# US 10,767,637 B2 · Scalable and economic solid-state thermokinetic thruster

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- Number: US 10,767,637 B2
- Document ID: US10767637B2
- Status: Granted
- Kind: B2
- Application number: 15/923,496
- Filed: 2018-03-16
- Published: 2018-09-20
- Granted: 2020-09-08
- Earliest claimed: 2017-03-17
- Applicants: Sean Preston Wagner; Thomas Thundat
- Inventors: Sean Preston Wagner; Thomas Thundat
- Web page: https://patentgrep.com/patent/US10767637B2

## CPC

- F03H 99/00: Subject matter not provided for in other groups of this subclass
- F03G 7/016: {Photosensitive actuators, e.g. using the principle of Crookes radiometer}
- Y02E 10/46: Conversion of thermal power into mechanical power, e.g. Rankine, Stirling or solar thermal engines
- F03H: PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR (from combustion products F02K)
- F03G: SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR (arrangements in connection with power supply in vehicles from force of nature B60K16/00; electric propulsion with power supply in vehicles from force of nature B60L8/00)
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION

## Abstract

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.

## Claims

### Claim 1

A solid-state device capable of creating unidirectional thrust based off the principles of the radiometric effect, being comprised of:
a. A porous plate structure of any thickness between 10 nm and 100 mm and comprising of at least two major surfaces defined as a surface that comprises between 15-50% of the external surface area of the device;
b. The pores on each major surface being of a regular patterning or a random arrangement, such that each pore on each surface is connected to at least one other pore on the opposing major surface, with the smallest dimension of said pores in the plane of the major surfaces being between 0.5-10 times the length of the Mean Free Path of the gas in which the device is to operate;
c. A coating of uniform thickness, between 2-20 nm, of thermally conductive material, or catalytic material for the growth of thermally conductive material in a subsequent step, on one of the major surfaces and continuing through the majority of the thickness of the pores;
d. A coating of uniform thickness, between 2-100 nm, of thermally conductive material, or catalytic material, for the growth of thermally conductive material in a subsequent step, on the opposite major surface and extending a distance between 1-10 times that of the Mean Free Path of the gas in which a thruster is to operate, down each pore from said major surface;
e. A gap, or a thermally non-conductive material coating, measuring a distance equal to that of the Mean Free Path of the gas the device is designed to be operating in, plus or minus 50% of the length of the Mean Free Path, between the coatings of uniform, but with potentially different thickness.