`space vehicle shown in FIG. 7;
`FIG. 7 is a schematic representation in elevation illus-
`trative of a heavier-than-air aerospace vehicle incorparat-
`ing the structure of the present invention;
`FIG. 8 is a perspective view of the aerospace vehicle
`embodiment as viewed from the under portion thereof;
`and
`FIG. 9 is an enlarged partialview in elevation of a por-
`tion of the illustrative embodiment shown in FIG. 8.
`FIG. 1 illustrates a point-contact semiconductor diode
`rectifier of the type employed in radar microwave receiver
`apparatus to rectify returned radar pulses. Any of the
`high burnout semiconductor diodes having high recti-
`fication characteristics are preferred and are commercially
`available, such as the 1N82 or 1N830. The rectifying junc-
`tion is formed by whisker element 2 contacting the semi-
`conductor element 4 respectively connected to leads 6 and
`8. Silicon is preferred over germanium for element 4
`because of its ability to operate at higher temperatures and
`thereby handle higher powers. Envelope 10 houses the
`rectifying elements and may be of a hermetically sealed
`dielectric material or combination metal and ceramic com-
`position. The inherent characteristic of such diode recti-
`0005
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`4
`fiers is that the microwave energy is intercepted and recti-
`fied in a unidirectional manner and the line 11 indicate
`pictorially the rays of the beamed electromagnetic micro-
`wave energy in a plane normal to the envelope. In FIG. 2
`a full-wave bridge connected diode network is illustrated
`with the forward direction of the rectified DC electric
`current indicated by the direction of the arrow symbols.
`The network shown consists of half-wave dipoles 20 and
`22 each terminated with a diode rectifier element 24 to
`27 in an arm of the bridge connected network. The di-
`pole elements 20 and 22 are of the half-wave configura-
`tion and may be spaced apart from each other a one-half
`wavelength at the frequency of the beamed electromag-
`netic energy.
`Referring now to FIG. 3, an array of bridge connected
`diode networks each with the half-wave dipoles are shown
`connected in series. Each network is referred to -by the
`numeral 30 and is similar in the bridge connections to the
`single element network shown in FIG. 2. The DC output
`of the collective rectified energy is coupled by means of
`terminals 32 and 33. In FIG. 4, a similar number of in-
`dividual bridge connected diode-dipole networks are
`shown connected in a parallel array. Each network is in-
`dicated by the numeral 40, and the output terminals are
`indicated as 41 and 42.
`Any number of diode-dipole networks may be pro-
`vided and in FIG. 5 such a multi-element array is illus-
`trated by mounting on a flexible material 50 which may
`be rolled or folded into any desired package or en-
`closed within a capsule to be launched and released at a
`predetermined point in space. Any flexible material which
`is pervious to electromagnetic energy is preferred. The
`total power desired would be the determining factor in a
`number of individual diode-dipole elements required. In
`this embodiment, the bridge connected networks 51 are
`connected in parallel to the output load ‘indicated by ter-
`minals 52 and 53, and representative measurements of
`electrical characteristics have shown that approximately
`five watts of DC electrical energy is realizable for each
`square foot of area of the combined antenna-rectifier.
`While the dipole elements 54 have been indicated in a
`particular array, it is within the scope of the invention to
`stagger the placement of such dipoles to increase the over-
`all efficiency of the antenna-rectifier.
`To further increase the DC powder output, the full-
`wave -bridge connected networks are preferably arranged
`with a plurality of diodes in series in each arm of the
`bridge. An illustrative schematic circuit diagram of such
`a configuration is shown in FIG. 6 wherein seven diodes
`60 are shown in each arm of the bridge circuit and are
`connected in series for a total of twenty-eight diodes in
`each bridge network. The dipole members will then be the
`substantially U-shaped end portions 61 at the ends of each
`brace of seven diodes.
`In the ‘illustration three such
`twenty-eight diode bridge networks are shown connected
`in parallel to terminals 62 and 63. This closer spacing
`and compact arrangement has been shown to be a source
`of improved power output and is capable of a high degree
`of reliability through the redundant nature of the parallel
`series connections within each bridge network. If one of
`the diode rectifiers fails to function the over-all -voltage_
`drop across this element would be divided among the six
`remaining diode rectifiers. If any of the -connecting wires
`between the diode elements should break, the adjacent
`arms of the other bridge assemblies would take the addi-
`tional load due to the close proximity of the respective
`arms to each other. In addition, it is possible to have a
`number of open connections or inoperative diodes dis-
`persed throughout the array without any serious impair-
`ment in performance.
`.
`In relation to the array concept to be hereinafter de-
`scribed it may be stated that within a six inch square area
`ten such individual bridge networks each containing
`twenty-eight diode rectifiers for a total of 280 diode rec-
`tifiers may be deployed in such a manner as to provide
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`3,434,678
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`maximum exposed area for each diode as well as the
`connecting leads. Such an arrangement will be hereinafter
`referred to as a “module” and a DC output in excess of
`fourteen watts has been measured for such a module. Any
`number of such modules could be connected provided for
`a desired power yield and this module concept readily
`lends itself to use in certain aerospace applications now
`to be described.
