149 results about "Trajectory of a projectile" patented technology

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 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.

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 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.

The invention discloses a high-altitude parabolic detection method based on spatio-temporal information, and the method comprises the steps: obtaining a to-be-recognized image pair sequence which is auniform sampling image sequence in the same video scene in continuous time; inputting the to-be-recognized image pair sequence into a pre-trained deep neural network model for forward operation, andobtaining a falling track probability graph of the high-altitude projectile body; if the falling track probability graph has a vertical communication area with a certain length, determining that a high-altitude parabolic behavior exists in the time period. The falling track of the high-altitude projectile body can be accurately positioned, and then whether the high-altitude projectile behavior exists or not is judged.

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 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.

The invention discloses a near-space hypersonic target trajectory prediction method. The method belongs to the field of near-space hypersonic target trajectory prediction. In order to solve the problems that in the prior art, trajectory prediction is achieved through methods such as guidance law online identification, fitting extrapolation or template matching, in the defense process of an approaching hypersonic speed target, a dynamic model of the target is unknown, and the hypersonic speed target guidance law is complex and changeable, and online estimation is difficult and an error is large, the obtained historical ballistic data is decomposed into the ballistic trend signal and the ballistic cycle jump signal; modeling is carried out on the trend signals respectively; modeling is carried out on the periodic jump signal; and finally, superposing the trend signal model established in the step 2 and the periodic jump signal model established in the step 3 to obtain a trajectory complete parameterized model, and realizing trajectory prediction based on complete model extrapolation. The method is mainly suitable for the aspects of hypersonic target transverse maneuvering trajectoryprediction, target speed prediction and the like.