Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

A projectile and stabilizer therefor are provided. The sliding stabilizer is used instead of fixed or glued tail feathers, vanes or other fletching as a means for stabilizing projectile flight. The invention improves current projectile technology with reduced assembly labor cost, the elimination of bow clearance issues, improved accuracy with the consistent production of the sliding stabilizer, easy replacement of the stabilizer in the field, and improved projectile storage. A sliding stabilizer is designed to slide along the shaft of a projectile and comprises a circumferentially extending wing and a plurality of fins. In use, the stabilizer is positioned at the front of the projectile prior to launch, and the projectile slides quickly through the stabilizer until secured at a stop position at or near the trailing end of the projectile. An annular arrow fletch and arrow stabilizer are also provided. The annular arrow fletch may be used for; stabilizing arrow flight, providing better clearance and functionality then conventional fixed glued tail feathers. A stabilizer may be used with light emitting diode arrow nocks. The stabilizer may improve arrow shaft stabilization technology with reduced assembly labor cost, the elimination of facial and or face mask interference issues providing more clearance, improved accuracy, repeatable production with the consistent injection mold production of the annular arrow fletch, easy replacement of the annular arrow fletch in the field, and improved arrow storage. An annular arrow fletch may incorporate a metallic contact point, which will work with all light emitting nocks. A design of an annular arrow fletch may be affixed to an arrow by an arrow nock and may comprise an annular wing, a central elongated cylindrical cylinder with a cap and a plurality of fins with micro-groves and a metal contact. In use, the annular arrow fletch is affixed at the aft end of the arrow by an arrow nock prior to launch.

A dart with a telescopic tail wing composes a dart rod, a dart head disposed at a front end of the dart rod and a tail wing disposed at a rear end of the dart rod. A tail wing connecting part is disposed at the rear end of the dart rod. The tail wing comprises a sleeve and multiple wing blades disposed on the sleeve. A clamping part is disposed on the tail wing connecting part. A limiting part is disposed in the sleeve. The tail wing connecting part is inserted into the sleeve. The clamping part stretches from one side to the other side of the limiting part and is matched with the limiting part. An elastic piece is disposed around the tail wing connecting part. The tail wing can rotate on the tail connecting part and can telescopic. In case of a collision, the tail wing can rotate to reduce force, so that compared with the prior art, dart is simple in structure, easy to assemble and low in production cost.

A dart with a telescopic tail wing composes a dart rod, a dart head disposed at a front end of the dart rod and a tail wing disposed at a rear end of the dart rod. A tail wing connecting part is disposed at the rear end of the dart rod. The tail wing comprises a sleeve and multiple wing blades disposed on the sleeve. A clamping part is disposed on the tail wing connecting part. A limiting part is disposed in the sleeve. The tail wing connecting part is inserted into the sleeve. The clamping part stretches from one side to the other side of the limiting part and is matched with the limiting part. An elastic piece is disposed around the tail wing connecting part. The tail wing can rotate on the tail connecting part and can telescopic. In case of a collision, the tail wing can rotate to reduce force, so that compared with the prior art, dart is simple in structure, easy to assemble and low in production cost.

Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

A projectile and stabilizer therefor are provided. The sliding stabilizer is used instead of fixed or glued tail feathers, vanes or other fletching as a means for stabilizing projectile flight. The invention improves current projectile technology with reduced assembly labor cost, the elimination of bow clearance issues, improved accuracy with the consistent production of the sliding stabilizer, easy replacement of the stabilizer in the field, and improved projectile storage. A sliding stabilizer is designed to slide along the shaft of a projectile and comprises a circumferentially extending wing and a plurality of fins. In use, the stabilizer is positioned at the front of the projectile prior to launch, and the projectile slides quickly through the stabilizer until secured at a stop position at or near the trailing end of the projectile. An annular arrow fletch and arrow stabilizer are also provided. The annular arrow fletch may be used for; stabilizing arrow flight, providing better clearance and functionality then conventional fixed glued tail feathers. A stabilizer may be used with light emitting diode arrow nocks. The stabilizer may improve arrow shaft stabilization technology with reduced assembly labor cost, the elimination of facial and or face mask interference issues providing more clearance, improved accuracy, repeatable production with the consistent injection mold production of the annular arrow fletch, easy replacement of the annular arrow fletch in the field, and improved arrow storage. An annular arrow fletch may incorporate a metallic contact point, which will work with all light emitting nocks. A design of an annular arrow fletch may be affixed to an arrow by an arrow nock and may comprise an annular wing, a central elongated cylindrical cylinder with a cap and a plurality of fins with micro-groves and a metal contact. In use, the annular arrow fletch is affixed at the aft end of the arrow by an arrow nock prior to launch.

An aircraft, missile, projectile, or underwater vehicle with an improved control system, an improved control system, or a method of maneuvering an aircraft, missile, projectile, or underwater vehicle uses control surfaces that are movable along a track. The control system on a track (or tracked control surface) advantageously enables the aircraft, missile, projectile, or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight by adjusting the center of pressure of the aircraft, missile, projectile, or underwater vehicle relative to its center of gravity.

An aircraft, missile, projectile, or underwater vehicle with an improved control system, an improved control system, or a method of maneuvering an aircraft, missile, projectile, or underwater vehicle uses control surfaces that are movable along a track. The control system on a track (or tracked control surface) advantageously enables the aircraft, missile, projectile, or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight by adjusting the center of pressure of the aircraft, missile, projectile, or underwater vehicle relative to its center of gravity.