15 results about "External ballistics" patented technology

A cartridge is disclosed with a casing and a projectile, wherein external ballistic stability is provided by a center of pressure of the projectile being rearward of a center of mass of the projectile. The projectile includes flight control surfaces that cooperate with the bore of a barrel without requiring rifling or sabots. The projectile can include fin configurations that cooperate with the bore to form a bearing surface with the bore.

The invention relates to the technical field of cannonball outer trajectory measurement, in particular to an outer trajectory parameter measuring device and method based on an electric field sensor array. The system comprises a detection array composed of four electric field sensors. The method comprises the following steps: according to an electric field intensity change rate detected by an electric field sensor when a charged projectile flies nearby the electric field sensor, establishing each parameter relational expression by combining a Coulomb law; and carrying out indirect measurement on the position and the speed of the charged projectile according to the calibration and speed calibration equation. According to the invention, the electric field sensor is used for non-contact measurement of outer ballistic parameters based on the electrostatic detection technology, no interference is caused to the projectile, the cost is low, and the operation is simple; the device is high in adaptability, can be suitable for various different measurement environments, and is wide in application range.

The invention discloses a rocket projectile launching end point intensity influence factor analysis method, system and device and a medium. The method comprises the following steps: establishing a six-degree-of-freedom rigid in-vitro ballistic equation of the variable mass rocket projectile in a matrix form; the method comprises the following steps: generating a parameter sample based on a Monte Carlo random simulation principle by comprehensively considering three types of influence parameters of rocket projectile processing errors, initial disturbance and meteorological conditions, performing external trajectory equation numerical integration by combining a fourth-order Runge-Kutta method, and calculating a rocket projectile launching end point coordinate; three uncertainty sensitivity analysis methods are adopted, the influence degree of various parameters on the emission end point is quantified, results of the three methods are compared, and the influence degree of each factor is determined. According to the method, the influence degree of each factor on the rocket projectile launching terminal point is compared and analyzed by using multiple uncertainty sensitivity analysis methods, and the accuracy is relatively high.

This invention discloses a method for correcting firing parameters in a closed-loop firing correction system suitable for conditions with very few satellite measurement points. It adds a rotational speed measuring device to the projectile system to measure the real-time rotational speed of the artillery projectile. Based on external ballistics theory, this invention utilizes muzzle rotation speed, ballistic speed, and measurement data (coordinates and velocities) from a limited number of ballistic points to propose a method for estimating the range and lateral deviations of a single projectile relative to the target point. This allows for the rapid determination of the launch angle and directional corrections, enabling artillery firing correction. This invention solves the key problem of how to quickly and accurately determine the firing parameter corrections of a closed-loop firing correction system when there are very few ballistic measurement points, greatly improving the adaptability and reliability of the closed-loop firing correction system under complex battlefield conditions and effectively enhancing the combat capability of the weapon system.

The integrated ammunition design and use method and system constructed by the application comprises ammunition structure parameterized modeling, interior ballistic solution and launch strength checking, aerodynamic layout and bullet shape coefficient calculation, exterior ballistic solution and shooting precision calculation, damage power calculation, forms a complete ammunition database, shortens the ammunition development cycle, and enables related personnel to have a more in-depth and comprehensive understanding of the principle structure of the ammunition; damage evaluation and ammunition decision strategy are constructed, including target vulnerability database, bullet-target intersection condition calculation, connection of the integrated ammunition design, evaluation of the damage effect of the ammunition on the target, and giving of an ammunition use scheme according to the type, quantity and bullet-target intersection condition of the incoming target, to assist battlefield command decision; simulation training is executed, the damage effect of the ammunition on the target can be truly experienced in daily training, the use characteristics of various types of ammunition are well known, the battlefield fear is overcome, and through VR virtual reality technology, the soldiers can truly experience the battlefield gun smoke.

