Hmx, Inc.

Oisin Biotechnologies, Inc.

Gary Charles Hudson

Bevin C McKinney

Matthew Rein Scholz

John David Lewis

Provided nucleic acid-based expression construct for the target cell-specific production of a therapeutic protein, such as a pro-apoptotic protein, within a target cell, including a target cell that is associated with aging, disease, or other condition, in particular a target cell that is a senescent cell or a cancer cell. Also provided are formulations and systems, including fusogenic lipid nanoparticle (LNP) formulations and systems, for the delivery of nucleic acid-based expression constructs as well as methods for making and using such nucleic acid-based expression constructs, formulations, and systems for reducing, preventing, and/or eliminating the growth and/or survival of a cell, such as a senescent cell and/or a cancer cell, which is associated with aging, disease, or other condition as well as methods for the treatment of aging, disease, or other conditions by the in vivo administration of a formulation, such as a fusogenic LPN formulation, comprising an expression construct for the target cell-specific production of a therapeutic protein, such as a pro-apoptotic protein, in a target cell that is associated with aging, disease, or other condition, in particular a target cell that is a senescent cell or a cancer cell.

Fusogenic lipid nanoparticles for target cell-specific production of a therapeutic protein

A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Capsule spacecraft emergency landing system

An orbital stage system has an orbital stage and one or more launch stages. The orbital stage incorporates an orbital maneuvering system (OMS) and an abort propulsion system which both utilize the same propellants, propellant tankage, and propellant pressurization system, but which employ radically different engines. The OMS engines are comprised of at least two engines which have a combined thrust in the neighborhood of 1/10 the weight of the orbital stage, an area ratio of 50 or more and an operating life of many hundred seconds, preferably many thousands of seconds or more. The abort engine may be a single engine and typically has a thrust of three, four, or more times the weight of the vehicle and an area ratio in the neighborhood of two and an operating life of at most a few tens of seconds.

Integrated abort rocket and orbital propulsion system

A launch vehicle which employs a rotor similar to a helicopter. The vehicle has a four bladed rotor which is mounted on the vehicle body. The body of the vehicle includes propellant tanks and a payload compartment contained within an integral aeroshell. Rocket engines used to propel the vehicle into earth orbit are mounted at the ends of the rotor blades. The engines are connected by propellant feed lines to a propellant transfer hub surrounding the axis of rotation of the rotor. Propellants are fed from an oxidizer tank and a fuel tank through a propellant transfer coupling to oxidizer and fuel lines which extend to the engines at the rotor blades ends. The rotor blades incorporate air foils. To operate the vehicle the vehicle is positioned on a concrete or asphalt pad and fueled with liquid oxygen and kerosene. The engine are positioned tangent to the blade paths and ignited. The thrust of the engines which is tangent to the rotor causes the rotor to turn which accelerates the rotor thus increasing the pressure developed by the propellants as they flow towards the engines. When the rotor has reached operational speed the airfoil creates sufficient lift that the vehicle begins to ascend vertically. As the vehicle exits the atmosphere the rocket engines are aligned with the flight path of the vehicle. After reentry from earth orbit the vehicle utilizes the spun up rotor to fly the vehicle to a soft landing.

Growing community of inventors

Redwood City, CA, United States of America

Gary Charles Hudson