20 results about "Projectile" patented technology

A device (1) is provided for measuring imbalance of a projectile (10), comprising a support (2) defining a main axis (2a) and a main plane (2b) orthogonal to the main axis (2b), and including a cavity (20) suitable for housing a projectile (10) centred with respect to the main axis (2a), a tubular body (21 ) bounding the cavity (20) radially to the main axis (2a) so as to surround the projectile (10), a base (22) bounding the cavity (20) parallel to the main plane (2b) so as to face the bottom of the projectile (10); movement means (3) configured to move the projectile (10) in the cavity (20) rotating about the main axis (2a); and measurement means (4) configured to measure at least one vibration of the support (2) in the main plane (2b) and / or parallel to the main axis (2a) with respect to a fixed structure, such as a floor or a frame integral with the floor; and one or more compressed air circuits (5) distributed between the body (21 ) and the base (22), configured respectively to apply at least a second pneumatic force (F2) on the projectile along the main axis (2a), defining a second air bearing (5b) between the projectile (10) and the base (22) to allow the projectile (10) to float in air with respect to the base (22), and to alternatively or simultaneously apply at least a first pneumatic force (F1) normal to the main axis (2a) and / or tangential to the projectile (10) parallel to the main plane (2b), defining at least a first air bearing (5a) around the projectile (10), and apply at least a third pneumatic force (F3) tangential to the projectile (10), realizing at least part of the movement means (3).

The application discloses a light-weight split type centering structure suitable for a sub-caliber dynamic accelerating device and belongs to the technical field of special launching. The application comprises a front centering part, a rear centering part and an adjusting mechanism; the front centering part is composed of a plurality of annular supports with the same structure according to the length of a projectile body and is sequentially sleeved on the projectile body; the rear centering part is connected with the sleeve through a center blind hole; the bottom surface of the center blind hole of the rear centering part abuts against the tail end surface of the projectile body; the adjusting mechanism is composed of a long screw rod and a plurality of nuts; the position of the annular support of the front centering part is adjusted by adjusting the screwing position; the application reduces the proportion of useless projectile support mass in the launching mass; under the condition of the same launching propellant amount, the projectile body obtains a higher speed, and the design index of reducing the launching mass is realized.

The invention relates to a projectile (10) with a projectile casing (12) having a projectile front (14) with a front opening (18), wherein the front opening (18) can be closed by means of a locking screw (20), wherein a filling explosive charge centering tube (42) is attached inside the projectile casing (12), in which at least one filling explosive charge (60, 62) limited by a filling explosive charge cup (64, 66) is arranged, wherein a predetermined breaking point (68) is formed on a bottom (54) of the filling explosive charge centering tube (42) facing away from the projectile front (14), and wherein at least one vent channel (70, 72) is formed on the filling explosive charge cup (64, 66), which provides a flow connection between a first internal section (74) at the bottom (54) of the filling explosive charge centering tube (42) and a second internal section (76) of the filling explosive charge centering tube. (42) is produced, which is located on the side of the filling explosive charge (60, 62) facing the projectile front (14).

The invention relates to an optical gate (100) for determining a velocity vector (V) of a spherical projectile (10), which comprises a sensor array (20) defined by a row of light detecting sensors (22) arranged next to each other, and an illuminating array (30) defined by a row of point light sources (32) arranged next to each other and illuminating towards the sensors (22), wherein the illuminating array (30) is arranged opposite the sensor array (20). The illuminating array (30) and said sensor array (20) being arranged in a common plane (S), and an optical diffuser plate (40) being arranged between said illuminating array (30) and said sensor array (20), said light detecting sensors (22) defining a detection area (42) on said diffuser plate (40) parallel to said sensor array (20), and the optical gate (100) comprises an electronic control unit (36) configured to consecutively flash the point light sources (32) at predetermined time instants at high frequency, and an electronic measuring unit (26) for processing the signals generated by the light detecting sensors (22). The measuring unit (26) being configured to determine the brightness distribution and total brightness along the detection area (42) based on the data generated by the sensors (22) of the sensor array (20). The invention also relates to methods for determining the velocity vector (V) of a spherical projectile (10).