The invention discloses a method for selecting a weak environment information active sensitive device of a patrolling ammunition fuze, which comprises the following steps of: selecting a function, calculating scores, and selecting an active sensitive device with the highest score to detect weak environment information; the selection principle comprises the measurement precision, the installation performance, the frequency response range, the detection sensitivity and the linearity of the active sensitive device and the measurement precision under the change of natural environmental factors. According to the method, the patrolling ammunition fuze can select the active sensitive device with the optimal performance to sensitize the environment characteristics according to the weak environment information available in the outer trajectory flight, so that fuze researchers do not need to select the sensitive device depending on experience, trial and error are avoided, the fuze research and development period is shortened, and the process cost is reduced; and the fuze can be reliably sensitive to weak environment information.

The invention provides an internal and external ballistic parameter optimization method based on an NSGA-III algorithm and multi-factor coupling, and the method is used for optimizing an engine design scheme of an aircraft, and comprises the steps: obtaining an initial population containing a plurality of initial individuals, each initial individual representing a group of design variables of an engine; the initial individual is any one of missile appearance parameters or launching initial state parameters; for each initial individual, performing multi-factor coupling to obtain a plurality of aircraft state parameters corresponding to the initial individual and inner trajectory parameters corresponding to the aircraft state parameters; and performing parameter optimization on the initial individuals in the initial population by using an NSGA-III algorithm according to the plurality of aircraft state parameters and the respective corresponding inner ballistic parameters to obtain a parameter optimization result, thereby optimizing the engine design scheme on the premise of ensuring the optimal outer ballistic.

The invention discloses a high-precision calculation method and system for an outer trajectory of a projectile, and belongs to the technical field of artillery fire control. The method comprises the following steps: firstly, establishing a double-model structure consisting of a mass point differential equation model and a rotation angular velocity attenuation model so as to comprehensively describe mass center movement and rotation around the center of a projectile; and then, a four-order Runge-Kutta algorithm (RKF45) with adaptive step length is adopted to carry out numerical integration solution on the model, and the optimal balance between the calculation precision and the efficiency is realized by estimating a local truncation error in real time and dynamically adjusting the integration step length. According to the method, the defects that a traditional firing table method is low in precision and poor in adaptability and a fixed step size numerical solution method is insufficient in stability are effectively overcome, firing elements with higher precision and higher stability can be provided for a fire control system, and the hit rate and combat effectiveness of artillery are remarkably improved.

This invention discloses a method, system, device, and medium for extracting micro-motion features of projectile targets, relating to the field of target feature extraction. It involves constructing a measured model of the projectile target based on acquired projectile echo data; using simulation software to simulate the flight data of the measured model under experimental conditions and the measured model itself, and obtaining a simulated spectrum using modal decomposition and current time-frequency analysis methods; using a data fusion method to obtain fused data based on the measured projectile echo data of the projectile target within a certain time period and the external ballistic parameter data of the projectile target obtained through optical remote sensing; processing the fused data using data analysis to obtain a measured spectrum, which is then matched with the simulated spectrum to determine if the difference value is within a set range; if not, optimizing the initial time-frequency analysis method and determining the correct time-frequency analysis method; if yes, determining the target micro-motion features; this invention enables the detection or extraction of target micro-motion features.

The present invention belongs to the technical field of range testing, and particularly relates to an all-day enhanced external ballistic parameter measurement device and method. The device includes an infrared transceiver device, a wireless data transceiver device, a computer, and two unmanned aerial vehicles (UAVs). A sky screen target is installed under each of the two UAVs. The sky screen target includes a housing and a lens group fixedly arranged therein that can form an N-shaped light curtain. When a projectile passes through the N-shaped light curtain, the light flux entering the lens group becomes smaller, and the change in the light flux is converted into an electrical signal; the electrical signal can be calculated by the computer to obtain projectile information. The present invention has a high safety factor, accurate measurement, a wide range of applications, and the targeted selection of an ultrasonic altimeter can avoid the influence of using an infrared altimeter on the detection accuracy of the double N-shaped light curtain. The device of the present invention has a simple structure, low cost, is convenient to carry and operate, has a simple target layout for the device, and has a relatively high position tolerance, greatly improving the adaptability.