`In FIG. 7 a propelled type of space vehicle 70 is shown
`wholly supported ‘by means of the transfer and rectifica-
`tion of continuous wave electromagnetic energy via a
`microwave ‘beam 72. The source of the microwave energy
`which may be of the Amplitron type device as described
`-in the aforementioned issued Patent _No. 2,933,723 is
`indicated as 74. This energy is fed by waveguide means
`76 to a transmitting horn 78 to illuminate an ellipsoidal
`beam forming focusing antenna 80 for the transmission
`of the microwave beam 72. It will be appreciated by
`those skilled in the art that the representations of the
`microwave generation and transmitting antenna means
`are pictorial representations to illustrate the usage of the
`invention in diagrammatic form and the present invention
`is not
`limited to any particular source of microwave
`energy or transmitting antenna assembly.
`It may be
`stated the reflector of the antenna assembly is consider-
`ably larger than most of the reflectors of the prior art
`in order to focus a large amount of tlie microwave power
`at high altitudes for use in the transfer of energy to
`space vehicles. Such antenna assemblies may be partially
`supported in a large hollowed area on the earth’s sur-
`face or other convenient means of support.
`The space vehicle or helicopter 70 can be described as
`a main body member supporting antenna-rectifier means
`82 including a large number of the so-called modules
`connected together and rigidly supported in a planar
`parallel array. A motor 84 is supported ‘by the com-
`bined body member and the receiving antenna—rectifier
`means and actuates the rotor 86 of conventional design
`employed in such self-propelled hovering vehicles. The
`disclosed vehicle provides for the illumination of the
`planar array of the semiconductor diode dipole elements
`‘by the microwave beam and the direct conversion of the
`microwave power transmitted by the beam into usable
`electrical energy for the self-propulsion of the device
`without any local fuel supply being required.
`FIGS. 8 and 9 illustrate a space vehicle 82 comprising
`a plurality of the combined receiving antenna-rectifier
`module means for interception and rectification of the
`electromagnetic microwave
`energy beam emanating
`from an earth or mother planet source. A planar array
`of the antenna-rectifier modules is mechanically sup-
`ported by means of structural members 90 of any light-
`weight wood or metal. Insulators 91 positioned coexten-
`sive with the members 90 support the diode rectifier array
`and avoid interference with the receiving and electrical
`performance characteristics ‘by
`the structural support
`members. Carrying forward the module concept of 280
`diode rectifiers to provide an approximate power output
`of 14 watts,
`it was noted” that any number of such
`modules may be coupled together since the individual
`module outputs are relatively insensitive to a wide range
`of load resistances connected to the common output
`terminals. To achieve the desired electrical output of ap-
`proximately 120 volts and 250 watts of power, subgroups
`of four modules each were assembled and parallel con-
`nected with an approximate 30 volts availa-ble for each
`subgroup. Four such subgroups were series-connected
`to result in a total of 4,480 diode rectifiers or 16 modules
`assembled in a two foot square self-supporting planar
`parallel array structure. The individual diode rectifiers
`connected in each arm of the bridge network are indicated
`by the numeral 92. An exemplary module configuration
`would extend within the area delineated by the dotted lines
`and reference letter A on one side and similar dotted lines
`and reference letter B on the other side.
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`A motor 94 is connected to the DC side of the overall
`array and may be additionally supported by tu'bular mem-
`ber 95. A shaft and propulsion means consisting of rotor
`blades 97 provide for the upward lift of the overall
`vehicle for the self-supporting of same in space applica-
`tions. Additional structural support such as interlaced
`rigging 96 of a high tensile strength material such as
`nylon or steel wire, as well as bracing member 98, may
`be employed for strengthening of the body means to with-
`stand the vibrational
`forces and downwash from the
`propulsion means.
`In accordance with the well known technology of micro-
`wave transmission the combined array of diode rectifiers
`and propulsion means presents a specific load impedance
`which must be suitably matched to the transmitted micro-
`wave energy beam to result in maximum efliciency. In
`aerospace applications a mismatch of approximately ten
`to one may be evident. Matching of the load impedance to
`a value of approximately 377 ohms as the free space value
`will be provided by a plurality of coplanar parallel metal-
`lic rod members 99 disposed in a grating array in front
`of the diode rectifiers a predetermined distance. Rod mem-
`bers 99 are linearly disposed and extend in a similar di-
`rection as the assembled diode rectifiers. A selected frontal
`spacing of one-quarter of the wavelength of the micro-
`wave frequency being transmitted has been experimen-
`tally determined to be suitable for impedance matching
`purposes. An approximate spacing of two inches between
`the respective members was preferred for a selected
`microwave frequency of ‘2,450 megacycles. Each of the
`members 90 are provided with lateral sections 100 to sup-
`port the elongated bar members 101 which in turn main-
`tain the rod members 99 in the desired position. A tubu-
`lar member 102 of a lightweight metal may also be pro-
`vided to combine with the motor support member 95 for
`structural support.
