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 o
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.
대표청구항▼
1. A firefighting aircraft adapted for use in an unmanned aircraft system, the aircraft comprising: a storage tank for firefighting fluid having a plurality of filling ports spaced from one another in direct fluid communication with said storage tank and a vent to aid inflow and discharge of water f
1. A firefighting aircraft adapted for use in an unmanned aircraft system, the aircraft comprising: a storage tank for firefighting fluid having a plurality of filling ports spaced from one another in direct fluid communication with said storage tank and a vent to aid inflow and discharge of water from the storage tank;a probe carrying a conduit in fluid communication with the storage tank, the conduit being operative to receive water from a body of water overflown by the aircraft while the aircraft is in-flight and moving forward,a filling system for controlling the flow of water to and from the storage tank directly, the filing system comprising a plurality of valves, each of the plurality of valves associated with each filling port and remotely and automatically operable; anda control system in communication with each valve, and operative to command the position of each valve to regulate the flow of fluid through each filling port, each of the plurality of valves having an equal flow rate during the inflow of water to maintain stability of the aircraft and the plurality of valves having a balanced flow rate during the discharge of water to maintain stability of the aircraft,wherein the probe is directly attached to the aircraft and extends from a bottom of the aircraft. 2. The firefighting aircraft according to claim 1, further comprising a flow meter associated with each valve operative to measure fluid flow through each valve, wherein each flow meter is in communication with the control system, and provides flow data to the control system, the control system using the flow data from the flow meters to operate the valves and regulate the flow of fluid through each filling port. 3. The firefighting aircraft according to claim 1, wherein the filling ports are spaced from one another along at least one of a longitudinal or lateral axis of the aircraft. 4. The firefighting aircraft according to claim 1, wherein the filling ports are arranged in an array, the array being substantially centered on the center of gravity of the aircraft. 5. The firefighting aircraft according to claim 1, wherein the valves are controllable to regulate a rate of fluid flow there through. 6. The firefighting aircraft according to claim 1, further comprising a discharge gate for discharging fluid carried in the storage tank from the aircraft; and a manifold in fluid communication with the probe-carried conduit, with each filling port, and with the discharge gate,wherein the control system is further operative to command the position of each valve to regulate the flow of fluid from each filling port to the discharge gate. 7. The firefighting aircraft according to claim 1, 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. 8. The firefighting aircraft according to claim 7, further comprising a recess for receiving the probe in the second position. 9. The firefighting aircraft according to claim 8, further comprising a door that covers the probe and the recess when the probe is in the second position. 10. The firefighting aircraft according to claim 7, further comprising an actuator operative to move the probe between the first and second positions. 11. The firefighting aircraft according to claim 1, further comprising 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.
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이 특허에 인용된 특허 (3)
Ramage, Lee; MacDonald, Alan B.; Parker, Rory D., Fluid loading system.
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