Patent US3114517A — Microwave Operated Space Vehicles (Raytheon / William C. Brown)
Bibliographic Information
| Field | Details |
|---|---|
| Patent Number | US3114517A |
| Title | Microwave Operated Space Vehicles |
| Inventor | William C. Brown, Western Division, Raytheon Company |
| Assignee | Raytheon Co., Lexington, Massachusetts |
| Filing Date | May 12, 1959 |
| Publication Date | December 17, 1963 |
| Status | Expired — Lifetime |
| Application Number | US812,698 (related: Serial No. 812,697, filed May 12, 1959; now US3,083,528) |
| Classifications | B64G1/00; B64G1/22; B64G1/40; B64G1/409; B64G1/411; B64G1/415; B64G1/42; B64G1/428; F03H; F03H3/00; H01Q19/00; H01Q19/10; Y10S343/00; Y10S343/02 |
| Jurisdiction | United States (US) |
Abstract
This invention pertains generally to space vehicles and the like, and more particularly to a novel form of space vehicle and a system for maintaining such vehicle in flight or at a desired location in spaced-apart relationship with respect to a point on another planet or the like. The vehicle is maintained in flight by microwave electromagnetic energy beamed from a ground control station, which is converted onboard to thrust-producing forces. The vehicle requires no on-board fuel and can operate indefinitely.
Claims (11 Total)
Claim 1: A thrust-propelled space vehicle adapted to be maintained centered on a radiated energy beam, comprising multiple thrust engines mounted for rotary movement about a common axis, wherein the major thrust portion of each engine is tangential to the rotation circle with a minor outward-directed component, airfoil means providing lifting force, and energy receiving means that apportion beam energy to engines based on their positions relative to the beam center, enabling corrective forces maintaining vehicle centering.
Claim 2: A thrust-propelled space vehicle with multiple thrust engines mounted equidistant from a common rotation axis, major thrust tangential with minor outward components, airfoil means sustaining flight, and energy receiving means distributing radiated beam energy proportional to each engine's distance from the beam centerline, providing movement and corrective forces for beam centering.
Claim 3: The vehicle of claim 2 using microwave electromagnetic energy, wherein engines convert electromagnetic energy to propulsive thrust, and the energy receiving and applying means comprise a concave surface of revolution reflecting the electromagnetic beam energy to the engines.
Claim 4: A thrust-propelled space vehicle maintaining centered position on radiated energy beams, comprising paired thrust engines mounted symmetrically on opposite sides of a central axis, in a common plane including the axis at angles providing thrust components directed away from the axis, with symmetrically disposed means directing beam energy to engines in amounts proportioned to their distances from the beam centerline.
Claim 5: The vehicle of claim 4 using microwave electromagnetic energy, wherein engines convert electromagnetic energy to propulsive thrust, and the directing means comprise paired concave reflecting members each reflecting beam energy portions to respective converting means.
Claim 6: A thrust-propelled space vehicle maintaining centered position on radiated energy beams, comprising multiple thrust engines for energization by radiated energy, mounted symmetrically relative to a central vehicle axis, engine thrust confined to respective planes including the central axis, containing both parallel and outward-directed components, with symmetrically disposed means directing beam energy to engines in amounts proportioned to their distances from beam centerline.
Claim 7: A system maintaining thrust-propelled space vehicles in spaced-apart relationship with a mother planet at selectable locations, comprising a control station transmitting microwave electromagnetic energy in a substantially vertical beam toward the vehicle, multiple thrust engines on the vehicle mounted for rotary movement about a substantially vertical common axis, major thrust tangential with minor outward components, airfoil means providing lifting force, and energy receiving means applying transmitted energy to engines with apportionment based on engine positions relative to beam center.
Claim 8: A system maintaining thrust-propelled space vehicles in spaced-apart relationship with a mother planet at selectable locations, comprising a control station transmitting microwave electromagnetic energy in a substantially vertical beam toward the vehicle, paired thrust engines on the vehicle adapted for energization by radiated energy, mounted symmetrically on opposite sides of the vehicle's central axis, engines mounted in a substantially common plane including the axis at angles providing respective thrust components both normal to and parallel with the axis, and symmetrically disposed means directing beam energy to engines in amounts proportioned to their distances from the energy beam centerline.
