Sparton Corporation

David J Powell

Keith R Huber

Earl H Mark

Taylor J Durrance

Charles M Nowell, Jr

Tanner Sizemore

John T Houck

An axial piercing mechanism for a pressurized gas canister includes a housing, electric motor assembly, pushrod assembly, and lancet. The housing defines one or more radial exhaust ports and coaxial internal cavities. The electric motor assembly and pushrod assembly are disposed in the respective first and second cavities. The pushrod assembly is coupled to the electric motor assembly and is rotatably driven along the longitudinal axis thereby. The lancet is coupled to the pushrod assembly. The housing includes a second end that receives or couples to a sealed end of the pressurized gas canister proximate the lancet such that the electric motor assembly, when energized, causes the pushrod assembly and lancet to translate along the longitudinal axis, pierce a sealed end/diaphragm of the canister, and release pressurized gas through the exhaust port. A system includes the axial piercing mechanism and the pressurized gas canister.

Axial piercing mechanism for pressurized gas canister

A payload launch system includes a launch tube, payload, rocket tube, pressurized motor assembly, and control system. The motor assembly has a launch actuator and an accumulator housing containing compressed gas. The accumulator housing defines a vent opening having a closure. The control system transmits an actuation signal to the actuator in response to a launch request signal to open the closure and cause a discharge of pressure into the launch tube. This causes the rocket tube to launch from the launch tube to a threshold altitude in a single gaseous thrust phase. A method includes deploying a launch system, transmitting a launch actuation signal to the launch actuator via a control system, and opening a closure to allow compressed gas to enter the launch tube, thereby launching the rocket tube from the launch tube to a threshold altitude in the single gaseous thrust phase.

Payload launch system and method

A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

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Sanford, FL, United States of America

David J Powell