US 12,297,792 B2 · Hybrid solar thermal and chemical vehicle configurations for space mining applications

Abstract

Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area. Multiple propellants can be present in a single chamber and be forced from a nozzle to produce thrust. Pressure in a rocket can be achieved from heating inert gasses, and alternatively or simultaneously, from mixing and igniting non-inert gasses.

Claims31

Dependent claims

A rocket propulsion system configured to provide rocket thrust, comprising:

a wall generally enclosing a rocket chamber;
a solar absorber material positioned within the rocket chamber;
a rocket nozzle;
a solar power collection system comprising a plurality of transparent windows including a first transparent window configured to allow one or more propulsive gases to pass therethrough and a second transparent window, each of the plurality of transparent windows formed of a solid transparent material, the solar power collection system configured to:
collect solar energy from the sun,
generate a solar energy beam by focusing the collected solar energy with at least the second transparent window,
heat the solar absorber material with the solar energy beam to transfer heat to the one or more pressurized propulsive gases, and
expel the heated pressurized propulsive gases through the rocket nozzle;
a pressurized gas inlet configured to introduce the one or more propulsive gases into a first plenum chamber formed between the between the first and second transparent windows;
a manifold configured to mix combustible materials;
and
an igniter configured to ignite combustion in the combustible materials;
the wall of the rocket chamber generally forms a frustoconical portion surrounding a propellant exit configured to allow the heated pressurized propulsive gases and byproducts from the combustion of the combustible materials to exit to the rocket nozzle.

10 more elements

A hybrid rocket motor configured for multiple energy modes within a single rocket chamber immediately upstream from a nozzle, the motor comprising:

a wall generally enclosing a hybrid rocket chamber;
a first window forming part of the wall, the window configured to allow radiation to enter while helping contain heat energy;
a second window spaced apart from the first window and configured to allow propellant to pass therethrough;
a thermal mass positioned to absorb radiation after entry through the window;
a pressurized gas inlet configured to introduce gas into the chamber such that the gas is heated by contact with the thermal mass;
a manifold configured to mix combustible materials;
and
an igniter configured to ignite combustion in the combustible materials;
the wall of the rocket chamber generally forming a frustoconical portion surrounding a propellant exit configured to allow pressurized gas and combustion byproducts to exit to the nozzle.

6 more elements

Dependencies are inferred from the claim text.

Hybrid solar thermal and chemical vehicle configurations for space mining applications

Life of this patent

Hybrid solar thermal and chemical vehicle configurations for space mining applications

Life of this patent

Abstract

Claims31