Abstract: The present disclosure provides systems and techniques for an electromechanical sear that is implementable in a gun. The gun may include a fire control manager, and the fire control manager may identify a trigger break based on a trigger sensor, transmit, based on the trigger break, a first signal to a first actuator located in a displacement path of a sear, so as to cause the first actuator to be displaced in a first direction, and transmit, based on the trigger break, a second signal to a second actuator located in the displacement path of the sear, so as to cause the second actuator to be displaced in a second direction. The transmitting the first signal to the first actuator and the transmitting the second signal to the second actuator may cause displacement of the sear and firing of the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical trigger that is implementable in a gun. The gun may include a trigger mechanism, a trigger sensing mechanism, and a fire control manager. The fire control manager may identify a trigger break based on the trigger sensing mechanism generating a voltage, and the fire control manager may transmit a signal to an actuator mechanism based on the trigger break. A detent mechanism may be dislocated in response to a force applied to a trigger mechanism, and the trigger sensing mechanism may generate the voltage based on the dislocating of the detent mechanism. Dislocating the detent mechanism may correspond to satisfying a trigger break threshold. The actuator mechanism may be displaced in response to the signal, and displacing the actuator mechanism may result in a projectile being propelled from the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical trigger that is implementable in a gun. The gun may include a trigger mechanism, a trigger sensing mechanism, and a fire control manager. The fire control manager may identify a trigger break based on the trigger sensing mechanism generating a voltage, and the fire control manager may transmit a signal to an actuator mechanism based on the trigger break. A detent mechanism may be dislocated in response to a force applied to a trigger mechanism, and the trigger sensing mechanism may generate the voltage based on the dislocating of the detent mechanism. Dislocating the detent mechanism may correspond to satisfying a trigger break threshold. The actuator mechanism may be displaced in response to the signal, and displacing the actuator mechanism may result in a projectile being propelled from the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical sear that is implementable in a gun. The gun may include a fire control manager, and the fire control manager may identify a trigger break based on a trigger sensor, transmit, based on the trigger break, a first signal to a first actuator located in a displacement path of a sear, so as to cause the first actuator to be displaced in a first direction, and transmit, based on the trigger break, a second signal to a second actuator located in the displacement path of the sear, so as to cause the second actuator to be displaced in a second direction. The transmitting the first signal to the first actuator and the transmitting the second signal to the second actuator may cause displacement of the sear and firing of the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical trigger that is implementable in a gun. The gun may include a trigger mechanism, a trigger sensing mechanism, and a fire control manager. The fire control manager may identify a trigger break based on the trigger sensing mechanism generating a voltage, and the fire control manager may transmit a signal to an actuator mechanism based on the trigger break. A detent mechanism may be dislocated in response to a force applied to a trigger mechanism, and the trigger sensing mechanism may generate the voltage based on the dislocating of the detent mechanism. Dislocating the detent mechanism may correspond to satisfying a trigger break threshold. The actuator mechanism may be displaced in response to the signal, and displacing the actuator mechanism may result in a projectile being propelled from the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical sear that is implementable in a gun. The gun may include a fire control manager, and the fire control manager may identify a trigger break based on a trigger sensor, transmit, based on the trigger break, a first signal to a first actuator located in a displacement path of a sear, so as to cause the first actuator to be displaced in a first direction, and transmit, based on the trigger break, a second signal to a second actuator located in the displacement path of the sear, so as to cause the second actuator to be displaced in a second direction. The transmitting the first signal to the first actuator and the transmitting the second signal to the second actuator may cause displacement of the sear and firing of the gun.

Abstract: The present disclosure provides systems and techniques for an electromechanical sear that is implementable in a gun. The gun may include a fire control manager, and the fire control manager may identify a trigger break based on a trigger sensor, transmit, based on the trigger break, a first signal to a first actuator located in a displacement path of a sear, so as to cause the first actuator to be displaced in a first direction, and transmit, based on the trigger break, a second signal to a second actuator located in the displacement path of the sear, so as to cause the second actuator to be displaced in a second direction. The transmitting the first signal to the first actuator and the transmitting the second signal to the second actuator may cause displacement of the sear and firing of the gun.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: The invention relates to systems and methods for manufacturing composite parts for aircraft. In one innovative aspect, a system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of a wing of the aircraft is disclosed, wherein a modular spar tunnel mold is provided and configured to be detachably fixed at a plurality of selected locations within a main mold for a fuselage portion of the aircraft. In another innovative aspect, a movable detail or mold is used for manufacturing complex composite parts for an aircraft. In yet another innovative aspect, a movable detail is used to fabricate a common feature for a plurality of different parts for one or more aircraft or a family of aircraft of similar design.

Abstract: A system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of a wing of the aircraft. In one innovative aspect, a modular spar tunnel mold is provided and configured to be detachably fixed at a selected location within a main mold for a fuselage portion of the aircraft.

Abstract: A system and method for adjusting a location of a center of gravity of an aircraft relative to a center of lift of awing of the aircraft. In one innovative aspect, a modular spar tunnel mold is provided and configured to be detachably fixed at a selected location within a main for a fuselage portion of the aircraft.