Abstract: A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.

Abstract: A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.

Abstract: A hybrid-like liquid fuel motor (the “motor”) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.

Abstract: A hybrid-like liquid fuel motor (the “motor”) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.

Abstract: An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.

Abstract: An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.