This invention discloses a constrained free-fall type fragile cover impact test system and method, belonging to the field of mechanical equipment performance testing. It includes: a support base to ensure the guide frame is perpendicular to the ground; an impact projectile suspended within the guide frame, with an adjustable height; the guide frame connected to the fragile cover by fasteners, simulating the constraint and guidance of the launch box / tube on the impact projectile, allowing the projectile to impact the fragile cover in free fall without jamming or eccentricity; and a sensor for measuring the impact force. This invention replaces the constraint and guidance of the launch box (tube) on the projectile with the constraint and guidance of the guide frame, utilizes the principle of free fall to represent the velocity of the projectile impacting the fragile cover, and measures the impact force that breaks the fragile cover using a sensor. The structure is simple, significantly reducing testing costs; it offers good guidance and centering accuracy, preventing projectile eccentricity and accurately simulating actual working conditions; the fragile cover is easy to assemble and disassemble, resulting in high testing efficiency.

This invention discloses a multi-pulse loading nonlinear response amplification test device and method for explosive structures, relating to the field of structural and material response simulation technology under impact loads. It includes a loading section and a structural response section. The loading section includes a projectile A, which has a large-diameter end and a small-diameter end. A projectile B is disposed outside the small-diameter end of projectile A, and a projectile C is disposed outside projectile B. An adjusting ring B is disposed at the end of projectile B near the large-diameter end of projectile A, and an adjusting ring C is disposed at the end of projectile C near the large-diameter end of projectile A. The masses of projectiles A, B, and C are equal. The structural response section includes a limiting block and a mass block, with a force transmission rod disposed between the limiting block and the mass block. The mass block has a loading through-hole and a mounting hole for the force transmission rod. This test device can achieve loading pulses of no less than 3 times, explosive pressure on the order of hundreds of MPa, and pressure amplitude amplification of approximately 1.9 times, with a short test cycle and low cost.

This invention discloses an efficient analysis method for projectile-target separation during the penetration resistance process of a hollow heterogeneous protective structure, belonging to the field of impact dynamics. The method includes: for a given hollow heterogeneous protective structure; establishing a finite element model of the projectile; constructing a storage array for the spatial position information of the hollow heterogeneous protective structure; establishing a target drag function based on cavity expansion theory; constructing a projectile-target separation analysis model for the hollow heterogeneous protective structure; obtaining the results of the projectile-target separation analysis method using explicit dynamics methods; obtaining the storage array for the spatial position information of the hollow heterogeneous protective structure at the time of simulation termination, including projectile deformation, stress state, and the spatial position information at the time of simulation termination; further obtaining the crater morphology of the hollow heterogeneous protective structure through data processing of the storage array; and determining whether the given hollow heterogeneous protective structure will lead to projectile destruction by combining axial force and bending moment failure criteria. This invention achieves high-efficiency, low-cost, and rapid simulation analysis.

Training and / or entertainment device (1), wherein the device (1) provides a plurality of targets for a projectile fired by the user, the plurality of targets comprising a first opening (2) and a second opening (2'), the second opening (2') being bidirectionally connected to the first opening (2) via a path through at least a part of the device (1), such that, when in use, a projectile entering the device (1) through the first opening (2) can fly along the path and exit the device (1) through the second opening (2') and vice versa, wherein the device (1) comprises: at least one indicator instructing the user to propel the projectile from outside the device (1) towards one or more of the targets provided by the device (1), comprising at least one indicator instructing the userto propel the projectile from outside the device (1) towards the first opening (2), and at least one indicator instructing the user to propel the projectile from outside the device (1) towards the second opening (2'); at least one sensor operable to detect the movement of the projectile along the path; wherein the sensor(s) is / are operable in such a way as to be connected to the indicator(s) such that, after detecting the movement of the projectile along the path, one of the indicators is selectively activated to instruct the user to propel the projectile towards one of the targets provided by the device (1).

A method of three-dimensional mapping using a projectile equipped with LIDAR, the method comprising: transmitting a signal to a light source to cause the light source to emit a plurality of light pulses, the light source being located on a spin projectile advancing along a predetermined path; receiving a plurality of reflected light pulses at the spin projectile, the plurality of reflected light pulses being responsive to the plurality of light pulses reflected from the object or terrain portion; determining a distance of the object or terrain portion from the light source; and generating a three-dimensional map of the object based on the determined distance of the object or terrain portion from the light source.

