132results about How to "Improve hit accuracy" patented technology

A golf club head includes a body, a striking plate engaged with the body and including a front side for striking a golf ball and a rear side, at least one vibration-receiving member made of an elastomeric material, and at least one adjusting member. At least one compartment is defined in a rear side of the body and is delimited by the rear side of the striking plate. The vibration-absorbing member is mounted in the compartment and in contact with a portion of the rear side of the striking plate. The adjusting member is adjustably mounted in the compartment to adjust a pressing force exerting on the rear side of the striking plate by the vibration-absorbing member and to adjust a compressed amount of the vibration-absorbing member, thereby effectively absorbing residual vibrations and avoiding loss of momentum.

A golf club, a driver, designed to provide an inprovement in the accuracy of ball control as club head speeds are increased from 100 miles per hour to the level of a semipro at 120 miles per hour. Most forces on the club head increase as the square of the velocity, representing a forty four percent increase. A detailed analysis has been made of forces generated during the collision of the ball and club head and their effect on trajectory of the ball. The design proposed greatly reduces the aerodynamic drag of the clubhead, increases the allowable tolerance to angular misalignment of the club striking face from two degrees to ten degrees and reduces the torque that twists the club head causing an angular misalignment prior to contact with the ball.

A gun barrel having a muzzle brake (2), especially for large-caliber guns, in which the muzzle brake (2) includes a tubular piece that has openings (16) around its circumference, and a jacket tube (4), which surrounds the tubular piece and has diametrically opposite gas-exit openings (17) that extend perpendicular to the bore longitudinal axis (15). To provide an arrangement comprising a barrel (1) and a muzzle brake (2) that minimizes the firing stresses on the parts of the muzzle brake (2) that are detachably connected to the barrel (1), the muzzle region (3) of the barrel (1) itself is used as a component of the muzzle brake (2. That is, the muzzle region of the barrel is provided with a plurality of openings (16) arranged in ring formation around the barrel (1), and the attached the jacket tube (4) is provided with slot-shaped gas-exit openings (17) over this muzzle region (3).

A carbon fiber tow composed of many carbon filaments and having a strand tensile strength of 3.8 to 5.5 GPa, a strand tensile modulus of 180 to 220 GPa and a carbon crystal size (Lc) of 13 to 18 Å. This carbon fiber tow can be produced by subjecting a precursor fiber tow composed of many polyacrylonitrile filaments which have a lightness difference (ΔL) of 50 or below and fineness of 1.1 to 1.7 dtex to oxidative stabilization and subjecting the stabilized fiber tow to carbonization with the maximum temperature within the range of 1,100 to 1,300° C. in an inert atmosphere while raising the temperature from 1,000° C. to the maximum temperature at a temperature rise rate of 100 to 2,000° C./min.

The invention discloses a method for improving coiling temperature control accuracy of hot rolled new-variety new-specification band steel and belongs to the field of control. The method includes that an on-site control computer dynamically controls production running parameters of production equipment in a hot rolling laminar flow cooling process according to a coiling temperature control model, a released product task and production process indicators; key production process information like band steel type, target thickness, target coiling temperature, rolling speed and band steel cooling mode are combined in a hot rolling laminar flow cooling control process; whether incoming materials from a previous process belong to new variety or new specification or not in a current process is automatically judged; model parameters of the new variety or the new specification in the current process during first-time production are automatically determined through a series of presumption logic so as to improve coiling temperature control accuracy and control qualification rate during first-time production of the band steel of the steel type or the new specification by the current process and lower 'waste, defective and downgraded rate in the process of first-time production to lower product manufacturing cost. The method can be widely used for the field of control on the hot rolling laminar flow cooling process.

The invention relates to a low-cost radar seeker semi-physical simulation test platform. The low-cost radar seeker semi-physical simulation test platform comprises a radar seeker, a turntable, a simulation computer, a target echo signal simulator, a target motion control system, a power amplifier component, a waveguide stimulation head, a FPGA (Field Programmable Gate Array) delay trigger module, a signal source and a target motion bracket, wherein the radar seeker is mounted on the turntable, the turntable is in control connection with the simulation computer, the target echo signal simulator is connected with the simulation computer, and the target motion control system, the power amplifier component and the waveguide stimulation head are connected. Compared with a common radio frequency semi-physical simulation test platform, the low-cost radar seeker semi-physical simulation test platform saves an anechoic chamber and radio frequency store-and-forward equipment, the simulation and test costs are greatly lowered, the construction period of a test system is shortened, and the development condition of the radar seeker and the development efficiency are improved.

