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US-12618418-B1 - Gas propulsion thrust device

US12618418B1US 12618418 B1US12618418 B1US 12618418B1US-12618418-B1

Abstract

The gas propulsion thrust device comprises a cone-shaped propulsion element with a rigid concave internal surface and a second convex external surface. The propulsion element is submerged in gas and aligned with a high-frequency linear actuator, which causes its reciprocal motion along the longitudinal axis, generating thrust. The device includes a thrust chamber that supports the actuator and surrounds the propulsion element, maintaining a consistent gap between the propulsion element and the chamber to direct gas from the second side to the first side. The chamber tapers around the propulsion element, and a gas directing cap is configured to direct gas around the second side towards the first side. Propulsion element is rigid and its shape remains unchanged during the operation. The reciprocal motion creates a gas pressure differential across the propulsion element, generating thrust by propelling gas away from the propulsion element in the opposite direction of propulsion. The device offers efficient and controlled thrust generation.

Inventors

  • Igor Morozov

Assignees

  • Igor Morozov

Dates

Publication Date
20260505
Application Date
20250329

Claims (8)

  1. 1 . A gas propulsion thrust device comprising: a cone-shaped propulsion element having a rigid concave first side, the concave first side extends to an outer edge and is axisymmetric about a longitudinal axis aligned along the direction of propulsion thrust, the propulsion element having a convex second side adjacent to the concave first side, the propulsion element is submerged in and surrounded by gas, a high-frequency linear actuator aligned along a direction of propulsion thrust, the high-frequency linear actuator operates at a frequency from 500 Hz to 200 kHz and is operatively cooperating with the propulsion element to cause reciprocal motion thereof along the longitudinal axis and along the direction of propulsion thrust, wherein the high-frequency linear actuator comprises a plurality of linear actuators positioned symmetrically around and individually spaced along the outer edge of the propulsion element, a thrust chamber supporting the high-frequency actuator fixedly attached thereto, the thrust chamber surrounds the propulsion element while being spaced away from the outer edge thereof by a gap configured to direct gas from the second side to the first side of the propulsion element, wherein the thrust chamber is shaped to maintain the same gap throughout a reciprocal motion of the propulsion element within the thrust chamber, the thrust chamber is shaped to narrow and taper around the propulsion element at the second side thereof, and a gas directing cone-shaped cap mounted on the thrust chamber adjacent and outside the second side of the propulsion element, the gas directing cone-shaped cap is configured to direct gas around a periphery thereof and further around the second side and toward the first side of the propulsion element, wherein the thrust chamber and the gas directing cone-shaped cap are submerged in and surrounded by the gas surrounding the cone-shaped propulsion element, wherein the reciprocal motion of the propulsion element within the thrust chamber is done without altering the shape of the propulsion element, and wherein the reciprocal motion of the propulsion element forms a high gas pressure zone on the concave first side of the propulsion element and a low gas pressure zone on the convex second side thereof, thereby generating a gas pressure differential across the propulsion element and along the direction of propulsion thrust causing propulsion of gas away from the concave first side of the propulsion element and in a direction opposite the direction of propulsion thrust.
  2. 2 . The gas propulsion thrust device, as in claim 1 , further comprising an inert gas supply system configured for injecting an inert gas in the thrust chamber on the first side of the propulsion element, the inert gas being different from the gas surrounding the propulsion element.
  3. 3 . The gas propulsion thrust device, as in claim 1 , further comprising a liquid supply system configured for injecting a mist of liquid in the thrust chamber on the first side of the propulsion element, wherein the liquid is different from the gas surrounding the propulsion element and may be mixed therewith.
  4. 4 . The gas propulsion thrust device, as in claim 1 , wherein the first side is spaced apart from the second side to define a thickness of the propulsion element to be less than a diameter of the outer edge thereof.
  5. 5 . The gas propulsion thrust device, as in claim 4 , wherein the first side of the propulsion element is parallel to the second side thereof.
  6. 6 . The gas propulsion thrust device, as in claim 2 , wherein the inert gas supply system is positioned within the concave first side of the propulsion element.
  7. 7 . A gas propulsion thrust device comprising: a cone-shaped propulsion element having a rigid concave first side, the concave first side extends to an outer edge and is axisymmetric about a longitudinal axis aligned along the direction of propulsion thrust, the propulsion element having a convex second side adjacent to the concave first side, the propulsion element is submerged in and surrounded by gas, the propulsion element is equipped with a plurality of electromagnetic coils, a magnetic levitation high-frequency linear actuator aligned along a direction of propulsion thrust, the high-frequency linear actuator operates at a frequency from 500 Hz to 200 kHz and comprises a plurality of permanent magnets operatively cooperating with the plurality of electromagnetic coils of the propulsion element to form a plurality of electromagnets, the electromagnetic coils configured to control position and cause reciprocal motion of the propulsion element along the direction of propulsion thrust, wherein the magnetic levitation high-frequency linear actuator comprises a plurality of linear actuators positioned symmetrically around and individually spaced along the outer edge of the propulsion element, a thrust chamber supporting the high-frequency actuator fixedly attached thereto, the thrust chamber surrounds the propulsion element while being spaced away from the outer edge thereof by a gap configured to direct gas from the second side to the first side of the propulsion element, wherein the thrust chamber is shaped to maintain the same gap throughout a reciprocal motion of the propulsion element within the thrust chamber, the thrust chamber is shaped to narrow and taper around the propulsion element at the second side thereof, and a gas directing cone-shaped cap mounted on the thrust chamber adjacent and outside the second side of the propulsion element, the gas directing cone-shaped cap is configured to direct gas around a periphery thereof and further around the second side and toward the first side of the propulsion element, wherein the thrust chamber and the gas directing cone-shaped cap are submerged in and surrounded by the gas surrounding the cone-shaped propulsion element, wherein the reciprocal motion of the propulsion element within the thrust chamber is done without altering the shape of the propulsion element, and wherein the reciprocal motion of the propulsion element forms a high gas pressure zone on the concave first side of the propulsion element and a low gas pressure zone on the convex second side thereof, thereby generating a gas pressure differential across the propulsion element and along the direction of propulsion thrust causing propulsion of gas away from the concave first side of the propulsion element and in a direction opposite the direction of propulsion thrust.
  8. 8 . The gas propulsion thrust device, as in claim 7 , wherein the magnetic levitation high-frequency linear actuator is configured with the plurality of permanent magnets mounted on the thrust chamber and the plurality of electromagnetic coils mounted on the propulsion element.

