162 results about "Trajectory of a projectile" patented technology

A ballistic trajectory method for a golf ball is disclosed wherein a ballistic trajectory of a golf ball having a plurality of dimples formed on the surface thereof when the golf ball is hit to fly at an arbitrary number of rotations and an arbitrary initial speed can be estimated and ballistic trajectory and flight characteristics of the golf ball can be evaluated without depending upon experimental evaluation which is based on an actual model thereby to allow a golf ball to be developed efficiently. The ballistic trajectory of the golf ball when the golf ball is hit to fly is estimated by successively calculating the flight distance and the height of the ball after every lapse of a very short period of time after the ball is hit to fly until it drops to the ground making use of arithmetic operation by a computer.

A gun sight base which is designed to allow the user to quickly adjust the elevation of the attached gun sight as a means to affect the trajectory of a projectile discharged from the host firearm. Provided is a removable, pre-calibrated adjustment cam which is in operational contact with the attached gun sight. A distance indicator is visible to the user to allow for rapid elevation adjustments without the need for tools.

Systems and methods usable to facilitate adjustments to a sighting device, such as a scope. In one example, an adjustment calculator associated with the scope receives data relating to a distance to a target and relating to at least one environmental variable, such as for example, wind and / or humidity, which may affect the trajectory of a projectile. The adjustment calculator processes the data and calculates a recommended scope adjustment. For instance, the adjustment calculator may output a number of adjustment “clicks” for a rifle scope in order to at least partially compensate for the distance and / or the environmental variable(s). In another example, the adjustment calculator receives data relating to properties of ammunition that may affect the trajectory of the ammunition.

A target in a physical environment can be interrogated. Feedback can be received from the target that is encoded within a radio frequency signal. The feedback can include position and movement data of the target. Adjustments can be calculated for a simulated kinetic projectile traveling to the target. The adjustments can account for target movement, kinetic projectile travel time, and travel path to the target. A distance from a point of origin of the simulated kinetic projectile to the target and movement of the target relative to the point of origin can be determined utilizing the feedback. A result signal can be conveyed that includes result data. The result data can include all information necessary for the target to react to the simulated kinetic projectile.

A passive electro-optical tracker uses a two-band IR intensity ratio to discriminate high-speed projectiles and obtain a speed estimate from their temperature, as well as determining the trajectory back to the source of fire. In an omnidirectional system a hemispheric imager with an MWIR spectrum splitter forms two CCD images of the environment. Three methods are given to determine the azimuth and range of a projectile, one for clear atmospheric conditions and two for nonhomogeneous atmospheric conditions. The first approach uses the relative intensity of the image of the projectile on the pixels of a CCD camera to determine the azimuthal angle of trajectory with respect to the ground, and its range. The second calculates this angle using a different algorithm. The third uses a least squares optimization over multiple frames based on a triangle representation of the smeared image to yield a real-time trajectory estimate.

A practice ammunition projectile comprises a head which bursts when the projectile strikes a target and contains a marking agent which optically indicates the point of impact after the head has burst. The marking agent consists of several chemical components (7, 8) which are each contained in separately breakable compartments (4, 5) within a burstable hood at the head of the projectile. When the compartments (4, 5) break open the compartments combine and undergo a chemical reaction which creates an optical mark. The hood is formed of an optically transparent material to enable the trajectory of the projectile to be tracked.An ammunition cartridge comprising a hollow projectile and a cartridge case with a propellant charge, the projectile comprising a projectile head designed to withstand the forces applied when the projectile is fired from a gun and designed to burst when the projectile strikes a target. A marking agent is disposed in the head for optically marking the impact with the target after the head has burst. The marking agent includes a plurality of chemical components each received in a separate frangible compartment in the head. These components are mixed and react chemically with each other when the compartments break up, causing the mixed components to luminesce. The compartments are designed to be broken up by the initial acceleration and / or the centrifugal forces on the projectile when the projectile is fired from a gun, while retaining the chemical components in the head. The components are therefore mixed at the time the projectile is fired from a gun and luminesce by the time the projectile strikes the target.

A method and system for guiding and controlling an ordinance body having a trajectory and a bore sight angle including making corrections to the trajectory based on bore sight angle vs. time history. The system is incorporated with existing fuse components in a replacement kit for existing munitions. The method determines nominal time values of the ballistic trajectory of the munition in relation to launch time and determines deviation from the nominal time values by an algorithm by analyzing signals received from a source of radiation located at the target. A processor determines lateral (left / right) and range errors and provides steering commands to a plurality of flight control surfaces mounted on the munition.

