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 tra
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.
대표청구항▼
1. A payload launch system comprising: a cylindrical outer launch tube having a longitudinal axis;a payload;a rocket tube containing the payload, wherein the rocket tube is contained within the outer launch tube;a pressurized motor assembly held stationary within the outer launch tube, wherein the p
1. A payload launch system comprising: a cylindrical outer launch tube having a longitudinal axis;a payload;a rocket tube containing the payload, wherein the rocket tube is contained within the outer launch tube;a pressurized motor assembly held stationary within the outer launch tube, wherein the pressurized motor assembly includes a launch actuator and an accumulator housing containing a volume of compressed gas and defining a vent opening having a closure; anda control system in communication with the launch actuator;wherein the control system is configured to transmit a launch actuation signal to the launch actuator in response to a launch signal to thereby open the closure of the vent opening and thereby cause a discharge of the compressed gas from the actuator housing into the outer launch tube, thereby translating the rocket tube along the longitudinal axis and launching the rocket tube from the outer launch tube in a single gaseous thrust phase, such that the pressurized motor assembly remains in the outer launch tube after launch of the rocket tube. 2. The payload launch system of claim 1, further comprising tether material connecting the rocket tube to the outer launch tube, wherein flight of the rocket tube is arrested at a threshold altitude via tension on the tether material. 3. The payload launch system of claim 1, wherein the compressed gas is selected from the group consisting of carbon dioxide, nitrogen, and air. 4. The payload launch system of claim 1, wherein the outer launch tube has a diameter of 3 inches and a length of 39 inches. 5. The payload launch system of claim 1, wherein the launch actuator includes a sacrificial element holding the closure in a closed position, and wherein the launch actuation signal severs the sacrificial element to thereby open the closure. 6. The payload launch system of claim 1, wherein the control system includes at least one of a sea water switch operable for determining that the payload launch system is submerged below a surface of a body of water and a pressure switch operable for confirming that the payload launch system is exposed to hydrostatic pressure. 7. The payload launch system of claim 1, further comprising an end cap disposed at an end of the outer launch tube and configured to separate from the outer launch tube in response to a threshold force from the rocket tube along the longitudinal axis. 8. The payload launch system of claim 7, wherein the payload is an unmanned aerial vehicle. 9. The payload launch system of claim 1, further comprising: an end cap disposed at an end of the outer launch tube and configured to separate from the cylindrical outer launch tube in response to a threshold force from the rocket tube along the longitudinal axis; andtether material connecting the rocket tube to the outer launch tube, wherein the tether material is configured to arrest flight of the rocket tube at a threshold altitude;wherein the control system includes a sea water switch operable for determining that the launch system is submerged below a surface of a body of water and a set of inertial sensors for determining an attitude of the launch system with respect to the surface;wherein the control system is configured, when the sea water switch detects that the launch system is not submerged below the surface of the body of water and the attitude of the launch system is within a calibrated window, to launch the rocket tube from the outer launch tube to the threshold altitude, only when the launch system is not submerged and the attitude is within the calibrated window, by transmitting a launch actuation signal to the launch actuator, and wherein the launch actuation signal opens the closure of the vent opening and causes a discharge of the compressed gas from the actuator housing into the outer launch tube in the single gaseous thrust phase, thereby translating the rocket tube along the longitudinal axis and launching the rocket tube from the outer launch tube. 10. The payload launch system of claim 9, wherein the outer launch tube has a diameter of 3 inches and a length of 39 inches. 11. The payload launch system of claim 9, wherein the launch actuator includes a sacrificial element holding the closure in a closed position, and wherein the actuation signal is an electrical current that is sufficient for severing the sacrificial element. 12. The payload launch system of claim 9, wherein the payload is an unmanned aerial vehicle. 13. A method for launching a payload, comprising: deploying a payload launch system that includes a launch actuator, a pressurized motor assembly having an accumulator housing containing a volume of compressed gas, and a rocket tube containing the payload within a cylindrical outer launch tube having a longitudinal axis;transmitting a launch actuation signal to the launch actuator via a control system in response to a launch request signal; anddischarging the compressed gas from the accumulator housing into the outer launch tube to thereby launch the rocket tube from the outer launch tube to a threshold altitude via gaseous thrust from the pressurized motor assembly in a single gaseous thrust phase, such that the pressurized motor assembly remains in the outer launch tube after the launch of the rocket tube. 14. The method of claim 13, wherein deploying the payload launch system includes ejecting the payload launch system into a body of water. 15. The method of claim 14, further comprising determining, via a sea water switch of the control system, that the outer launch tube is not submerged below a surface of the body of water before transmitting the launch actuation signal, and via an inertial sensor whether the payload launch system has attained a predetermined attitude with respect to the surface, and discharging the compressed gas in response to the launch actuation signal only when the payload launch system has attained the predetermined attitude above the surface. 16. The method of claim 14, wherein deploying the payload launch system includes ejecting the payload launch system into the body of water via a signal ejector tube of a submarine submerged beneath a surface of the body of water. 17. The method of claim 13, further comprising: connecting the rocket tube to the outer launch tube via tether material;arresting flight of the rocket tube near the threshold altitude via tension on the tether material; andexpelling the payload from the rocket tube via momentum of the rocket tube. 18. The method of claim 13, wherein the compressed gas is selected from the group consisting of carbon dioxide, nitrogen, and air. 19. The method of claim 13, wherein the launch actuator includes a sacrificial element, and wherein transmitting the launch actuation signal includes severing the sacrificial element via an electrical current. 20. The method of claim 13, further comprising determining, via a pressure switch of the control system, that the payload launch system is exposed to hydrostatic pressure before transmitting the launch actuation signal.
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이 특허에 인용된 특허 (6)
MacLeod, Brenda Brennan; Moody, Paul E., Pressure-balanced gas turbine underwater launcher.
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