This application relates to the field of shipbuilding, specifically to a method and apparatus, electronic equipment, and computer-readable storage medium for confirming shot peening strengthening parameters of corner structures. The method includes: performing single-projectile impact simulation on a simulated target model to obtain single-projectile impact parameters; determining the number of projectiles corresponding to different crater coverage rates based on the crater size, and constructing multiple data pairs with one-to-one correspondence between projectile velocity, projectile number, and crater coverage rate; performing simulated shot peening tests on the simulated target model based on the multiple data pairs to obtain the simulated shot peening test results corresponding to each data pair; and determining the target shot peening strengthening parameters corresponding to the target corner structure based on the simulated shot peening test results. The method and apparatus, electronic equipment, and computer-readable storage medium for confirming shot peening strengthening parameters of corner structures provided in this application can improve the technical effect of confirming the optimal shot peening strengthening parameters of corner structures and improve the reliability of shot peening strengthening results.

This application discloses a method, apparatus, electronic device, and medium for detecting objects thrown from heights. The method includes: if a target lens detects a projectile in either a short-focal-length lens or a long-focal-length lens, then, based on a target image captured by the target lens, determining first motion information of the projectile within the target lens's field of view; based on the first motion information of the projectile within the target field of view and another field of view of the other lens, determining second motion information of the projectile within another field of view; and verifying the projectile detection result of the target lens based on the detection result of an object satisfying the second motion information in another captured image of the other lens. This solution can improve the accuracy of projectile detection by using the predicted second motion information of the projectile in another field of view and verification in another captured image when one lens detects a projectile, through the synergistic effect of the two lenses.

This utility model provides a corner reflector launching system, relating to the field of corner reflector launching technology. The corner reflector launching system provided by this utility model places the projectile component in the launching chamber and uses the driving force generated by the driving component to push the projectile component to launch, so that the projectile component flies in the air. At this time, the first connecting rope is in a slack state. When the first connecting rope is taut, the projectile component stops in the air, thereby relying on the inertial descent component and the corner reflector component to separate from the projectile component, realizing the separation operation. This alleviates the technical problem of the complex separation structure used by the existing corner reflector device to detach from the projectile.

This utility model belongs to the technical field of testing equipment and discloses a device for detecting the depth of the propellant surface of a projectile. It includes a frame, a mounting plate mounted on the frame, a motor mounted on the mounting plate, a lead screw connected to the output end of the motor, slide rails mounted on the frame, a movable plate mounted on both slide rails, a threaded sleeve fixedly mounted on the back side of the movable plate, a bracket connected to the lower end of the movable plate, a guide sleeve mounted on the bracket, and a reference plate mounted on the lower side of the guide sleeve. A displacement sensor is mounted on the movable plate, a pull rod connected to the output end of the displacement sensor, a connecting sleeve connected to the end of the pull rod, and a guide rod connected to the connecting sleeve. The guide rod slides and matches the guide sleeve, and a detection probe is connected to the lower end of the guide rod. The device uses a physical contact method for measurement, which effectively flattens the propellant surface during measurement and avoids problems such as fluffing, ensuring the accuracy of the detection data.

The invention relates to a projectile (10) with a projectile casing (12) extending along a central longitudinal axis (M) and having a projectile front (14), wherein the projectile casing (12) has an opening (30) along the central longitudinal axis (M) facing away from the projectile front (14), at which the projectile casing (12) is provided with an internal thread (32), wherein a projectile base insert (36) is provided which has a first external thread (38) with which the projectile base insert (36) can be screwed into the internal thread (32), wherein the projectile base insert (36) closes the opening (30) when screwed in, wherein a retaining ring (40) is provided which has a second external thread (42) and which secures the projectile base insert (36) screwed into the internal thread (32) to the projectile front (14). the opposite side of the floor insert (36) can be screwed into the opening (30),wherein the retaining ring (40) rests against the floor base insert (36) when screwed in.

