John E. Brandenburg

Unification of gravity and electromagnetism in the plasma universe

The basic arguments and results of the gravity-electromagnetism (GEM) theory are presented. This theory unifies gravity and electromagnetism using simple models and concepts and is based on two postulates: (1) gravity is a spatially varying Poynting field that defines the geometry of space such that ultrastrong fields are self-canceling and (2) the splitting or separation of characteristics of gravity and EM are mirrored in the splitting of protons and electrons and these quantities merge at the Planck level to give one field and one particle type. Consequently, it is shown that two highly accurate formulas can be derived: (1) G=e/sup 2//(4 pi epsilon /sub 0/m/sub p/m/sub e/) alpha exp(-2R/sup 1/2/), where m/sub p/ and m/sub e/ are the proton and electron masses respectively, alpha is the fine structure constant, and R=m/sub p//m/sub e/, and (2) alpha /sup -1/=R/sup 2/3/-R/sup 1/3/-2/3/(1+4/(3R)). It is found that the GEM theory is consistent with a flat open cosmos and predicts the value of the cosmic background temperature to high accuracy and the Hubble time to reasonable agreements with current estimates. >

The microwave electro-thermal (MET) thruster using water vapor propellant

The research to develop the microwave electro-thermal (MET) thruster at Research Support Instruments, Inc. (RSI) using a variety of gases as fuel is described. The MET has undergone dramatic evolution since its first inception, and it is now moving toward flight development. The MET uses an electrodeless, vortex-stabilized microwave discharge to superheat gas for propulsion. In its simplest design, the MET uses a directly driven resonant cavity empty of anything except gaseous propellant and the microwave fields that heat it. It is a robust, simple, inexpensive thruster with high efficiency, and has been scaled successfully to operate at 100 W, 1 kW, and 50 kW using 7.5-, 2.45-, and 0.915-GHz microwaves respectively. The 50-KW, 0.915-GHz test was perhaps the highest power demonstration of any steady-state Electric thruster. The MET can use a variety of gases for fuel but the use of water vapor has been shown to give superior performance, with a measured specific impulse (I/sub sp/) of greater than 800 s. When this added to the safety, ease of storage and transfer, and wide availability of water in space, the potential exists for using a water-fueled MET as the core propulsion system for refuelable space platforms.

HIGH POWER MICROWAVE ELECTROTHERMAL THRU STER PERFORMANCE ON WATER

Thrust, specific impulse, thrust efficiency, and microwave coupling efficiency were measured for a nominally 1 kW microwave electrothermal thruster (MET) operating on He, N 2, and N 2O, and for a nominally 5 kW MET operating on water. For He, N 2, and N 2O thrust varied from approximately 100 to 700 mN at discharge pressures from 500 to 2000 Torr and magnetron input powers from 900 to 1500 W. Thrust measurements agree well with idealized calculations based on the assumptions o f one -dimensional, isentropic flow of a perfect gas with constant specific heats. Peak specific impulses for He, N 2, and N 2O were 418, 243, and 209 seconds respectively. Water was run at magnetron input powers from 2.1 to 4.1 kW and discharge pressures f rom 300 to 1100 Torr. Thrust varied from approximately 100 to 250 mN with a peak specific impulse of 428 seconds.

Experimental investigation of large-volume PIA plasmas at atmospheric pressure

Large-volume atmospheric-pressure plasmas have been the subject of previous research as a laboratory simulation of ball lightning, but measurements of the plasma properties have been unavailable. The present investigation employed a non-resonant microwave chamber with a 1000-W microwave-source operating at 2.45-GHz frequency to produce large volume (up to 0.8 L) plasmas that persisted after microwave shutoff. A Langmuir probe was used to measure electron density and temperature, and the highest values measured were 10/sup 10/ cm/sup -3/ at 0.67 eV, respectively. Plasma lifetimes after microwave shutoff were also measured, using both a photocell and a video camera, and were found to average 200 ms. A working hypothesis of the formation of shared electron orbitals in dense gas discharges is put forth to explain this phenomenon.

Progress on the MET ( microwave electrothermal) thruster with water propellant

Summary form only given. Progress on the MET thruster using water vapor propellant is reported. The MET heats gas in a vortex stabilized, electrodeless, microwave discharge for propulsion. In this research the start-up and asymptotic behavior of the MET specific impulse with increasing run time is investigated. It is found that after a run time of approximately thirty seconds, that the MET thruster running on water vapor achieved a specific impulse of approximately 900 seconds, in agreement with previous research. Chemical physics code runs with, have confirmed the high specific impulse numbers for water as being due to rapid hydrogen-oxygen recombination in the nozzle during expansion and the high source temperature in the electrodeless microwave discharge of approximately 8000 K. Models and diagnostics for this high performance on water vapor will be discussed

The MET (microwave electro-thermal) thruster using water vapor propellant

Summary form only given, as follows. The Research to develop the MET (Microwave Electro-Thermal)Thruster at Research Support Instruments and University of Pennsylvania using a variety of gases as fuel is described. The Microwave thermal thruster has undergone dramatic evolution since its first inception and is now entering flight development. The MET uses an electrodeless, vortex stabilized microwave discharge to superheat gas for propulsion and in its simplest design, uses a directly driven resonant cavity empty of anything except gaseous propellant and the microwave fields that heat it. It is robust, simple inexpensive thruster with high efficiency and has been scaled successfully to operate at IOOW, IkW, and 50kW using 7.5, 2.45 and 0.9I5Ghz microwaves respectively. The 50KW at 0.915GHz continuous operation being perhaps the highest power demonstration of any steady state Electric thruster. The MET can use a variety of gases for fuel but the use of water vapor has been shown to give superior performance, with a measured I,, of greater than 800 sec. When this added to the safety, ease of storage, and transfer of water in space, the potential exists for using water fueled MET as core propulsion system for many re-fuel capable space platforms.

Further investigation of PIA (Persistent Ionization in Air) plasmas using room air

Summary form only given. It is now possible to create glow discharge-type plasmas in room air. These plasmas are made in a modified 1 kW microwave oven (2.45 GHz) and can be sustained for an indefinite period by the microwaves. When the microwaves are turned off the plasma continues to emit light with an exponential decay of time constant of 60 milliseconds. Plasmas occur as mobile spherical regions of approximately 3 cm radius or can be stabilized as liter sized volumes in steady state. Vortex motion appears to occur in the plasmas. The plasmas are created by a spark UV source with or without Argon gas to promote ionization. Measurements using Langmuir probes and microwave sensors have obtained an approximate electron number density of n/sub e/=5/spl times/10/sup 10/ cm/sup -3/ and an approximate electron temperature of Te=0.7 eV. A large plasma has also been made using room air in a gas vortex stabilized configuration using 45 kW at 915 Mhz. We believe these plasmas are a new and unusual plasma state first reported by Manwaring, Powell, and Finklestein (l970) who used 30 kW of RF power at 75 MHz. Recent research results will be shown.