Abstract: A method for providing optimized power balanced low thrust transfer orbits utilizing split thruster execution to minimize an electric orbit raising duration of an apparatus includes monitoring an electric power balance on the apparatus. The method also includes firing a first thruster in response to the apparatus exiting an eclipse and based on the electric power balance. The method additionally includes firing a second thruster at a predetermined time delay after firing the first thruster based on the electric power balance. The method additionally includes ending firing one of the first thruster or the second thruster after a predetermined time duration based on the electric power balance. The method further includes ending firing another of the first thruster or the second thruster in response to the apparatus entering a next eclipse.

Abstract: This invention presents a unique propulsion and maneuver-control system for crafts and devices. This invention develops its desired thrust force vectors from the vectors sum of centrifugal force vectors of rotating masses and their controlled gyroscopic force vectors. Also shown are applications of this propulsion and maneuver-control system for future VTOL-Hovering-Flying crafts, Scooters, Surfboards, marine/submarine-crafts, earth, moon, mars satellites disks and space-crafts. This invention has great potentials of creating new businesses in aerospace markets, all planets' weather modification business, bring people of the world closer together and perform critical tasks of modify trajectories to prevent run-away asteroids from hitting the earth.

Abstract: A method of space travel using a high acceleration thrust vehicle in combination with a plurality of low acceleration thrust vehicles. A primary spacecraft has a kinetic launcher that is utilized to discharge a plurality of subsidiary spacecraft in order to navigate the primary spacecraft along a flight path. Each of the plurality of subsidiary spacecraft has a propulsion system, allowing each of the plurality of subsidiary spacecraft to navigate to a refueling point. The refueling point for each of the plurality of subsidiary spacecraft may be a central location or a unique position along a subsequent flight path. Each of the plurality of subsequent spacecraft is then reloaded onto the primary spacecraft or loaded onto a subsequent spacecraft for another voyage. The kinetic launcher can be repositioned in order to control the direction of the acceleration experienced by the primary spacecraft.

Abstract: A system and method for propelling spacecraft is disclosed. An electrical propulsion system is mounted on a base stage. A plurality of spacecraft couplers are also mounted on the base stage. Each spacecraft coupler securedly attaches a spacecraft to the base stage. Each spacecraft includes an internal power source that is coupled to the electrical propulsion system via an electrical connection. The internal power source consists of solar panels and/or batteries. A power regulation circuit is coupled between the electrical propulsion system and each internal power source. The power regulation circuit is draws an equal and proportional amount of power from each spacecraft. The spacecraft are preferably satellites and the electrical propulsion system preferably propels the base stage and attached satellites from a lower-Earth orbit to a higher-Earth orbit so that the electrical propulsion system in each satellite need only be capable of providing propulsion for orbit maintenance and maneuvering.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame, a power source coupled to the frame and a payload coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus.

Abstract: A debris removal management system and a method of removing space debris. In one embodiment, the system includes: (1) a frame, (2) a plurality of net sections coupled to the frame and (3) a plurality of microvehicles coupled to the plurality of net sections and configured to be ejected relative to the frame to deploy the plurality of net sections, the plurality of net sections cooperating to form a net configured to capture space debris.

Abstract: A control system for a vehicle having a dry dual clutch transmission (DCT) includes a launch condition detection module, a vehicle stop module, and a vehicle launch module. The launch condition detection module detects a launch condition based on whether (i) the vehicle is on an uphill grade and (ii) a driver of the vehicle has requested power via an accelerator. The vehicle stop module stops the vehicle when the launch condition is detected by (i) commanding an on-coming clutch of the dry DCT to a predetermined position and (ii) applying brakes of the vehicle. The vehicle launch module launches the vehicle after the vehicle is stopped by (i) fully engaging the on-coming clutch of the dry DCT and (ii) opening a throttle to a desired position corresponding to the power request.

Abstract: An article and device are provided comprising a switchable microstructure or nanostructure array of non-parallel conducting plates, supported by a plurality of shaped prismatic oxide stages upon layered conductive and substrate-base materials, for directly generating a lateral or transverse Casimir force. Illustrative embodiments include a device for switchable generation of lateral or transverse Casimir force components that work in an orthogonal direction to normal Casimir forces which can be externally switched “on” or “off” electronically, mechanically or thermally by using a semiconductor PN-junction or superconductor to produce a thrust for guidance, maneuvering and propulsion of a manned or unmanned space vehicle, or in other novel applications requiring generation of precisely switched or continuous forces.

Abstract: An electrodynamic method includes providing an electrodynamic structure with a periphery, providing power, collecting electrons, and emitting electrons. The emitting electrons and the collecting electrons utilizes at least 20% of the periphery of the electrodynamic structure. The method includes conducting current to provide at least one of electrodynamic propulsion and power generation.

