Abstract

An infused solid polymeric fuel for use in a hybrid rocket or as explosive ordnance. An infused solid polymeric fuel can include a porous polymeric body having continuous pores distributed throughout a volume of the polymeric body and connecting to an external surface of the polymeric body. A combustion enhancement agent can be infused into the polymeric body. The combustion enhancement agent can be deposited on interior surfaces of the pores and on the external surface of the polymeric body. The combustion enhancement agent can include a catalyst, an oxidizer, a hypergolic fuel, or a combination.

IPC Classes  ?

• C06B 45/20 - Compositions or products which are defined by structure or arrangement of component or product comprising a coated component the component base containing an organic explosive or an organic thermic component
• C06B 21/00 - Apparatus or methods for working-up explosives, e.g. forming, cutting, drying

Abstract

An exemplary embodiment of the present disclosure provides a method of sensing at least one characteristic of an analyte comprising: flowing media with the analyte through one or more microcavities; energizing the microcavity; and sensing at least one of the characteristics of the analyte via interrogation of the energized microcavity. Each of the one or more microcavities can comprise: a first mirror on a first planar surface; a second mirror on a second planar surface opposing the first planar surface; and at least one spacer between the first and second mirrors. The first mirror, second mirror, and at least one spacer can define a channel having an inlet and an outlet. The first and second mirrors can be positioned between the inlet and outlet.

IPC Classes  ?

• B01L 3/00 - Containers or dishes for laboratory use, e.g. laboratory glasswareDroppers

Abstract

For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method iteratively calculates a desired trajectory relative to the virtual point for a given spacecraft of the plurality of spacecraft using a relative orbital elements (ROE) state x of the virtual point and the given spacecraft. Model predictive control maintains the given spacecraft within an ROE constraint for a given time interval subject to a fuel consumption. In response to determining a drift trajectory of the given spacecraft is outside of a trajectory tolerance of the desired trajectory, maneuvering the given spacecraft to within the trajectory tolerance using a maneuver trajectory determined using the model predictive control.

IPC Classes  ?

• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• G06F 30/20 - Design optimisation, verification or simulation
• G06F 111/10 - Numerical modelling

Abstract

For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method further iteratively calculates an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. In response to determining the inner polytope boundary will be breached, the method maneuvers the given spacecraft to within the inner polytope boundary based on a switching condition, a guidance law, and model predictive control to minimize fuel consumption.

IPC Classes  ?

• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• G06F 30/20 - Design optimisation, verification or simulation