The invention discloses an attack angle and attack time control method based on trajectory planning. Firstly, a planned missile flying trajectory is assumed to be composed of an arc section SA and a line section AT, the arc section SA has a radius of R, and the line section AT passes across a target point T(xT, yT) and the requirement that the tail attack angle of the missile is thetaf is met; the arc section SA starts at the initial position S (x0, y0) of the missile and is tangent to the line section AT at a to-be-determined point A(xa, ya), and the point A(xa, ya) is obtained by specified missile attack time tf through an iterative algorithm. On the basis of trajectory planning, the invention provides a trajectory tracking control algorithm based on a virtual target; a feedforward and feedback composite control scheme is put forward in the arc section, and a sight line angle PD control scheme is put forward in the line section; and the method has a small calculation amount, and engineering implementation is facilitated.

The invention discloses a guidance method for attack time control. The guidance method comprises the following steps of establishing mathematical models of a missile and a target by considering the three-dimensional space of motion of the missile and the target; obtaining a dynamic equation of the trajectory inclination angle and the trajectory deflection angle of the missile, and obtaining a dynamic equation of the distance between the missile and the target, the angle of sight of the missile and the deflection angle of sight of the missile; on the basis, establishing a dynamic equation of the attack time error of the missile; then, separately designing the guidance law of the missile according to a pitching channel and a yaw channel, wherein the guidance law of the pitching channel is designed as an augmented proportion guidance law, the guidance law of the yaw channel is designed as a guidance law with an attack time error feedback item, and the trajectory track is adjusted to realize time control over attack on the target; and when the yaw angle is zero, adjusting the guidance law of the yaw channel to avoid singularity conditions. According to the guidance method, the attack time error is estimated, the attack time error tends to be zero through a guidance strategy, and the distance between the missile and the target tends to be zero. The guidance method for attack time control has the characteristics of clear structure and high applicability.

The invention provides a method for controlling coordinated operation of multiple missiles, which can accurately control the position, attack time, attack angle and attack velocity of each of the multiple missiles. The method comprises the following steps: selecting one missile from the multiple missiles to serve as a driving missile, and defining the rest missiles as driven missiles; assigning a virtual lead point to the driving missile as well as each of the driven missiles, and designing the path of motion of each lead point; determining the law of motion of the lead points in an arc coordinate system; establishing a model of relative motion of missiles and the lead points; designing the relative distances xr, yr and zr between the missles and the virtual lead points according to the needs of the missiles for cooperation in terms of position, attack angle and attack velocity; and designing a tracking controller based on the relative kinetics theory and allowing the missiles to fly in a way of tracking the virtual lead points with the designed relative distances, so as to perform coordinated operation. The method has the advantages of convenience in application and flexibility in use and has broad application prospects in the military field.

The invention relates to a laser screen target tachymeter and a ballistic trajectory capturing method, wherein the laser screen target tachymeter and the ballistic trajectory capturing method are applied to velocity measurement of a bullet. The laser screen target tachymeter is characterized by comprising a microprocessor unit, a display touch screen unit for display and operation, an X-axis laser screen transmitting unit, a laser receiving unit of an X-axis receiving laser screen, a Y-axis laser screen transmitting unit, a laser receiving unit of a Y-axis receiving laser screen and a signal processing circuit unit. The ballistic trajectory movement locus of the bullet can be traced out in the space through multiple points while velocity is measured, and compared with a ballistic trajectory measuring method in the prior art, the ballistic trajectory capturing method is low in cost, simple in principle, high in efficiency, free of influences of visibility of external environment and visual in measuring result.

The invention discloses an intelligent full-automatic gun correcting system and method. The system comprises a fixing rack used for fixing a gun body, a laser bullet simulating the normal bullet ballistic trajectory, a sighting device laser transmitting device simulating the sighting trajectory, a bar sight adjusting mechanism used for controlling the left-right movement of a bar sight in the horizontal direction, a sight head adjusting mechanism used for controlling the up-down movement of a sight head in the vertical direction, a laser target used for receiving the fall points of laser beams, and a control circuit used for receiving coordinate information of the fall points and controlling the bar sight adjusting mechanism and the sight head adjusting mechanism to achieve fall point coinciding. The method comprises the following steps that a gun is placed; coordinates of the fall points are calculated; the bar sight and the sight head are adjusted; and gun correcting is finished. The laser technology, the digital image processing technology, the automatic adjusting technology and other means are utilized, full-automatic correction of the gun shooting precision is achieved, and bullet launching and manual intervention are not needed; and the correcting precision and the correcting efficiency are improved, consumption of a large number of bullets in the gun correcting process is reduced, safe gun correction is achieved, and very high practicability and economic benefits are achieved.

