Paul Howard Conner

Bio: Paul Howard Conner is an academic researcher. The author has contributed to research in topics: Electron & Quadrupole magnet. The author has an hindex of 1, co-authored 2 publications receiving 6 citations.

Electron propulsion unit

Abstract: An electron acceleration device uses thermionic fission cells, an electromagnetic scoop coil, and/or microwaves for power. A power control junction and electron injector control and feed free electrons in packets into the acceleration components that consist of a series of either induction module units, or radio-frequency linacs module units, having quadrapole magnet units in series between the induction module units or RF linac units. The RF linac and quadrapole series are surrounded by a Klystron series. At the high speed electron exit from the device, deflector plates control the exit path of the electrons to direct the course of a craft or electrons to a work area.

Electron propulsion engine

Abstract: An electron acceleration device using thermionic fission cells and an electromagnetic scoop coil for power. A power control junction and electron injector control that feeds free electrons in packets into the acceleration components that consist of a series of induction linac module units, having quadrupole magnet units in series between the induction module units. Has on-board xenon gas for a deep space electron source. At the high speed electrons exit from the device, deflector plates control the exit path of the electrons to direct the course of a craft.

Compact helical resonator coil for ion implanter linear accelerator

Abstract: A compact coil design is provided for a linear accelerator resonator (70) capable of resonating at a predetermined frequency. The coil (90) comprises a plurality of generally circular coil segments (90a-90n), each of the coil segments having a polygonal cross section wherein flat surfaces (122) of adjacent coil segments face each other. The polygonal cross section may take the form of a rectangle having dimensions of length x and width y, wherein dimension x section defines the flat surfaces (122) of adjacent coil segments (90a-90n). The coil segments (90a-90n) are provided with a dual channel construction for providing the introduction of a cooling medium into the coil. The dual channel construction comprises an inlet passageway (118) and an outlet passageway (120) having separate a separate inlet (100) and outlet (102), respectively, at a first end (94) of the coil, and wherein the inlet and outlet passageways (118, 120) are connected and in communication with each other at a second end (96) of the coil.

Acceleration cavity and accelerator

Abstract: The objective of the present invention is to provide an acceleration cavity and an accelerator such that the Q value can be increased compared to prior art normal conducting acceleration cavities, and power efficiency can be increased. This high-frequency acceleration cavity (1) comprises: a housing (3) whereof the inner peripheral surface is cylindrical in shape, and electrically conductive at least on the surface thereof; and a plurality of acceleration cells (2) provided inside the housing (3), each being a dielectric having formed in a central portion thereof an opening (5a) wherethrough a charged particle can pass. The housing (3) has a cylinder body (6) having a cylindrical shape, and end plates (7) provided at both ends of the cylinder body (6). A plurality of the acceleration cells (2) are disposed throughout from the end plate (7) at one end side to the end plate (7) at the other end side of the housing (3). Each of the acceleration cells (2) comprises: a cylinder body (4) having a diameter smaller than the internal diameter of the cylinder body (6) from the housing (3); and a disc portion (5) where the opening (5a) is formed, fixed onto the cylinder body (4) on the inner side of the cylinder body (4), and disposed in such a manner that the plate surface thereof is orthogonal to the charged particle passage axis.

Electrodynamic space thruster method and apparatus

Abstract: A method and apparatus for producing a linear thrust force, comprising an array of phase-shifted electric oscillations having frequency greater than or equal to ratio of the speed of electromagnetic waves in free space to length of the array (f ≥ c/L). Operated at adequate frequencies and powers, such device can produce highly efficient levels of thrust force for propelling spacecrafts and satellites with low consumption of energy. Further comprises a custom amplifier for producing and radiating powerful electric oscillations by accelerating, decelerating, and retaking electrons, producing several megawatts of thrust power.

Method of hitting dangerous space objects and device to this end

Abstract: FIELD: transport.SUBSTANCE: set of invention release to space engineering, particularly, to displacement in space using space resources and can be used for hitting the dangerous space objects (DSO) Proposed method comprises selecting the comet nucleus of one of mini-comet in orbits 6 approaching the Earth 3 as hitting space body (HSB). Rocket engine unit exploiting comet nucleus evaporant as a working medium is launched in space from the Earth and placed in orbit 8 to approach said HSB. Landing thereto is carried out at point 9. Said rocket engine unit is used to change said HSB from initial orbit 7 to trajectory 10 that ensures its collision with DSO 3 at point 11. This imparts to DSB the impulse that changes it from initial orbit 4 that implies the collision of the Earth at point 5 to safe orbit. Device to this end (not shown) comprises said rocket engine unit, snapper with comet matter evaporator, power plant (with solar concentrator and astronavigation device. With snapper penetrated into comet nucleus, evaporator sublimates nucleus volatile matters. Evaporated vapors are heated by solar concentrator effuse from rocket engine nozzle generates the thrust. Astronavigator sets required direction of thrust vector.EFFECT: power savings in mission, lower operating period of engines, higher reliability.4 cl, 2 dwg

Method and device for sampling material from astronomical object surface

Abstract: FIELD: physics.SUBSTANCE: group of inventions relates to the active research of the astronomical object (AO), such as an asteroid or a comet. The method includes the AO subjecting the surface with the directed AO electron beam from the spacecraft hovering over the AO surface. The evaporation products of the AO soil are captured by the material collector (a substrate with the lens hood) mounted on the device in front of the electron beam source.EFFECT: increasing reliability and safety of sampling materials from the AO surface.2 cl; 1 dwg