Claim 9: A system maintaining thrust-propelled space vehicles in spaced-apart relationship with a mother planet at selectable locations, comprising a control station transmitting microwave electromagnetic energy in a substantially vertical beam toward the vehicle, multiple thrust engines on the vehicle adapted for energization by transmitted energy, mounted symmetrically relative to the vehicle's central axis, engine thrust confined to respective planes including the central axis, containing both parallel and outward-directed components, and symmetrically disposed means directing beam energy to engines in amounts proportioned to their distances from the energy beam centerline.
Claim 10: A space vehicle comprising body means, antenna means on the body for intercepting incident microwave energy, means on the body for converting intercepted microwave energy directly into flight-producing forces applied to the body, and means for directing intercepted microwave energy to the converting means.
Claim 11: A system for remotely energizing a space vehicle, comprising means at a control station on a mother planet for generating microwave energy, means radiating such microwave energy toward the space vehicle, antenna means on the vehicle intercepting radiated microwave energy, means on the vehicle converting intercepted microwave energy directly into flight-producing forces applied to the vehicle, and means directing intercepted microwave energy to the converting means.
Description / Specification
Background
The prior art provides vehicles requiring on-board fuel expenditure for operation. While orbital satellites require no applied energy once in orbit, enormous quantities are consumed during launch. Vehicles designed for orbital corrections must carry fuel supplies, limiting payload capabilities. Such vehicles cannot operate indefinitely. The present invention addresses these limitations by energizing vehicles through transmitted microwave electromagnetic energy.
Microwave Selection Rationale
Microwave superiority for this application derives from focusing requirements: beam sharpness varies as the ratio of antenna dimensions to wavelength. Decreased wavelength permits corresponding antenna dimension reductions while maintaining beam collimation. Atmospheric absorption increases significantly below 5–10 cm wavelength; water vapor absorption peaks occur near 1–2 cm. Therefore, microwaves in the approximate range of 2–30 centimeters (preferably 5–10 cm) are "readily adaptable to convenient radiation of energy to a remote point with small transmission loss."
Amplitron Power Source
The high-power generation requirement is met by the Amplitron tube: a crossed-field vacuum tube functioning as a compact, highly efficient, broadband amplifier handling high peak and average powers. It comprises a circular but non-reentrant, dispersive network matched over frequencies of interest, with a reentrant electron beam originating from a continuously-coated cathode coaxial with the network, with direct-current potential applied between cathode and anode, and magnetic field applied parallel to the cathode axis, transverse to the anode-cathode electric field.
Amplitron performance: "currently available are capable of producing kilowatts of average radio-frequency power in the neighborhood of ten centimeters in wavelength, and future models are expected to yield 500 kilowatts or more average power, with 50 megawatt peak power."
Figure 1 Description (Preferred Embodiment)
Vehicle 10 is adapted for maintenance in flight relative to Earth 12 through energy transmitted as radiated microwave electromagnetic energy in beam form (lobe 14 with centerline). Transmitter 16 and beam-forming transmitting antenna 18 provide transmission. The antenna assembly reflector is considerably larger than prior art reflectors for focusing large power at high-altitude vehicles (e.g., 65,000 feet); the antenna reflector is partially supported in large bowl or dug-out Earth surface areas.
The concave underside of reflecting member 29 receives the microwave energy and reflects it along substantially straight lines parallel to the radiated beam's central axis into annular opening 22 in frame member 24. Frame member 24 may comprise a hollow waveguide for the received radio-frequency energy, with energy transferred to engines 26.
Multiple engines 26 effect rotary vehicle frame motion (shown by arrows) about the substantially vertical central axis. Rotary motion produces sustaining lift from multiple airfoil members 28 in helicopter rotary wing form.
Figure 3 Description (Self-Centering Mechanism)
Engine 26 thrust direction is not quite tangential to the rotation circles. Engines 25 mount at small angles relative to frame member 24 periphery, so while major thrust portions are tangential, small components are directed away from vehicle centers. This provides vehicles with self-centering or beam-riding operation.
Upon lateral vehicle displacement from beam 14, one side of reflecting member 29 is illuminated with more radiated energy than the opposite side. Engines on that side receive greater energization and produce greater outward thrust components, creating a net lateral corrective force toward beam center. Minimum transient response lag in each engine is essential for self-centering action.