`The combined antenna—rectifier array provides a source
`of electrical energy to render any space vehicle self-sup-
`porting. The diode rectifier elements when assembled in
`the antenna array have been found to -"be nondirectional
`with respect to interception of the beamed microwave en-
`ergy. This represents a large step forward in the utiliza-
`tion of high power microwave energy over the prior art
`horn-type receiving antennas which must be accurately
`focused and pointed in a particular direction for the re-
`ception of any energy. The connections between the re-
`spective members of the diode rectifier array and de-
`ployment in the parallel configuration serves to provide
`maximum exposed area. Such connections and in partic-
`ular the end loop portions adjacent the terminus of each
`arm of the bridge networks serves as an eflicient dipole
`for the interception of the microwave energy.
`Although it is not intended as a full explanation of the
`high degree of efficiency attained with the disclosed an-
`tenna-rectifier array, it is believed that the whisker ele-
`ments within the semiconductor diodes themselves are a
`contributing‘ factor and may function as additional dipole
`elements. The disclosed embodiment functioned efliciently
`when illuminated by microwave energy generating a verti-
`cally polarized beam. Hence, an efficient and light weight
`energy conversion apparatus is disclosed which may be
`self-supporting without the requirement of a large local
`fuel supply payload.
`It may be within the purview of the invention to use
`the available rectified electrical energy for performing
`many functions in addition to the actuation of the pro-
`pulsion means. Hence, communications’ payloads may be
`maintained at predetermined positions in space in a hov-
`ering attitude utilizing a portion of the electrical energy
`available. Relay signals to other such vehicles or return
`signals to ground stations would then be within the realm
`of possibility. Such available energy may also be em-
`ployed for servomechanisms, stabilizing and counter-
`torque systems for the navigation of such vehicles.
`The electrical efliciencies realized with the combined
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`arm full-wave bridge connected rectifier circuit net-
`works each having a plurality of unidirectional semi-
`conductors in each arm;
`said networks being electrically interconnected to com-
`mon output terminals;
`electrically operable propulsion means comprising a
`motor and rotor members carried by said body means
`and connected to said terminals for the utilization of
`said rectified DC energy; and
`means for matching the load impedance of said com-
`bined antenna and electrical energy rectification
`means to the incident microwave energy.
`2. A space vehicle according to claim 1 wherein said
`load impedance matching means are arranged in a co-
`planar array coextensive with said antenna and energy
`rectification means array, and spaced therefrom a dis-
`tance of approximately one-quarter of a wavelength at
`the frequency of the microwave energy.
`3. A space vehicle according to claim 2 wherein said
`load impedance matching means comprise a plurality of
`parallel disposed elongated metallic members.
`References Cited
`
`UNITED STATES PATENTS
`
`1,217,149
`2,165,055
`2,444,458
`2,927,321
`3,‘09‘8,971
`3,174,705
`
`2/1917 Caldwell ________ __ 321-27 X
`7/1939 Kafka _____________ _.. 321-27
`7/1948 Master _____________ __ 321-8
`3/ 1960 Harris ____________ _. 343—6.8 X
`7/ 1963 Richardson ______ __ 325-592 X
`3/1965 Schiff et al. _________ __ 244-1
`
`RODNEY D. BENNETT, Primary Examiner.
`MALCOMB F. HUBLER, Assistant Examiner.
`
`U.S. Cl. X.R.
`
`307-151; 318-16; 321-27; 325-494; 343-100
`
`3,434,678
`
`7
`receiving antenna and rectifier means have also provided
`certain weight advantages over other energy converters in
`aerospace applications. Examples of
`such converters
`would be heat exchangers or solar cells. In comparison
`to the present invention where five to eight pounds per
`kilowatt of energy realized is a normal characteristic,
`other energy conversion means weigh in the vicinity of
`150 pounds per kilowatt of realizable energy. The inherent
`advantages of the present invention are therefore appar-
`ent. While the technology in the diode rectifier art is be-
`ing continually advanced, new diode power rectifiers as
`well as integrated circuit techniques are readily available
`to future configurations of the present invention. The so-
`called Schottky barrier diodes could be employed to pro-
`duce combined antenna—rectifier means weighing even less
`than two pounds per kilowatt of available energy.
`Although the foregoing detailed description has re-
`ferred to DC power rectification it will be evident that
`with suitable circuit components low frequency AC energy
`may also be made available. In addition, other propulsion
`means may be readily substituted using electrical energy.
`The embodiments disclosed herein are illustrative only
`and other modifications or alterations will be apparent to
`those skilled in the art which do not depart from the
`scope of the broadest aspects of the present invention as
`defined in the appended claims.
`What is claimed is:
`1. A space vehicle comprising:
`body means;
`said body means including spaced structural support
`members;
`combined antenna and DC electrical energy rectification
`means for the interception and rectification of inci-
`dent high frequency electromagnetic microwave en-
`ergy carried by said support members in a planar
`parallel array;
`said rectification means comprising a plurality of four
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