Description

CROSS-REFERENCE DATA This US Patent Application claims a foreign priority date benefit to my Ukrainian Patent Application No. a202405732 filed on 4 Jan. 2024, entitled “GAS PROPULSION DEVICE”. This application is incorporated herein by reference in its entirety. BACKGROUND Without limiting the scope of the invention, its background is described in connection with gas propulsion devices. More particularly, the invention describes a device configured to convert the reciprocal motion of an actuator into a gas propulsion oriented in the desired direction. The device of the invention may be used as a main or a secondary thrust engine for a flight apparatus, for example, an airplane, an air taxi, a rocket, a helicopter, a hovercraft, a powered parachute, an air balloon, as well as other manned and unmanned aircraft devices. A rotating propeller is the main thrust device used in many aircraft devices flying with speeds not exceeding the speed of sound. These devices include drones, quadcopters, automated air taxis, and other devices configured for take-off and landing in highly populated areas such as cities. Close encounters with people nearby creates a risk of injury to people from the rotation of one or more propellers of such a flying device. A recent trend in aerial taxi systems increased safety risks from high-speed, fast-rotating blades used in vertical takeoff and landing. These rotor assemblies, close to passengers and urban infrastructure, pose hazards, especially in dense city settings. The need exists therefore for a simpler and safer engine device that can be configured to provide both the vertical lifting power as well as the horizontal thrust for an aircraft used in highly populated areas. SUMMARY Accordingly, it is an object of the present invention to overcome these and other drawbacks of the prior art by providing a novel gas propulsion device configured to provide a superior propulsion force as compared to prior art. It is another object of the present invention to provide a gas propulsion thrust device with increased efficiency of converting reciprocal movement energy to propagation forces moving the device through the gas medium. It is a further object of the present invention to provide a novel gas propulsion thrust device with gas flow dynamics characterized by improved stability throughout various components of the device. The present invention aims to create a gas propulsion device that enhances thrust and stabilizes the direction of the gas flow. In some embodiments, it further allows for additional thrust increase by injecting inert gases or their mixtures to enable operation in limited or standard atmospheric conditions and using a combustion chamber to ensure safety and emergency operation. A gas propulsion device comprises a cone-shaped gas propulsion element with a circular outer edge, featuring a concave inner surface facing its first side and a convex outer surface facing its second side, opposite to the first side. A high-frequency actuator is also provided and oriented along the propulsion thrust direction. It is operatively connected to the gas propulsion element to cause its reciprocating motion along the thrust direction with sufficient speed and amplitude to form a high-pressure gas zone on its first side and a low-pressure gas zone on its second side thereof. This, in turn, creates gas flow from the gas propulsion element in a direction opposite to the thrust direction. The gas propulsion element is placed in a thrust chamber with a gap between its outer edge and the inner surface of the thrust chamber. A directional cap may be placed on the second side of the gas propulsion element to redirect the gas flow from the second side to the first side. Further embodiments focus on increasing thrust by optimizing the thrust chamber design, including a narrowed upper part and conical sections, applying magnetic levitation to eliminate mechanical losses, and using high-frequency linear drives such as piezoelectric stacks, magnetostrictive transducers, ultrasonic resonators, and horns. Additionally, embodiments are described which are configured for injecting inert gases, liquid mists, and other mixtures so as to increase pressure and cavitation effects. Other embodiments integrate the propulsion element with a combustion chamber, which provides additional thrust and expands the functional capabilities of the device. The present invention enhances efficiency, stabilizes the flow direction, and allows the device to operate in various modes including at supersonic speeds. BRIEF DESCRIPTION OF THE DRAWINGS Subject matter is particularly pointed out and distinctly claimed in the concluding portion of the specification. The foregoing and other features of the present disclosure will become more fully apparent from the following description and appended claims, taken in conjunction with the accompanying drawings. Understanding that these drawings depict only several embodiments in accordanc