A telescoping tail assembly for use on an aircraft having a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction, a tailboom slidable along the housing into various positions including an extended position and a retracted position and one or more control surfaces coupled to the tailboom. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

Systems and methods for a weapon mountable tactical heads-up display (HUD) are provided. The HUD may include a 9 degrees of freedom (9DOF) sensor, a target library, and a target finder visualization. The target library may store respective ballistic information for each target of a plurality of targets. The respective ballistic information may include a target vector for each target of the plurality of targets. The target vector may be calculated based on data received from the 9DOF sensor. The target finder visualization may allow a shooter to locate a selected target of the plurality of targets. The target finder visualization may be based on the target vector.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.