The application discloses an analysis method for large attack angle and large attack angle aerodynamic interpolation, relates to the field of computer technology methods, and comprises the following steps: S1, acquiring a launch system speed vector and a flight attitude of an aircraft; S2, constructing a projectile body coordinate system and a speed coordinate system; S3, analyzing a conversion matrix from the launch system to the projectile body coordinate system; S4, analyzing a speed vector of the projectile body coordinate system; S5, analyzing an attack angle, a sideslip angle and a total attack angle; S6, analyzing a total normal force coefficient, a total axial force coefficient and a total pitching moment coefficient; and S7, decomposing the total normal force coefficient and the total axial force coefficient into projectile body coordinate system aerodynamic force coefficients, and decomposing the total pitching moment coefficient into a projectile body coordinate system moment coefficient. The method is based on speed vector analysis of more than 90 degrees of large attack angle, can be applied to large attack angle flight or static instability flight attack angle and sideslip angle analysis, and can directly analyze aerodynamic force and aerodynamic moment conversion methods in a sideslip angle direction and a total attack angle plane, so that the number of aerodynamic calculation state point spaces is simplified under the premise of ensuring interpolation precision.

The application provides a layered protection structure damage determination method and device based on a virtual explosion source, and relates to the technical field of protection, to solve one of the technical problems that the layered protection structure is difficult to determine the collapse damage effect and has poor accuracy. The method comprises the following steps: obtaining the incident speed of a projectile body and the thickness of each layer of the protection structure; determining that the projectile body is embedded in the corresponding layer of the protection structure according to the incident speed of the projectile body and the thickness of the corresponding layer; if the projectile body is embedded in the main support layer and the explosion center of the projectile body is located in the main support layer, it is determined that the protection structure is damaged; if the projectile body is embedded in the bullet-proof layer or the dispersion layer, the first stress wave peak value at the top of the main support layer is calculated; the projectile body is equivalent to explosion in a preset structure by using a virtual explosion source method; and whether the protection structure is damaged is determined according to the position of the virtual explosion source in the preset structure and the thickness of the main support layer. The method can effectively determine the damage effect of the protection structure.

This invention belongs to the technical field of oil extraction equipment, specifically disclosing a retrieval device for a perforated projectile in an oilfield well. The device includes an upper connector, a control chamber, a retrieval chamber, and a guide head. The upper connector has oil threads and its end is connected to the flange of the control chamber. The control chamber contains a remote communication unit and a hydraulic valve group. The retrieval chamber is divided into an inner cylinder and an outer cylinder. A hydraulic cylinder is located at the top of the inner wall of the outer cylinder and is connected to the end of the inner cylinder. The inner cylinder extends and retracts within the outer cylinder driven by the hydraulic cylinder. The control chamber is detachably connected to the outer cylinder. The inner cylinder contains a retrieval mechanism for retrieving foreign objects from the well. The guide head is composed of several fan-shaped plates forming a cone shape, each fan-shaped plate being hinged to the outer cylinder. A connecting rod is located on the inner cylinder. The extension and retraction of the hydraulic cylinder drives the connecting rod to synchronously rotate the fan-shaped plates, adjusting the opening angle of the guide head. Once the device reaches the location of the foreign object, the retrieval mechanism is activated to complete the retrieval. The entire process is automated through hydraulic drive and remote control.

The application discloses a method and device for estimating the attitude angle of a projectile based on a space-time fusion double-branch network, and belongs to the technical field of carrier attitude estimation. The method comprises the following steps: using a pitch angle branch of the space-time fusion double-branch network to perform feature coding and time sequence modeling on an infrared grayscale image sequence to obtain time sequence enhanced pitch angle features; using a roll angle branch of the space-time fusion double-branch network to perform feature coding and time sequence modeling on the infrared grayscale image sequence to obtain time sequence enhanced roll angle features; inputting the time sequence enhanced pitch angle features and the time sequence enhanced roll angle features into corresponding multi-layer perceptrons respectively to obtain space-time fused pitch angle cosine and sine representation results and roll angle cosine and sine representation results; and using four-quadrant inverse tangent functions to solve the pitch angle cosine and sine representation results and the roll angle cosine and sine representation results respectively to obtain an estimated value of the pitch angle of the projectile and an estimated value of the roll angle of the projectile. The application can realize real-time and high-precision attitude estimation of a rotating projectile.

A projectile and method for stopping aerial vehicles. The projectile (101) comprises a shell (120) and a bunch of filaments (105). The bunch (105) is wound in a coil and placed inside the shell (120). The projectile (101) according to the solution may be brought to a target by different methods and utilising different means. For example, the projectile (101) may be fired with compressed air or a propulsion charge, by using a compressed air weapon or rocket launcher. In addition, the projectile (101) may be taken to the target by using a rocket or aerial vehicle.