GB2591653A

GB2591653A - In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane

Info

Publication number: GB2591653A
Application number: GB2103317.0A
Authority: GB
Inventors: A Burgener John; Lee Delong Daniel; Burnside Clapp Mitchell
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-09-19
Filing date: 2018-09-19
Publication date: 2021-08-04
Anticipated expiration: 2038-09-19
Also published as: GB202103317D0; GB2591653B; WO2020060549A1

Abstract

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.

Claims

1. A process of launching a high altitude vehicle designed to fly to high altitudes above 100,000 feet comprising the steps of: connecting a tow cable and fuel and oxidant transfer lines between a towing airplane and the high altitude vehicle for towing the unpowered high altitude vehicle behind the towing airplane from takeoff and for an initial portion of a flight, the high altitude vehicle having a fuel tank and an oxidant tank and having less than 10% fuel and oxidant in the respective tanks from takeoff and for the initial portion of the flight; transferring fuel and oxidant from the towing airplane to the high altitude vehicle via the fuel and oxidant transfer lines at a desired altitude above 25,000 feet and at a desired flight speed sufficient for lift of the high altitude vehicle to support the vehicle, transferred fuel, and transferred oxidant in flight; disconnecting the tow cable and fuel and oxidant transfer lines from the high altitude vehicle; and commencing powered flight of the high altitude vehicle substantially at the desired altitude and at the desired flight speed, whereby the high altitude vehicle commences flight from takeoff with a minimal amount of fuel and oxidant and with a concomitant lower structural weight and smaller wings than if configured for self-powered takeoff and flight with sufficient fuel and oxidant in the respective tanks for independently achieving the desired altitude and desired flight speed and, after transfer of the fuel and oxidant from the towing airplane to the high altitude vehicle, the high altitude vehicle commences self-powered flight with maximum fuel and oxidant while substantially at the desired altitude and desired flight speed, enabling achievement of a higher altitude and speed and/or to carry a larger payload than if configured for self-powered takeoff with fully loaded fuel and oxidant tanks.

2. The process of claim 1, wherein the high altitude vehicle is configured to fly to the ground and for re-use at least one additional cycle of the connecting, transferring, disconnecting, and commencing steps.

3. The process of claim 1, wherein the high altitude vehicle is self-powered with one or more of an engine selected from the group consisting of a jet engine, rocket engine, scramjet engine, ramjet engine, plasma engine, and hybrid air breathing rocket engine .

4. The process of claim 1, wherein the high altitude vehicle is a drone either remotely operated or self-controlled via on-board guidance and control systems.

5. The process of claim 1, wherein the high altitude vehicle is under the control of an on board person acting as a pilot to control the high altitude vehicle.

6. A process of launching a high altitude vehicle comprising the steps of: mechanically and fluidly connecting the high altitude vehicle to a support aircraft, whereby the support aircraft is configured for carrying the high altitude vehicle, with respective engine(s) unstarted, during takeoff and for an initial portion of a flight, the support aircraft carrying fuel and oxidant for use by the high altitude vehicle, the high altitude vehicle having fuel and oxidant tanks and having less than 10% fuel and oxidant in the respective tanks at the commencement of the flight, from the ground to the desired altitude; transferring fuel and oxidant from the support aircraft to the high altitude vehicle while in flight at a desired altitude above 25,000 feet and at a desired flight speed sufficient to enable the lift of the high altitude vehicle to support the vehicle, transferred fuel, and transferred oxidant; mechanically and fluidly disconnecting the high altitude vehicle from the support aircraft substantially at the desired altitude and at the desired flight speed; and commencing self-powered flight of the high altitude vehicle substantially at the desired altitude and substantially at the desired flight speed of the support aircraft from which the high altitude vehicle is disconnected, whereby the high altitude vehicle is configurable to have a lower structural weight than if configured to commence self-powered flight from the ground with full fuel and oxidant tanks, thereby enabling achievement of a higher altitude and flight speed and/or a greater payload capacity than would be possible if configured to commence self-powered flight from the ground with full fuel and oxidant tanks.

7. The process of claim 6, wherein the high altitude vehicle is configured to fly to the ground and for re-use at least one additional cycle of the mechanically and fluidly connecting, transferring, mechanically and fluidly disconnecting, and commencing steps .

8. The process of claim 6, wherein the high altitude vehicle is self-powered with one or more of an engine selected from the group consisting of a jet engine, rocket engine, scramjet engine, ramjet engine, plasma engine, and hybrid air breathing rocket engine.

9. The process of claim 6, wherein the high altitude vehicle is a drone either remotely operated or self-controlled via on-board guidance and control systems.

10. The process of claim 6, wherein the high altitude vehicle is under the control of an on board person acting as a pilot to control the high altitude vehicle.