Abstract: A craft, having at least two counter rotating rotors within, or a multi unit craft having two or more units as desired, with counter rotating rings, having the ability to store inertia, within the spinning rings, so as to enable the craft to either accelerate from the front or decelerate from the back of the Earth, relative to the absolute inertial frame of reference.

Abstract: The invention relates to a plasma based aircraft possessing a magnetic field, and a plasma vortex. The craft is tubular in shape. The craft has a vast array of capacitors. The craft also has a proton accelerator, plasma guns, and diversion devices. The craft will approach the speed of light, over time. The craft obtains fuel direct from an atmosphere or a radiation induced atmosphere in space, at no cost, similar to our Moon's radiation induced atmosphere of the noble gases. The craft can travel to a gk star, for only the cost of construction of craft. The craft has three on-board escape, exploratory craft. The craft produces plasma vortices within an electromagnetic field. The field is an inhomogeneous, diamagnetic, orbiting plasma field, with a magnetohydrodynamic electrically conducting plasma current. The craft possesses approximately seven uninsulated, tungsten bands, encircling craft.

Abstract: Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. Due to the law of conservation of angular momentum, the first process is considered by some to not be possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it is clearly possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

Abstract: Existing spacecraft accelerate by ejecting propellant, and VTOL craft hover by creating violent downdrafts of air. We describe a propellantless propulsion system that can achieve practical spaceflight and hovering flight by exchanging momentum with normally unobservable quantum particles that pervade all of space. High-polarizability nanoparticles with electromagnetic resonances in the petahertz range are formed into nanoantennas, and exposed to high fields in the terahertz range. The fields increase the density of naturally occurring vacuum fluctuation (VF) petahertz oscillations in the nanoantennas. The nanoantennas are assembled into arrays, such that their naturally occurring zero-point oscillations are amplified by the terahertz fields, producing enhanced oscillations in VF densities during each petahertz oscillation period that interfere constructively in the intended direction of emission.

Abstract: An electrodynamic structure having a periphery. The electrodynamic structure includes a power system, a plurality of collectors, a plurality of emitters, and conductive paths. The plurality of collectors are disposed on the periphery of the electrodynamic structure and configured to collect electrons. The plurality of emitters are disposed on the periphery of the electrodynamic structure and configured to emit electrons. At least 20% of the periphery of the electrodynamic structure is utilized for electron collection and electron emission. The conductive paths are configured to conduct current between the power system, the collectors, and the emitters to provide at least one of power generation and electrodynamic propulsion.

Abstract: Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. Due to the law of conservation of angular momentum, the first process is normally considered not possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it becomes possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

Abstract: The invention relates to a plasma based aircraft maintained in a flight mode by rotating plasma vortices located above and beneath said aircraft. Said aircraft is comprised of chromium steel, or higher ferrochromium steel can be used. Said aircraft receives energy from aircraft produced plasma obtained from the atmosphere. Produced energy is stored within craft oscillatory circuit and plasma vortices. When energy from craft capacitance system is depleting, energy can be obtained from craft inductance system from craft magnetic field. Said craft is capable of space flight, use as a submersible craft, boring device, or lifting device. Particle propulsion in space will be accomplished utilizing metal ions stored within craft capacitor plates. Said craft is opaque to electromagnetic radiation, and also absorbs radiation directed at craft. Said craft is capable of verticle ascent, descent and landing, and is lenticular in shape. Said aircraft can operate within earth radiation belts safely.

Abstract: An article and device are provided comprising a switchable microstructure or nanostructure array of non-parallel conducting plates, supported by a plurality of shaped prismatic oxide stages upon layered conductive and substrate-base materials, for directly generating a lateral or transverse Casimir force. Illustrative embodiments include a device for switchable generation of lateral or transverse Casimir force components that work in an orthogonal direction to normal Casimir forces which can be externally switched “on” or “off” electronically, mechanically or thermally by using a semiconductor PN-junction or superconductor to produce a thrust for guidance, maneuvering and propulsion of a manned or unmanned space vehicle, or in other novel applications requiring generation of precisely switched or continuous forces.

Abstract: A propulsion method employing gyroscopes (1,2) with electric motors (4) which are being moved along a closed path in the spacecraft. Rotation axis of the gyroscopes are rotated periodically relative to movement direction so that gyroscopic effect is only obtained during movement in one direction. Thereby a gyroscopic resistance difference is obtained and used as a propulsion force. Another application is to use gyroscopes connected to generators in order to decelerate a spacecraft, transforming the moment created in gyroscope during deceleration into the electrical energy, distribute it to the space as heat transfer by means of radiation through the heat resistant panels.

Abstract: An extraterrestrial vehicle propulsion system uses a frusto-conical body member that is spun at high speeds by a drive member. A battery, which is rechargeable by a solar cell array, provides power to the drive member.

