US 11,680,543 B2
Extinguishable divert system
Russell Carlson, Reno, NV (US); Dustin Barr, Reno, NV (US); Allen Yan, Reno, NV (US); and Justin Carpenter, Loomis, CA (US)
Assigned to Valley Tech Systems, Inc., Reno, NV (US)
Filed by Valley Tech Systems, Inc., Reno, NV (US)
Filed on Sep. 14, 2021, as Appl. No. 17/447,623.
Application 17/447,623 is a division of application No. 16/411,108, filed on May 13, 2019, granted, now 11,143,143.
Claims priority of provisional application 62/670,685, filed on May 11, 2018.
Prior Publication US 2021/0404418 A1, Dec. 30, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F02K 9/26 (2006.01); B64G 1/40 (2006.01); F02K 9/94 (2006.01); F02K 9/22 (2006.01)
CPC F02K 9/26 (2013.01) [B64G 1/403 (2013.01); F02K 9/22 (2013.01); F02K 9/94 (2013.01); F05B 2270/301 (2013.01); F05D 2270/051 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A method for controlling the trajectory of a flight vehicle comprising:
(a) igniting solid propellant in a first hot gas generator and a second hot gas generator on the flight vehicle with a first hot gas stored in a hot gas accumulator and generating a second hot gas, the solid propellant in the first hot gas generator and the second hot gas generator burning at the same time;
(b) discharging the second hot gas through at least one divert thruster on the flight vehicle;
(c) extinguishing the solid propellant by rapidly depressurizing the first hot gas generator and the second hot gas generator; and
repeating (a) and (c) at least once;
wherein (b) and (c) can be performed in any order.