Unmanned aircraft systems for firefighting

Abstract

A firefighting aircraft adapted for use in an unmanned aircraft system includes a storage tank for firefighting fluid, having a plurality of filling ports spaced from one another. A probe carries a conduit that is in fluid communication with the storage tank. The conduit receives water from a body of water overflown by the aircraft. A filling system for controls the flow of water to and from the storage tank, and includes a remotely and automatically operable valve respectively associated with each filling port. A control system is in communication with each valve, and is operative to command the position of each valve to regulate the flow of fluid through each filling port. A baffle may be further provided internal to the storage tank at least partially defining a first chamber within the tank. The baffle may include one or more baffles, and be provided substantially vertically, horizontally, parallel with or transverse to a longitudinal axis of the aircraft, or otherwise, and is operative to contain water entering the tank through the filling port, substantially filling the first chamber before filing any other portion of the storage tank.

1 .- 11 . (canceled) 
     
     
         12 . A firefighting aircraft adapted for use in an unmanned aircraft system, the aircraft comprising:
 a storage tank for firefighting fluid having a at least one filling port;   a probe carrying a conduit in fluid communication with the storage tank, the probe being operative to receive water from a body of water overflown by the aircraft;   a baffle internal to the storage tank at least partially defining a first chamber within the tank, the baffle being operative to contain water entering the tank through the filling port, substantially filling the first chamber before filing any other portion of the storage tank.   
     
     
         13 . The firefighting aircraft according to  claim 12 , wherein the first chamber in centered substantially coincident with a center of gravity of the aircraft. 
     
     
         14 . The firefighting aircraft according to  claim 12 , wherein the baffle comprises a substantially vertical baffle in connected with a floor of the storage tank. 
     
     
         15 . The firefighting aircraft according to  claim 12 , wherein the baffle extends substantially transversely to a longitudinal axis of the aircraft. 
     
     
         16 . The firefighting aircraft according to  claim 12 , wherein the baffle extends substantially parallel to a longitudinal axis of the aircraft. 
     
     
         17 . The firefighting aircraft according to  claim 12 , wherein the baffle comprises a plurality of baffles defining a second chamber substantially co-centered with the first chamber, the second baffle positioned and operative to substantially contain within the second chamber water overfilling the first chamber, substantially filling the first and second chambers before filing any other portion of the storage tank. 
     
     
         18 . The firefighting aircraft according to  claim 12 , wherein the baffle comprises a substantially horizontal baffle extending from a side wall of the storage tank, operative to regulate the vertical movement of fluid within the storage tank. 
     
     
         19 . The firefighting aircraft according to  claim 12 , wherein the baffle forms part of an opening at the boundary of the first chamber, the opening operative to regulate the flow of fluid from the first chamber into the remainder of the storage tank. 
     
     
         20 . The firefighting aircraft according to  claim 12 , wherein the storage tank further comprises a vent that is selectively in fluid communication with dynamic air pressure of slipstream air over the aircraft, static air pressure surrounding the aircraft, a source of positive air pressure and a source of negative air pressure. 
     
     
         21 . The firefighting aircraft according to  claim 12 , further comprising a discharge gate for discharging fluid carried in the storage tank from the aircraft; and
 a valve operative to place the storage tank in fluid communication with the conduit or the discharge gate.   
     
     
         22 . The firefighting aircraft according to  claim 12 , wherein the probe is articulable from a first position wherein a distal end of the probe places the conduit in fluid communication with a body of water overflown by the aircraft, to a second position wherein the aerodynamic drag on the aircraft attributable to the probe is reduced compared to the first position. 
     
     
         23 . The firefighting aircraft according to  claim 22 , further comprising a recess for receiving the probe in the second position. 
     
     
         24 . The firefighting aircraft according to  claim 23 , further comprising a door that covers the probe and the recess when the probe is in the second position. 
     
     
         25 . The firefighting aircraft according to  claim 22 , further comprising an actuator operative to move the probe between the first and second positions.