A fuel less pneumatic and hydraulic lift system flight system provides the following systemic components. A chassis supporting an electric battery and a pressurized base hydraulic cylinder, a hydraulic fluid pumping assembly fluidly coupled to the pressurized base hydraulic cylinder; a lift mechanism assembly providing an attractive levitation plate mounted to the chassis; and a repulsive levitation plate mounted to a carriage, wherein the repulsive levitation plate is disposed in a magnetic pole repulsive alignment relative to the attractive levitation plate causing a magnetic lift effect to the chassis; and a plurality of propulsions jets mounted to the chassis, wherein the plurality of propulsion jets enabling motive functionality using hydraulic fluid propulsion and pneumatic pressure via the hydraulic fluid pumping assembly in conjunction with the magnetic lift effect.

A system for propelling craft which is applicable in any environment. It employs alternating electric fields supplied by a multi-layer capacitor to create an alternating magnetic field. A coil is situated so that the magnetic field interacts with the current elements in the coil. The capacitor is charged and discharged in synchronization with the alternating current in the coil. The changing electric fields in the capacitor create a magnetic field that applies a force to the current elements in the coil which is then transferred to the body of the device. Any reactive force from the magnetic field of the coil is negated since the gaps in the capacitor have no current elements with which the magnetic field of the coil can interact. Therefore the device is propelled in a single direction.

An engine that uses photons to create an Internal Directional Pressure Imbalance, resulting in thrust.

An engine that uses photons to create an Internal Directional Pressure Imbalance, resulting in thrust.

[Problem to be Solved] A propulsive force is generated without using reaction of a substance, eliminating the need for a portion exposed to an external environment.

[Solution] Rotary motion of at least one inclined circling trajectory A around the rotation axis B and circling motion of the substance C are performed simultaneously and continuously so that each time the inclined circling trajectory A rotates through 180 around the rotation axis B, a change in the inclination angle is caused for the circling trajectory of the substance C by up to 90 relative to each of the Y axis and the Z axis, and interaction with the resistance exhibited by the substance C against the change is used as a propulsive force.

Methods, structures, devices and systems are disclosed for fabrication of microtube engines using membrane template electrodeposition. Such nanomotors operate based on bubble-induced propulsion in biological fluids and salt-rich environments. In one aspect, fabricating microengines includes depositing a polymer layer on a membrane template, depositing a conductive metal layer on the polymer layer, and dissolving the membrane template to release the multilayer microtubes.

The present invention discloses an apparatus and method for electromagnetic spacecraft propulsion. The apparatus includes capacitor assemblies bracketed by electromagnetic solenoids configured in Helmholtz Coil geometries. The action of magnetic fields generated in the solenoids on segmented currents in conductive discharge elements during capacitor discharge produces unidirectional forces, while reaction momentum is carried away by Poynting Vector electromagnetic fields in conformity with the currently understood principles of electrodynamics.

This patent seeks to describe a design and method of production of a solid state radiometric thruster for the intent of producing a new method of powered flight at varying scales of operation. By using modern nano-manufacturing techniques it is possible to create surface microstructures of the same size as the mean free path for gases at any desired operational pressure, allowing for radiometric forces to be harnessed for propulsion even when the total part dimensions are several orders of magnitude larger than would normally allow this effect to create a noticeable force.

This patent seeks to describe a design and method of production of a solid state radiometric thruster for the intent of producing a new method of powered flight at varying scales of operation. By using modern nano-manufacturing techniques it is possible to create surface microstructures of the same size as the mean free path for gases at any desired operational pressure, allowing for radiometric forces to be harnessed for propulsion even when the total part dimensions are several orders of magnitude larger than would normally allow this effect to create a noticeable force.

Hydro-carbon nanorings may be used, e.g., in power storage power transmission and transportation. Sufficiently cooled, an externally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for electrons rotating in the nanoring. Such nanorings may transmit DC current with little or no loss. Similarly, an internally hydrogen doped carbon nanoring may be used to create a radial dipole containment field for positrons rotating in the nanoring. Virtually lossless transmission of AC current may be achieved by pairing such streams of electrons and positrons in their respective containment fields. Closed rotation of such streams may also be used to efficiently store large amounts of electrical energy. Finally, selectively accelerating and decelerating pairs of such paired electron and positron streams, which are moving at relativistic speeds, differential momentum may be created to cause physical movement.