Figure 4 Description (Alternative Configuration)
Vehicle 32 includes reflectors 33 and 34 with concave lower surfaces reflecting beam to focal points 35 and 37. Engines 36 and 38 are positioned slightly inboard of centered positions, so normally not all focal energy enters the engines — the "normally wasted" energy fraction (typically 10–15%) determines the self-centering sensitivity. At normal operation, 85–90% of available energy is utilized.
Engines provide respective thrusts directed upwardly and away from vehicle centers, with major components parallel to the RF transmission direction and minor components normal thereto. Three such engines are necessary for full 3-axis attitude control.
Energy Conversion Mechanism
The microwave energy may be:
- Directly converted to flight-producing force (ion engine or equivalent — Claim 10)
- Converted to heat with heat applied to fluid media that expand to perform propulsion work
For option 2, container means (electromagnetic waveguides with lossy characteristics) heat gaseous media through skin-effect current absorption. Stacked closely-spaced electrically-lossy plate members provide main microwave energy absorption and heat conversion. The heated gas forms jet streams providing propulsion, or drives turbines for rotary shaft output. The skin effect ensures rapid heat transfer with minimal time lag, enabling "almost instantaneous response to applied microwave energy level changes."
Operational Parameters
| Parameter | Value |
|---|---|
| Microwave wavelength (preferred) | 5–10 cm |
| Microwave wavelength (range) | 2–30 cm |
| Amplitron average power (1959 models) | Kilowatts at ~10 cm wavelength |
| Amplitron average power (projected) | 500+ kW average, 50 MW peak |
| Vehicle altitude capability | 65,000+ feet demonstrated |
| Control mechanism | Differential engine energization via beam displacement |
Classifications
- B64G1/00 — Cosmonautic vehicles
- B64G1/22 — Parts/equipment for cosmonautic vehicles
- B64G1/40 — Propulsion system arrangements/adaptations
- B64G1/409 — Unconventional spacecraft propulsion systems
- B64G1/411 — Electric propulsion
- B64G1/415 — Arcjets/resistojets
- B64G1/42 — Power supply system arrangements/adaptations
- B64G1/428 — Power distribution and management
- F03H — Reactive propulsive thrust production
- F03H3/00 — Photon utilization for reactive propulsive thrust
- H01Q19/00 — Antenna combinations with secondary devices
- H01Q19/10 — Combinations using reflecting surfaces
- Y10S343/00 — Communications: radio wave antennas
- Y10S343/02 — Satellite-mounted antennas
Prior Art / Citations
| Patent Number | Inventor | Year | Subject |
|---|---|---|---|
| US889790 | Kitsee | 1908 | Telegraphy |
| US930508 | Vreeland | 1909 | High-frequency oscillation receivers |
| US2471744 | Hershberger | 1949 | Microwave power measurement |
| US2769601 | Hagopian | 1956 | Automatic radio control systems |
| US2813242 | Crump | 1957 | Atmospheric energy extraction for electrical device powering |
| US2941764 | Lee et al. | 1960 | Supersonic aircraft escape system flaps |
| US2949550 | Brown | 1960 | Electrokinetic apparatus |
Non-patent references:
- Vistas in Astronautics, Pergamon Press (1958), page 192
- Advanced Propulsion Systems, Pergamon Press (1959), pages 81–88
Related Raytheon patent filed same date:
- US3083528 (Serial No. 812,697, filed May 12, 1959) — Thrust engine design details referenced throughout this patent
Historical Significance
Filed May 12, 1959, by William C. Brown at Raytheon Company — one of the earliest US patents on wireless power transmission for spacecraft propulsion. Brown was Raytheon's chief engineer for microwave power transmission and the inventor of the rectenna (rectifying antenna). The concept predates the Apollo program by nearly a decade. International filings (GB, BE, JP) in 1959–1960 established IP protection in allied nations' jurisdictions for what would become a key component of remotely-powered UAV architecture.
The 1959 filing confirms technical feasibility was established concurrent with early satellite programs. Raytheon possessed all component technologies in-house: Amplitron tube, parabolic dish antennas, and prototype rectenna arrays.
Citations
- Google Patents: US3114517A
- Brown, W.C. — Raytheon microwave power transmission and rectenna development, late 1950s
Patent text compiled from Google Patents. Full original at the above URL.