Abstract: The disclosure relates to an unmanned aerial vehicle, wherein the fuel cell provides a structural component of the vehicle.

Abstract: The invention is a single piece molded toy that is shaped like an animal wherein the center of the toy is in the shape of and accordion and a squeaker in the head portion makes sound when the toy is squeezed, and as the toy returns to its original state a grunter located in the rear of the toy makes a grunting sound similar to that of a pig.

Abstract: A launch includes a frame including a platform defining a slot designed to slideably receive a rudder of a fixed-wing unmanned aerial vehicle. The launch includes two drive wheels rotatably supported by the frame and defining a space between each other. The space is open to the slot and designed to receive the rudder. The launch includes at least one variable speed drive wheel motor supported by the frame and operatively engaged with the drive wheels.

Abstract: Aircraft configuration by applying the following method steps for improving the conventional box wing aircraft concept: dividing both the backward swept front and the forward swept rear wings into root and tip sections, wherein the tip sections (34) of the front wings are more backward swept than the root sections (37), and the tip sections (35) of the rear wings are more forward swept than the root sections (38). Preferred embodiments comprise moving the front wing to the nose and the rear wing towards the rear end of a long fuselage; adding a middle wing and thereby decreasing the wingspan by one third; dividing the middle wing into a backward swept root section (28) and two tip sections (29,30), one forward and another backward swept. The four wingtips on each side are interconnected by a wingtip fence (26), obtaining seven closed frame structures, as well as seven aerodynamic channels for the stream flow.

Abstract: Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap, an actuator, a first hydraulic module, and a second hydraulic module. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The first hydraulic module is located at the actuator. The second hydraulic module is located remotely from the first hydraulic module and includes a local power unit. The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module.

Abstract: A fluid-cooled LED-based lighting fixture for Controlled Environment Agriculture (CEA) to improve energy efficiency, recycle waste heat, and support the operation of environmental sensors in a controlled agricultural environment. In one example, a lighting fixture frame mechanically supports and houses respective components of the lighting fixture and includes a light spine to mechanically couple the lighting fixture to a support structure. One or more coolant pipes formed from copper and coupled to the lighting fixture frame conduct a fluid coolant through the lighting fixture to remove heat. The lighting fixture comprises one or more LED modules to emit light, and a multiple electrical power and communication ports to facilitate interconnection of the lighting fixture in a variety of controlled agricultural environments.

Abstract: A pet grooming tool includes a handle, a comb member, a push button, a gear rack, and a removal assembly. The removal assembly is rotatably connected to the handle and is movable between an original position and a removal position. The comb member has multiple claws, each has a distal end. A first slit is defined between every two adjacent claws. The removal assembly has a pinion section and multiple removing sections. The pinion section engages with the gear rack. The removing sections are corresponding to the first slits, respectively. when the removal assembly revolves from the original position to the removal position, the multiple removing sections pass through the first slits towards the distal ends of the multiple claws, so as to remove any hair from the claws.

Abstract: A drone with a horizontal rotor includes one or more rotor(s) (115, 116) which rotate in a horizontal plane, each rotor (115, 116) being equipped with one or more rigid or non-rigid blades (120, 121), the blade end being mounted on an electric motor (110, 111) with a propeller.

Abstract: A fluid-cooled LED-based lighting fixture for Controlled Environment Agriculture (CEA) to improve energy efficiency, recycle waste heat, and support the operation of environmental sensors in a controlled agricultural environment. In one example, a lighting fixture frame mechanically supports and houses respective components of the lighting fixture and includes a light spine to mechanically couple the lighting fixture to a support structure. One or more coolant pipes formed from copper and coupled to the lighting fixture frame conduct a fluid coolant through the lighting fixture to remove heat. The lighting fixture comprises one or more LED modules to emit light, and a multiple electrical power and communication ports to facilitate interconnection of the lighting fixture in a variety of controlled agricultural environments.

Abstract: A passenger seat arrangement is provided for a single-aisle vehicle, such as a narrow-body aircraft. In some examples, the passenger seat includes a passenger seat having a seat plane. The passenger seat is positioned such that the seat plane is at a non-square and non-zero acute angle relative to a plane of the aisle. The passenger seat is a non-lie flat seat movable between an upright position and a neutral position. A seat back of the passenger seat is at a non-zero angle relative to a seat base of the passenger seat in both the upright position and the neutral position.

Abstract: At least a selected one of a first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with the selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.

Abstract: An electric compound aircraft is disclosed with a capability of making vertical takeoff and landing and forward flight. In a specific embodiment, the compound aircraft includes an electric motor-powered tip-jet-driven rotary wing, an electric motor-powered tip-jet-driven propeller. The rotary wing provides lift for vertical takeoff and landing, hovering capability and during flight. The propeller provides thrust for forward flight. A fixed wing can be used, in addition to the rotary wing to provide lift for forward flight. Various electric control devices are used to provide control and stability for the compound aircraft and automation.

Abstract: Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes an engine reduction gearbox (“ERGB”) having a retractable driveshaft assembly with an actuation shaft and a first friction plate. Actuation of the retractable driveshaft assembly by the actuation shaft causes the first friction plate to selectively engage and disengage a second friction plate associated with a mid-wing gearbox (“MWGB”) via axially translatable motion of the retractable driveshaft assembly along its rotation axis. When the friction plates are engaged, rotation of the retractable driveshaft assembly imparts rotation to at least one rotor assembly. When the friction plates are disengaged, the wing assembly is capable of selectively rotation with respect to the fuselage about the stow axis between the flight position and the stowed position.

Abstract: A device for managing the mechanical energy of an aircraft, having an energy management auxiliary system, includes a support defining a guide, a centralized control lever for varying the energy of the aircraft, at least one position sensor detecting the position of the centralized control lever in the guide. The position sensor is configured to create position information for the position of the centralized control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an auxiliary support; for the or each motor of the aircraft, an individual control lever for the individual propulsion of the motor, mounted movably in the auxiliary support; and at least one auxiliary position sensor detecting the position of the or each individual lever configured to generate information intended to be sent to the flight control unit of the aircraft.

Abstract: A ground based control system and method for controlling nanosatellites in low earth orbit to fly as an array, comprises arranging the nanosatellites, each of which has an illumination element in the array, and operating selected illumination elements to produce a display in which a pattern, shape or letters or words are detectable at a predetermined ground location.

Abstract: A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Abstract: A deployment system for solar panels has the panels spring loaded to deploy, but held folded against a satellite framework by trigger bars engaging slots or notches in hinge bodies holding the solar panels. An actuator moves the trigger bars to disengage from the hinge bodies to release the panels to deploy.

Abstract: A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

Abstract: A satellite system may have a constellation of communications satellites that provides services to users with electronic devices such as portable electronic devices and home/office equipment. A network operations center may use gateways to communicate with the satellite constellation. The satellite constellation may include sets of satellites with different orbits such as circular orbits with different inclinations, sets of satellites with elliptic orbits, sets of satellites with circular orbits of different altitudes including low earth orbits, medium earth orbits, and/or geosynchronous orbits, sets of satellites with sun synchronous orbits, and/or sets of satellites with other orbits. The orbits of the satellites in the constellation may be selected to provide coverage to desired user population concentrations at different locations on the Earth, while reducing the amount of capacity that goes unused (e.g., is idle) at one or more times of day.

Abstract: One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.