公开(公告)号：US20020190156A1

公开(公告)日：2002-12-19

申请号：US09881790

申请日：2001-06-14

发明人： Warren S. Jensen

IPC分类号： F42B010/00 ,  F42B010/06

CPC分类号： F42B10/54

摘要： A projectile and a method of launching a projectile from a barrel. The projectile of the present invention may be matched to a pre-selected barrel rifling to produce a controlled spin rate. Controlled spin rate is characterized by substantially balanced forward and axial deceleration. Substantially balanced forward and axial deceleration is characterized by an axial speed that decreases in relationship to the decrease in forward speed. Substantially balanced forward and axial deceleration produces a trajectory that is characterized by a gyroscopic stability factor that remains highly stable over a given distance of a trajectory. Gyroscopic stability is controlled during the projectile's flight by controlling the spin damping moment as a design element. Control of the spin damping moment may be achieved by incorporating physical features in the projectile's design and manufacture and/or may result from the incorporation of physical features imparted upon the projectile during launch.

摘要翻译： 射弹和从枪管发射射弹的方法。 本发明的抛射体可以与预选的枪管枪匹配以产生受控的旋转速率。 受控旋转速度的特征在于基本平衡的前向和轴向减速。 基本平衡的前进和后退减速度的特征在于与向前速度的减小相关的轴向速度减小。 基本平衡的前向和轴向减速产生轨迹，其特征在于陀螺稳定性因子，其在给定距离的轨迹上保持高度稳定。 通过控制旋转阻尼力矩作为设计元素，在弹道飞行期间控制陀螺稳定性。 旋转阻尼力矩的控制可以通过将抛物体的设计和制造中的物理特征结合起来实现，和/或可以由在发射过程中施加于弹丸上的物理特征引起。

公开(公告)号：US20020109040A1

公开(公告)日：2002-08-15

申请号：US10067964

申请日：2002-02-08

发明人： Tom Kusic

IPC分类号： F42B010/06 ,  F42B010/00

CPC分类号： B64C9/06 ,  B64C5/04

摘要： A cross-section of a missile 1 with the missile attachment 2. The missile attachment consists of a cylindrical tube 3 which encircles part of the missile 1, and a protruding section 4 with a concave forward facing surface area 5. Shown also is a friction inducing moveable component in the form of a lever 11 pivotly attached to the missile by a bracket 12, such that the lever 11 can be pivotly moved an actuating mechanism which is in the form of an electric motor 13 using a rotor arm 14. When the lever is pivoted by the electric motor 13, using the rotor arm 14, a part of the lever is pressed through a hole 15 in the missile 1 so that the part of the lever that is pressed through the hole can reach the cylindrical tube. As the rotor arm 14 presses harder against the lever, the lever is pressed harder against the cylindrical tube. With the friction that occurs between the lever and the cylindrical tube, the rotation of the cylindrical tube relative to the missile can be controlled, so that the spiralling motion of the missile can be controlled. A computer 16 controls the action of the electric motor 13, and a battery 17 provides electrical power for the computer and the electrical motor.

摘要翻译： 具有导弹附件2的导弹1的横截面。导弹附件包括环绕导弹1的一部分的圆柱形管3和具有凹入的前向表面区域5的突出部分4.还示出了摩擦 引导杠杆11的形式的可移动部件，其通过支架12枢转地附接到导弹，使得杠杆11可以使用转子臂14以电动马达13形式的致动机构枢转运动。当 杠杆由电动马达13枢转，使用转子臂14，杆的一部分通过导弹1中的孔15被按压，使得通过孔按压的杆的部分可以到达圆柱形管。 当转子臂14更加压靠杠杆时，杆被更加压紧在圆柱形管上。 由于杠杆和圆柱形管之间发生摩擦，可以控制圆柱形管相对于导弹的旋转，从而可以控制导弹的螺旋运动。 计算机16控制电动机13的作用，并且电池17为计算机和电动机提供电力。