An improved display provides information regarding a projectile trajectory so that a user is informed whether or not there is a clear shot. The improved display provides trajectory path indicator shown over cross hairs. In some embodiments, an intermediate point in the projectile trajectory is an aiming point and is indicated in relation to the visualized target. A rangefinder device is calibrated to a weapon having a sight, such as a bow sight. The aiming point is displayed showing the intermediate point in the projectile trajectory that corresponds with a pin in the bow sight. The rangefinder device may be calibrated using a calibration sheet. The display may include a level. The trajectory path indicator shows the aiming point, which is the highest point in the projectile trajectory as perceived by the user.

Current targeting approaches involve guiding to a spatially derived guidepoint of a group of objects likely to be the preferred object. This method may not allow the intercepting missile to contain the preferred, or other probable object(s), within its divert capability. The guidepoint is shifted closer to the preferred object using specific energy and angular momentum, constants of orbital motion, which describe properties of an object's trajectory. Guiding to the specific energy derived guidepoint does not offer significant benefit over guiding to the spatially derived guidance point. However, computing the spatial rate of change of specific energy within the plane formed by the guidance objects establishes a vector pointing close to the preferred object. This is the direction to shift the guidepoint in order to contain the preferred object within the interceptor's divert capability.

A method for the dispersion of projectiles from guns capable of firing multiple projectiles in rapid succession whereby some of the projectiles are modified by moving the center of mass of the projectile away from it's central axis and oriented prior to firing. This, in combination with bring fired from a rifled gun barrel, imparts velocity to the projectile upon exiting the gun barrel at right angles to the barrel. This velocity along with the higher muzzle velocity will cause the modified projectile to diverge away from the trajectory of a standard projectile. The magnitude of the divergence will vary with the distance the projectile's center of mass is away from its central axis, and the placement of the modified projectile strikes around the bull's-eye will be determined by the loading orientation of the modified projectile. Firing a multiplicity of standard and modified projectiles in rapid succession will produce an accurate dispersion pattern on a target, increasing the hit probability on that target.

A range-finding and ballistics effect compensating scope 804 with a ballistic effect compensating reticle aim point field 650 and ammunition adaptive aim compensation method for rifle sights or projectile weapon aiming systems includes (a) a primary aiming point 658 adapted to be sighted-in at a first selected range and (b) the locus of the RF beam for sensing range 29 to a selected target 28. The when firing, the reticle's aim point field also includes a sloped array of wind dots (e.g., 660) illustrating aim points for a range of crosswind conditions. The method for compensating for a projectile's ballistic behavior permits the shooter to sense or measure the LOS range to target 29 and sense or input the slope angle 27 and local or nominal air density ballistic characteristics (e.g., air density), and then display corrected hold points.

A gas check member for use in muzzle-loading firearms is provided. The invented gas check is designed to conveniently, frictionally attach rearward of a sub-caliber bullet to maximize the efficiency of such firearms. The diameter of the gas check preferably exceeds that of the bore slightly to prevent scoring and deformation of the bullet during loading, to hold the projectile in place within the barrel and to prevent moisture from contacting the powder when in place. Upon firing, the gas check minimizes the escape of propellant gases around the projectile and imparts a large, uniformly distributed forward thrust to the bullet to maximize the ballistic qualities of the shot. The design incorporates an unstable connection between inner and outer members that, upon firing, fractures to facilitate quick and reliable detachment of the outer member from the bullet. Detachment occurs to prevent interference with the trajectory of the bullet upon exit from the barrel.

The invention relates to a process to control the initiation of an attack module (2), such as a projectile or sub-projectile, such attack module having at least one pre-determined direction of action (WH), such process wherein it has the following steps: before firing or on trajectory, the coordinates of at least one target (3) are programmed into a fixed terrestrial reference (4), the orientation of the direction(s) of action (WH) in the fixed terrestrial reference (4) is determined at least once on trajectory and the initiation of the attack module (2) is only authorized if the direction of action (WH) is oriented in the direction of the target (3).The invention also relates to the device implementing such a process.