A ballistically enhanced projectile 360, 460 includes a body having a distal ogive section with external ballistic effect uniforming surface discontinuity (e.g., nose ring groove 369, 469) defined therein to provide an unsupported gap in the ogive profile which affects the flow of air over the front half of the ogive to provide greater aerodynamic uniformity and shot-to-shot consistency with more uniform observed external ballistics and superior terminal ballistics. The bullet's external surface discontinuity feature (369 or 469) creates effects in the flowfield that dominate any dynamic effects from bullet-to-bullet manufacturing inconsistency and resultant differences in dynamic behavior.

A cartridge is disclosed with a casing and a projectile, wherein external ballistic stability is provided by a center of pressure of the projectile being rearward of a center of mass of the projectile. The projectile includes flight control surfaces that cooperate with the bore of a barrel without requiring rifling or sabots. The projectile can include fin configurations that cooperate with the bore to form a bearing surface with the bore.

This invention belongs to the field of commercial aerospace and solid rocket optimization, and discloses a solid rocket trajectory optimization design method based on internal ballistic parameterization modeling. The method includes: determining the structural and energy characteristic parameters of the solid rocket motor; designing different types of propellant grains and constructing their geometric models; determining the internal ballistic parameterization model of the motor; constructing a dynamic model for joint optimization of the internal and external trajectories of the solid rocket; based on the dynamic model, setting the optimization objective of the joint internal and external trajectory optimization problem and representing it with a performance index function, and setting the constraints of the joint internal and external trajectory optimization problem; discretizing the dynamic model, performance index function, and constraints, converting them into a nonlinear programming problem and solving it to obtain the optimization results corresponding to each type of propellant grain; determining the performance index corresponding to each type of propellant grain based on the optimization results, and using the performance index to determine the propellant grain as the optimal design scheme.

The present invention belongs to the technical field of overall design of guided rockets, and specifically relates to a method for designing ratio parameters of a single-chamber dual-thrust solid rocket engine taking into account external ballistic constraints, comprising: step 1: optimizing the internal ballistics of an outer loop; step 2: optimizing the external ballistics of an inner loop; step 3: integrating the internal and external loops; the outstanding advantage of the present invention is that, when designing the internal ballistic thrust curve of the engine, the external ballistic constraints and the optimality of the range are comprehensively considered, and at the same time, the previous two-stage ratio design method relying on experience is transformed into a computer-automated optimization process. The obtained engine internal ballistic parameters can effectively reduce the external ballistic thermal environment pressure, improve the range capability, reduce the design costs such as the thermal protection of the projectile body, and improve the advancement of the overall design indicators.

The present invention discloses an inertial firing module for a rifled artillery fuze that can prevent ballistic explosion. The module comprises an end cap, an outer shell, an energy storage needle firing mechanism, a forward overload and unload identification mechanism for controlling the energy storage needle firing mechanism, a centrifugal safety mechanism for the forward overload and unload identification mechanism, and an anti-recovery mechanism for the centrifugal safety mechanism. The forward overload and unload identification mechanism primarily comprises a movable body and a movable body spring for identifying forward overload, and a sliding sleeve, a sliding sleeve spring, and a first ball for identifying unload. Several centrifugal pins disposed within blind holes surrounding the movable body use the frictional force generated by the centrifugal force acting on the inner wall of the outer shell to resist the abnormal forward thrust experienced by the movable body when the projectile's nutation angle returns to zero on the external trajectory. The movable body's center of mass is adjusted to the axis of the inertial firing module through radial drilling, so that its radial eccentricity relative to the projectile axis is close to zero. This prevents the movable body from accidentally releasing the energy storage needle firing mechanism on the external trajectory, thereby causing ballistic explosion.