子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Aircraft, missile, projectile, or underwater vehicle with reconfigurable control surfaces | US12977519 | 2010-12-23 | US08367992B1 | 2013-02-05 | Mehul Patel; T Terry Ng; Alan B Cain; Zak Sowle; Jack DiCocco |
| The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight. | ||||||
| 142 | TIPPED PROJECTILES | US12199306 | 2008-08-27 | US20120216700A1 | 2012-08-30 | Gregory A. Dennison |
| A projectile is provided with a projectile tip having enhanced aerodynamic properties to improve accuracy of the projectile. The tip has a body having a base or lower end, an upper end and a curved, side wall between its upper and lower ends that defines an ogive tip length. The tip is received with a projectile jacket and also can have a series of aerodynamic features formed in its body to modify air flow about the body of the projectile in flight. | ||||||
| 143 | MULTI-CALIBER FUZE KIT AND METHODS FOR SAME | US12469443 | 2009-05-20 | US20120211592A1 | 2012-08-23 | Chris E. Geswender; Cesar Sanchez; Matthew A. Zamora |
| A multi-caliber fuze kit includes a fuze housing configured for coupling with multiple projectiles. One or more canards are moveably coupled with the fuze housing. The one or more canards are adjustable between two or more canard configurations. In a first canard configuration, the one or more canards are at a first canard angle relative to a bore sight of the fuze housing, and the first canard angle is configured for use with a first projectile. In a second canard configuration, the one or more canards are at a second canard angle relative to the bore sight of the fuze housing, and the second canard angle is configured for use with a second projectile. The first and second canard angles are different. In another example, in the first canard configuration the one or more canards include a first canard shape configured to provide a first specified trajectory with the first projectile. In the second canard configuration the one or more canards include a second canard shape configured to provide a second specified trajectory with the second projectile. The first canard shape and the second canard shape are different. | ||||||
| 144 | Ordnance | US13040377 | 2011-03-04 | US20120180625A1 | 2012-07-19 | Mohamed Mounir Gazayerli |
| A boomerang-shaped projectile, ammunition cartridge including the projectile, and a weapon barrel through which the projectile is fired. | ||||||
| 145 | Folding control surface assembly and vehicle incorporating same | US11474029 | 2006-06-23 | US07750275B2 | 2010-07-06 | Mark A. Turner |
| A folding control surface assembly includes a torsion shaft, a base, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base. A vehicle includes a body and at least one folding control surface assembly. The at least one folding control surface assembly includes a torsion shaft, a base attached to the body, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base. | ||||||
| 146 | Pellet for pneumatic and spring-piston operated weapons | US11483579 | 2006-07-10 | US07428871B2 | 2008-09-30 | L. Carl Dodson; David Phillips |
| A pellet for at least one of a compressed gas and spring operated weapon includes a forward head portion and a cylindrical rearward tail portion which is disposed about a common centerline with the head portion and which has an air pocket formed therein. A frustoconical middle portion connects the tail portion to the head portion. The pellet design is adaptable for use with various commonly available caliber weapons. | ||||||
| 147 | Telescoped projectile | US11204575 | 2005-08-16 | US20080000380A1 | 2008-01-03 | Richard Dryer |
| A projectile reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion and an aft portion, and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose, and a cylindrical central body attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow in a base of the aft portion. The base may be slidable relative to the central body. | ||||||
| 148 | Non-lethal ammunition projectile | US11652149 | 2007-01-11 | US20070227391A1 | 2007-10-04 | Carlos de Aguiar |
| The present invention relates to a projectile (1) for non-lethal ammunition of a body that is composed of a first portion (2) and a second portion (4). Said first portion (2) has a larger mass that the second portion (4), so as to increase the stability of the projectile (1). In addition, the projectile (1) has a strangulation (5) that connects the first portion (2) to the second portion, wherein the first portion (2) is formed by two rings (3), and the two rings (3) are interconnected by an annular groove (6), and wherein the end opposite the strangulation (50 of the second portion (4) has an annular base (7). | ||||||
| 149 | Penetrator and method of using same | US11411749 | 2006-04-26 | US07261040B2 | 2007-08-28 | David L. Hunn; Johnny E. Banks; Carlton B. Cowan |
| A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. | ||||||
| 150 | Penetrator and method of using same | US11411749 | 2006-04-26 | US20070039507A1 | 2007-02-22 | David Hunn; Johnny Banks; Carlton Cowan |
| A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. | ||||||
| 151 | Penetrator and method of using same | US10988125 | 2004-11-12 | US07107910B2 | 2006-09-19 | David L. Hunn; Johnny E. Banks; Carlton B. Cowan |
| A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. | ||||||
| 152 | Variable drag projectile stabilizer for limiting the flight range of a training projectile | US10709401 | 2004-05-03 | US06983700B1 | 2006-01-10 | Gregory Malejko; Anthony Vella; Eric P. Scheper; Philip M. Donadio |