In an aiming or sighting device and an aiming method for determining the impact point of a ballistic flying body such as a rocket or a tube weapon projectile, specific characteristic values of the ballistic flying body are stored in a memory and an evaluating stage produces control signals in response to the specific characteristic values and in response to actual supplied system parameters. The control signals are transmitted to a display and to an adjustment drive. A model of the trajectory of the ballistic flying body is produced on the basis of all respective possible actual system parameters in an evaluating stage, whereby the trajectory is subdivided into at least two phases, each with a respective submodel. The submodel of the first phase is thereby a model with three or six degrees of freedom and the submodel of the second phase is a model with three degrees of freedom. An input unit permits adjusting the mode of operation and the correction of the impact location.

A system and method for providing information regarding the trajectory of a projectile is disclosed. The system comprises two subsystems: a non-magnetic sleeve designed to fit over the barrel of a gun, with a series of rings of magnetic material disposed thereupon, and an onboard measurement and control system comprising at least one magnetic sensor and control electronics, located within a projectile. As the projectile passes through the sleeve, the magnetic sensors within the projectile produce signals as the projectile passes through the magnetic rings. From the time profile of the signals thus produced, the projectile's linear and angular muzzle velocities are determined.

A firing device is provided for launching and retrieving projectiles as well as firing laser weapons from a robotic platform. In robotic games or competitions the projectiles and laser weapons are fired at targets to score points. In a game of laser tag the laser and / or infrared weapons are fired at targets on competing robots to score points and / or to disable the targeted robot. The firing device has one, two, or three rotating launch wheels for launching spherical projectiles illustratively including ping pong balls, where the revolution speed of launch wheels may be varied to control projectile velocity and distance of travel. A deflector plate is used to change the trajectory of the projectile and / or the laser beam.

The invention discloses an air-to-ground guided weapon lateral attack method and device, wherein the method comprises the following steps of acquiring an attack target position, a preset lateral constraint angle psi c and a real-time flight state of an aircraft, wherein the flight state comprises a position, a speed and a wind field condition of the aircraft; according to the flight state and thepsi c, determining a virtual target position in a manner of trajectory simulation iterative calculation; then furthermore, determining a flight trajectory of the guided weapon according to the virtualtarget position, the attack target position and the flight state; and according to the flight trajectory, after the guided weapon flies to the virtual target position after being launched, starting aturning program, and then performing lateral attack on an attack target according to the psi c. the air-to-ground guided weapon lateral attack method and device solves the technical problem that thelateral attack capability of the weapon cannot be well achieved due to limitation of a projectile body in the prior art.

A system and method for determining the wind force along the planned trajectory of a projectile are disclosed herein. A drone is flown along the expected path of the trajectory along a set heading. The drone is programmed to maintain the heading. As wind forces act upon the drone during its flight, the drone's electronic stability system provides automatic power and directional control to one or more motors that control the rotors and propellers that keep the drone aloft. By monitoring the changes in motor or drone state information over time in response to wind forces, the wind can be determined at various locations along the flight path. This information can be provided to a ballistics calculator to determine the launch heading of the projectile.

The invention relates to an automatic correction method and system for a sighting point of a sniper rifle. The method comprises the steps of obtaining a ballistic trajectory equation by analyzing thestress condition of a bullet in air, calculating the initial offset of the bullet through the ballistic trajectory equation, reversely solving an initial adjustment firing angle of the rifle by takingthe initial offset as an input parameter, further calculating impact point coordinates of the initial adjustment shooting angle under the shooting distance, comparing the impact point coordinates with a target position to obtain an initial offset, if the initial offset is not within a set deviation value range, adjusting the shooting angle through a least square method until a correction offset corresponding to the adjusted shooting angle is within the set deviation value range, determining a final shooting angle, and directly projecting the corrected aiming point on a sighting telescope, sothat the accurate calibration of the aiming point can be quickly realized by utilizing the method and the system, the correction speed is far higher than the manual correction speed, the method and the system can adapt to various complex environments, and a direction is provided for the research of new-generation sniper rifle aiming equipment.

The invention discloses a ballistic missile three-dimensional trajectory estimation method based on an infrared early warning image, and the method comprises the steps: carrying out the point target detection of a pre-obtained missile infrared remote sensing image in a continuous time sequence, and extracting the pixel coordinates of the mass center of a target of each image point; according to the extracted time and space information of the target point, tracking the target and obtaining a motion trail; conducting ballistic missile trajectory screening on ballistic missile motion characteristic analysis; unifying the attitude data and the orbit data of the missile target in a coordinate system; predicting a target three-dimensional trajectory through a collinear equation and a constraintcondition in a z direction according to the image plane two-dimensional trajectory; and correcting the error track according to the kinematic model of the missile and the constraint condition of the active section of the missile. According to the method, three dimensions are estimated from two dimensions, and a new scheme is provided for tracking and early warning of missiles.