公开(公告)号：US12196162B1

公开(公告)日：2025-01-14

申请号：US17986711

申请日：2022-11-14

Applicant: Astron Aerospace LLC

Inventor： Matthew T. Riley

IPC: F02M21/00 ,  F02M21/02 ,  F02M47/06 ,  F02M51/00 ,  F02M51/04 ,  F02M51/06

Abstract: A fuel injection system is provided. The system includes a completely sealed housing surrounding the key components of the fuel injection system.

公开(公告)号：US11788462B2

公开(公告)日：2023-10-17

申请号：US17389239

申请日：2021-07-29

Applicant: ASTRON AEROSPACE LLC

Inventor： Matthew T. Riley

IPC: F02B53/04 ,  F01C1/08 ,  F02B53/02 ,  F01M13/00 ,  F02B55/14 ,  F02B55/02 ,  F02B55/08 ,  F02B53/08

CPC classification number: F02B53/04 ,  F01C1/08 ,  F01M13/00 ,  F02B53/02 ,  F02B53/08 ,  F02B55/02 ,  F02B55/08 ,  F02B55/14

Abstract: A rotary engine, parts thereof, and methods associated therewith is provided. The engine is modular and adjustable to accommodate a variety of requirements and preferences. The system includes a combustion assembly having a housing and a power rotor positioned therein. The power rotor rotates in a first direction from the beginning of each combustion process through the end of each exhaust process. The system also includes a compression assembly linked to the combustion assembly such that the compression rotor rotates in the first direction from the beginning of each intake process through the end of each compression process. A tank assembly in fluid communication with the compression assembly and the combustion assembly provides stability to the system while eliminating or otherwise reducing transitional loses.

公开(公告)号：US11384684B2

公开(公告)日：2022-07-12

申请号：US16732318

申请日：2020-01-01

Applicant: ASTRON AEROSPACE LLC

Inventor： Matthew T. Riley

IPC: F02B53/02 ,  F02B53/04 ,  F02B53/08 ,  F02B53/12 ,  F02B55/00 ,  F02B55/08 ,  F02B55/12 ,  F02B55/14 ,  F01C11/00

Abstract: A rotary engine, parts thereof, and methods associated therewith is provided. The engine is modular and adjustable to accommodate a variety of requirements and preferences. The system includes a combustion assembly having a housing and a power rotor positioned therein. The power rotor rotates in a first direction from the beginning of each combustion process through the end of each exhaust process. The system also includes a compression assembly linked to the combustion assembly such that the compression rotor rotates in the first direction from the beginning of each intake process through the end of each compression process. A tank assembly in fluid communication with the compression assembly and the combustion assembly provides stability to the system while eliminating or otherwise reducing transitional loses.

公开(公告)号：US12270331B2

公开(公告)日：2025-04-08

申请号：US18587705

申请日：2024-02-26

Applicant: ASTRON AEROSPACE LLC

Inventor： Matthew T. Riley

IPC: F02B53/04 ,  F01C11/00 ,  F01C21/08 ,  F02M25/028 ,  F02M26/04 ,  F02M27/04

Abstract: The instant invention includes systems for and methods of maximizing efficiencies in an internal combustion engine while minimizing costs and weight for the same and while also minimizing maintenance requirements for the same. Such systems include a compression assembly for compressing fluid to a desired pressure for combustion (such as above 220 psi) and a combustion assembly configured to receive at least a portion of the compressed volume of air for each power stroke. In this way, the power stroke of the engine is independent of the compression stroke of the engine, thereby eliminating or otherwise minimizing transitional losses associated with the same.

公开(公告)号：US12163461B2

公开(公告)日：2024-12-10

申请号：US17862172

申请日：2022-07-11

Applicant: ASTRON AEROSPACE LLC

Inventor： Matthew T. Riley

IPC: F02B53/02 ,  F01C11/00 ,  F02B53/04 ,  F02B53/08 ,  F02B53/12 ,  F02B55/00 ,  F02B55/08 ,  F02B55/12 ,  F02B55/14

Abstract: A rotary engine, parts thereof, and methods associated therewith is provided. The engine is modular and adjustable to accommodate a variety of requirements and preferences. The system includes a combustion assembly having a housing and a power rotor positioned therein. The power rotor rotates in a first direction from the beginning of each combustion process through the end of each exhaust process. The system also includes a compression assembly linked to the combustion assembly such that the compression rotor rotates in the first direction from the beginning of each intake process through the end of each compression process. A tank assembly in fluid communication with the compression assembly and the combustion assembly provides stability to the system while eliminating or otherwise reducing transitional loses.