| A variable drag projectile stabilizer is utilized by a training projectile to match the trajectory of a tactical projectile for up to 3 km while having a range limitation of 8 km. The stabilizer applies supersonic flow phenomena to alter the aerodynamic characteristics of a training projectile while in free flight to fulfill this requirement. The stabilizer uses a cowling supported by struts to provide tail lift and ensure a stable flight path. Supersonic flow is established through ducts formed by the cowling and struts when launched from a weapon. The flow remains supersonic until the projectile reaches the desired range but then quickly becomes subsonic (choked) due to shock waves emanating from interior angles in the ducts. The geometry of the ducts can be designed to create different shock wave patterns within the ducts. The variance of leading edge location, leading edge angle, cowling intake angle, and flight Mach number influences the shock patterns within the ducts and consequently, the range of the projectile. | ||||||
| 153 | Locking and stabilizing device for grenades | US10666824 | 2003-09-22 | US06968785B2 | 2005-11-29 | Lamar M. Auman; Douglas J. Love; Brad L. Bachelor |
| The locking and stabilizing device for grenades utilizes a solid nylon ring and multiple nylon ribbons that are attached to the ring at regular intervals around its circumference. During storage, the ring surrounds and locks the slider of the grenade in its storage position. But upon deployment, under aerodynamic forces the ring moves away from the slider, releasing the slider. When the slider is thusly released, it slides out and brings the detonator in place to be impacted upon by the pin when the grenade hits the target, thus detonating the grenade. The multiple ribbons extending from the ring unfurl due to the aerodynamic forces and provide stability to the grenade flight. | ||||||
| 154 | Projectile for rapid fire gun | US10270812 | 2002-10-15 | US06862996B2 | 2005-03-08 | Mark Key |
| An ammunition system for a rapid fire gun. The ammunition system includes a bullet having a tip that is stored in a retracted position and during flight is deployed create an aerodynamic shape. Another aspect of the ammunition system is that the bullet has a cylindrical body having a first length in storage and a second longer length after ignition of the propellant. | ||||||
| 155 | Penetrator and method for using same | US10251468 | 2002-09-20 | US20040055502A1 | 2004-03-25 | David L. Hunn; Johnny E. Banks; Carlton B. Cowan |
| A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. | ||||||
| 156 | Securing device for attaching a stabilizing band to air-dropped ammunition | US09388549 | 1999-09-02 | US06253681B1 | 2001-07-03 | Karlheinz Roosmann; Adolf Weber |
| An air-dropped ammunition includes an ammunition body having a rearward portion; a firing pin accommodated in the rearward portion; a stabilizing band being received in a folded state at least partially in the rearward portion of the ammunition body; and a device for securing the stabilizing band to the firing pin. The device includes a disk having an upturned rim. The disk engages face-to-face one of two overlapping ends of the stabilizing band, and the upturned rim is oriented away from the overlapping ends. The overlapping ends and the disk are firmly attached to the firing pin. | ||||||
| 157 | System and method for controlling a re-entry vehicle | US30627 | 1998-02-25 | US6076771A | 2000-06-20 | Richard A. Bailey; Aaron Cohen; Dale D. Myers |
| A re-entry vehicle includes a flare-stabilized cylindrical body with a center of gravity displaced from a centerline to define a windward side of the body upon re-entry. The body orients at an angle of attack between the centerline and a velocity vector to generate a lift vector. An actuator moves the lift vector relative to the velocity vector to control the descent of the re-entry vehicle. | ||||||
| 158 | Hunting bullet having a telescoping flechette and comprising a sub-projectile connected to a launcher | US663305 | 1996-06-25 | US5804759A | 1998-09-08 | Jean-Claude Sauvestre |
| An ammunition cartridge comprises a full bullet 1 held in a primer socket D containing a propellant charge P. The bullet 1 includes an flechette 2 and a launcher 10 concentrically received on the flechette to allow relative translation. The flechette 1 comprises an flechette body 3 of hard material having a conical head 4, and a stabilizer 6 fixed to a rear of the body 3. The stabilizer 6 has an integral lip 8 which seals the bullet 1 in the barrel to optimize pressure build-up during firing. The launcher translates forward relative to the flechette when released from the primer socket D. The full bullet remains intact in flight. The launcher strikes the target first and transmits high energy to the target. Immediately thereafter, the flechette translates forward to penetrate the target. | ||||||
| 159 | System for providing power and roll motion stability in a vehicle | US351821 | 1994-12-08 | US5660356A | 1997-08-26 | Brian J. Selfors; Vijay M. Gondhalekar |
| A dual flywheel assembly for use in an airborne vehicle for storing mechanical energy therein prior to flight and for permitting the extraction of electrical energy therefrom during flight, which assembly includes two flywheels which are linked by a suitable linkage structure such that, if roll motion of the vehicle starts to occur during flight, the flywheels tilt in equal and opposite directions out of their normal planes of rotation, which tilting motions act in a passive manner to stabilize the roll motion of the vehicle. | ||||||
| 160 | Resiliently deployable fairing for sealing an airframe cavity | US169223 | 1988-03-16 | US4838502A | 1989-06-13 | George T. Pinson |
| A cavity in an airframe from which an airfoil is deployed is automatically closed to reduce aerodynamic drag by a fairing element hinged to the force and aft cavity edges and resiliently deformable from an unbent aerodynamic position outside the cavity to a bent position within the cavity. The non-deployed airfoil overlies the bent fairing element and retains the fairing in a bent position against the resilient force tending to restore it to the unbent position, until airfoil deployment. | ||||||
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