128results about "Reactive propulsion thrust device" patented technology

A force generator for an active vibration control (AVC) system provides a mass located upon an inner circular member which is movable within an outer circular member to simultaneously complete one revolution about its axis as it orbits within the outer circular member to compensate for sensed vibrations. A crank mounts the inner circular member and a counterweight. The crank is rotated by a prime mover such as an electric motor. The mass will therefore generate a sinusoidal inertial force in a straight line. Multiple systems are suitably arranged to be used in conjunction with one another to provide a wide range of inertial force outputs.

A force generator for an active vibration control (AVC) system provides a mass located upon an inner circular member which is movable within an outer circular member to simultaneously complete one revolution about its axis as it orbits within the outer circular member to compensate for sensed vibrations. A crank mounts the inner circular member and a counterweight. The crank is rotated by a prime mover such as an electric motor. The mass will therefore generate a sinusoidal inertial force in a straight line. Multiple systems are suitably arranged to be used in conjunction with one another to provide a wide range of inertial force outputs.

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.

The gas turbine engine comprises at least one electrical generator and an electrical heater associated with a gas path of the engine. The heater is powered by the generator to selectively add heat to the gas turbine cycle.

A mass retentive linear impeller is used to convert rotational energy into directional, linear energy. The mass retentive linear impeller comprises a plurality of tracks with a plurality of torque carriages located on the tracks. The torque carriages further comprise two counter rotating flywheels, which are located on a framework. Two rotating arms are located inside of the flywheel and are attached to a center motor of the flywheel, which act as a central axis for the rotating arms. A weight is located at the distal end of each rotating arm. The rotating arms induce a centrifugal force, which creates a temporary pull in one direction. This produces a sequence of forward and backward thrusts.

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.

The present invention provides a thrust generator capable of generating thrust without using reaction of a combustion product, and a navigation body utilizing the same. The thrust generator has a rotation axis, a plurality of tops arranged symmetrically around the rotation axis, and a motor device for rotating the tops around the rotation axis. The spinning axis of the top is arranged along the radial direction of the rotation axis. The “top” generates a force by which it rises perpendicularly from the ground, that is, so-called couple of forces. By using the couple of forces, thrust is generated.

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.

The invention relates to a micro colloid propeller, in particular to a micro array type colloid propeller. The micro array type colloid propeller realizes micromation and microthrust, solves the problems of difficult control of liquid supply and jetting of a nozzle of a jetting pole and the like and comprises the jetting pole, a drawing pole and a glass supporting frame body; a base plate of the jetting pole is etched with a plurality of tubular nozzles which are arranged in row, and is also etched with a plurality of strip etching grooves which are parallel; each strip etching groove is internally provided with a row of tubular nozzles; the bottom of each etching groove and the top part of the tubular nozzle are sputtered with an aluminium layer; one end of each etching groove respectively provided with a terminal communicated with the aluminium layer at the bottom of the groove; the inside of a liquid delivery channel of the tubular nozzle is processed into a porous silicon structure by adopting HF etching technique; the drawing pole is paliform, and strip grid seams thereof face the etching grooves of the jetting pole. The micro array type colloid propeller has the advantages of stable performance, high aligning precision, convenient processing and easy control for liquid supply and jetting and the like and can realize the purpose of controlling jetting of the nozzle by batches.

The present invention is a spacecraft electromagnetic propulsion system which provides thrust without expelling propellant. The system includes a multi-element capacitor with rotating segmented cathodes, and electromagnetic coils for generating magnetic fields. Interactions between the electromagnetic fields and the rotating charged capacitor elements produce unidirectional forces, while reaction momentum is carried away by the Poynting Vector fields in conformity with the currently understood principles of modern physics.

The invention provides two methods of propulsion for vertical and horizontal aerospace flight. Both methods manipulate the mass of a moving particle stream to achieve a desired result. In vertical propulsion, the invention circulates matter, within the confine of a machine, such that a portion of particle speed, which is perpendicular to gravity, is greater than the magnitude of velocity required for circular orbit of the planet, so as to develop radial acceleration relative to the planet center, creating a vertical force, associated with the mass of the particle stream times the radial acceleration, thereby generating vertical thrust. This methodology shall be referred to as “Gyroscopic Lift”. This invention also provides an additional method of horizontal propulsion. In horizontal propulsion, the invention may alternate acceleration and deceleration of matter, as it travels in a circulatory system, so as to create changing centripetal acceleration, and a directional imbalance of forces, thereby developing an outlet to be employed in horizontal thrust. As particles accelerate to the rear during the first ½ cycle an opposite but equal reaction causes forward horizontal propulsion. As particles decelerate in the 2nd ½ cycle, the opposition to slowing down causes forward horizontal propulsion. On port and starboard sides, forces causing particle stream acceleration or deceleration are balanced so as to cancel each others effect. This method of alternating acceleration and deceleration shall be referred to as “Impulse Propulsion”. Although the particular embodiment shown utilizes particles traveling perpendicular to gravity, it should not be concluded that this is the only arrangement possible. Whenever a particle has a component of velocity perpendicular to gravity in excess of circular orbit velocity, it is suitable to provide some measure of vertical thrust. Thus many particle accelerator designs utilizing this feature are feasible for the present invention. As an example, a particle accelerator whose axis of rotation is not aligned with the z axis should provide vertical lift and possibly other precession types of motion for a vehicle. As an alterative embodiment of this invention it provides some measure of gyroscopic lift that may be harnessed. Another example; If the circulatory path of the doughnut is comprised of a shape other than a circle it may increase the potential effect of impulse propulsion, but reduce gyroscopic lift efficiency. A shape comprised of two half circle accelerators, linked into a circulatory pattern by two parallel linear accelerators, would increase the potential horizontal thrust of impulse propulsion. Such is an alternative embodiment of this invention. Thus the invention embraces all space engines which utilize the principles of Gyroscopic Lift, or Impulse Propulsion. Obviously, many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced other than as specifically described.

A method and system generate lift for a vehicle relative to a planetary body rotating at a rotational speed. The vehicle incorporates two concentric lift rings in a common plane. The lift rings are positioned such that their common plane is approximately perpendicular to a force of gravity on the planetary body. The hit rings are rotated M opposing directions at speeds that are at least 20 times greater than the rotational speed of the planetary body.