Abstract: Low mass-per-unit-area plastic film, preferably polyimide, prepared by a process of controlled treating of a supply of plastic film, possibly with one surface reflectively coated, at a microlithography workstation with included photoablation optics. This treatment achieves significant controlled removal of material in a selected pattern by providing relative motion between untreated plastic film and the workstation's photoablation optics while controlling photoablation of a pattern in the film. The material has a significant quantity of the mass of its plastic removed by photoablation, leaving a tessellated pattern of ridges surrounding individual wells. The resulting low-mass, rip-resistant film retains the general attributes of a large-area plastic film. The treated film also retains its reflective surface, on which amorphous silicon may be deposited. The silicon may be thereafter crystallized, utilizing the same optics, and used for fabrication of microelectronics.

Abstract: A spacecraft propulsion system includes a plurality of wires (102) or other electrically conductive elongated members deployed from a main body (101) into respective radial directions. An electric potential generator (605) generates an electric potential on board the main body (101). The electric coupling between the electric potential generator (605) and the elongated members is controlled (604) so that all or some of the elongated members (102) assume a high positive potential. An auxiliary propulsion system (203) rotates the main body around a rotational axis (502) that is perpendicular to the radial directions, thus creating a centrifugal supporting force to the elongated members.

Abstract: The present invention relates to a spacecraft (P) comprising a propulsion system (1) making it possible to exert a force of variable magnitude and orientation on the spacecraft, a control system designed to control the propulsion system in terms of magnitude and orientation so as to make the spacecraft approach a target around a planet, with the aid of a force which comprises at least one component (fx, fy, fz), in the rotating reference frame tied to the target, which depends substantially linearly on the corresponding coordinate (x, y, z) of the craft in this reference frame.

Abstract: A counterweight based rocket launch platform system and method uses gravity acting upon a counterweight to provide the initial assent for a rocket. This counterweight system is preferably built inside of a mountain so as to use the mountain as the supporting structure. By covering the exit opening with a thin membrane and closing the bottom, the system can have the air evacuated providing a free ascent without a terminal velocity. During the final moments of the ascent or after the rocket leaves the tube, the rocket will ignite carrying the payload into space. The velocity imparted to the rocket from the gravity assist in combination with bypassing the thickest part of the atmosphere will lower the amount of fuel required to lift payloads into space. This will result in increased payloads of existing rockets or the use of smaller and less expensive rockets.

Abstract: The Levitation and Propulsion Unit (LPU) defies the pull effect of gravity through the transformation of centrifugal force from spinning wheel into internal upward thrust without interaction with its external environment. It transforms the centrifugal force from spinning wheel by exerting balanced pulsating force parallel to the axis of spin, and reinforce by the compression and expansion of magnetic repulsive force, to create the internal upward thrust parallel to the axis of spin. Through systematic rapid succession of thrust, it counteract the pull effect of gravity, result in levitation; and by angulations of LPU propel the whole unit and its application. It serves to replace or complement the propeller, wheel, jet engine, solid fuel, etc, in the area of transportation and use in space travel.

Abstract: Method and device for directly generating a transverse Casimir force comprising a technique for fabricating a microstructure array of non-parallel conducting plates held in place by an insulating material and affixed either to a conducting or insulating substrate are disclosed. As described by the illustrative embodiment, the lateral or transverse force component generated by the present invention works in an orthogonal direction to the normal Casimir force, thereby allowing its use as a means of vectored thrust for precise positioning, guidance, maneuvering and propulsion in a manned or unmanned space vehicle, or any application requiring precise forces.

Abstract: The invention is a system and method for propellantless, ultrahigh precision satellite formation flying based on ultrahigh precision intracavity laser thrusters and tethers with an intersatellite distance accuracy of nanometers at maximum estimated distances of tens of kilometers. The repelling force of the intracavity laser thruster and the attracting force of tether tension between satellites form the basic forces to stabilize matrix structures of satellites. Users of the present invention can also use the laser thruster for ultrahigh precision laser interferometric metrology, resulting in simplification and payload weight reduction in integrating the thruster system and the metrology system.

Abstract: A momentum actuator for steering a spacecraft is disclosed. The momentum actuator comprises a rotor, a gimbal upon which the rotor is mounted, and a stepper motor coupled to the gimbal and operable to rotate the rotor about the gimbal in a series of steps. In one embodiment of the present invention the spin rate of the rotor can be varied to provide torque.

Abstract: An apparatus and method that make use of electromagnetic energy to maneuver an object, such as stop, slow, and/or divert a vessel or projectile in low and zero-gravity environments. The apparatus comprises an element capable of generating a magnetic field in the zero or low-gravity environment, and an object capable of electromagnetically interacting with the magnetic field so that the object's speed and/or trajectory is altered when moving in proximity to the magnetic-field generating element. As such, the method entails maneuvering an object in a zero or low-gravity environment by generating a magnetic field in the zero or low-gravity environment, and then moving the object in proximity to the magnetic field such that the magnetic field alters the trajectory and/or speed of the object.