A pneumatically operated projectile launching device preferably comprises an electro-pneumatic flow distribution mechanism that receives and directs compressed gas to a pneumatic mechanism to open a bolt.

A putter head includes a body and a light insert. The body includes a face portion, two mass portions, and a connecting portion. The face portion is located on a front side of the body, the mass portions are located on two sides of the body, and the connecting portion is formed between the mass portions for connecting the mass portions, with a compartment being defined between the mass portion and the connecting portion. The light insert is securely mounted in the compartment of the body. The light insert includes at least one aiming mark on a top face thereof. Further, the club head has a center of gravity positioned within the light insert.

The invention discloses a semi-strapdown air-to-air missile guidance method based on a sliding mode variable structural theory. The semi-strapdown air-to-air missile guidance method comprises the following steps of 1, acquiring a missile-target line-of-sight turn rate differential model under a line-of-sight coordinate system; 2, acquiring a motion tracking sliding mode guidance rule; and 3, acquiring an expected line-of-sight turn rate xd. According to the method, a sigmoid function is applied to the sliding mode surface design of the motion tracking sliding mode guidance rule, the missile-target line-of-sight angular rate is improved at the initial guidance stage, the estimation to the target motion state is improved, the missile-target line-of-sight angular rate is made to be zero at the last guidance stage, the miss distance is lowered, and the missile hit precision is improved.

A mating arrow mounted slide and arrow rest cradle assembly for bowfishing and bowhunting utilizes an arrow shaft mounted slide that is releasably snapped into a cradle carried by the riser of a bow, in which the slide cradle combination provides a tight arrow rest as well as an anchoring mechanism for one end of a line when used for bowfishing. When the arrow is released the slide unsnaps from the cradle and moves in unison with the arrow as the arrow moves out of the bow.

The invention disclosed is an apparatus and method for stabilizing an archery bow and reducing recoil during arrow draw and release. The apparatus comprises an adjustable arm clamp assembly; a rod; a support body for attaching the arm clamp assembly to the rod; and a mounting block for attaching the rod to an archery bow. The archery recoil stabilizer is lightweight, adjustable and relies on bracing the arm from the forearm position to restrict translational and rotational movement of the bow as well as minimize recoil impacts. It supports the arm by bracing the forearm relative to the bow, and reduces or eliminates bow hand torque, providing improved stabilization during both arrow draw and release. Additionally, this invention reduces the stress and recoil on the arm of the archer that can cause pain or injury, or can compromise the flight of the arrow and the accuracy of the shot.

The invention discloses a composite type anti-violence kinetic energy bullet with a two-stage dissipation mechanism. The composite type anti-violence kinetic energy bullet comprises a bullet shell, ahigh-pressure chamber, a low-pressure chamber, a bullet body, an impact rod, a buffer, a supporting body, an impact disc, a capsule and a bullet cap. A primer is riveted to the axis of the bottom endface of the bullet shell, the columnar high-pressure chamber is arranged on the upper side of the primer, a fire hole is formed in the axis of the upper end surface of the high-pressure chamber, the bullet shell is connected with the bullet body in an inserted mode to form the low-pressure chamber, one end of the impact rod is adhered to the top of the inner cavity of the bullet body in a connected mode, and the other end of the impact rod is connected with the buffer in an inserted mode; the supporting body extends into the impact rod and is fixedly connected with the impact rod, the supporting body is sleeved with an impact disc, and a capsule filled with a coloring agent is arranged on the top surface of the impact disc; and the bullet cap is in adhesion connection with the bullet body.The bullet is compact in structure and ingenious in design, the flying stability is improved through self-rotation of the bullet body, the striking precision is high, the two-stage dissipation mechanism is designed, excessive damage generated during short-distance shooting can be effectively avoided, meanwhile, the expected pain-causing effect is guaranteed during long-distance shooting, and dyeing marking of group targets is achieved at the same time.

The invention discloses a design method of an automatic pilot for a strapdown seeker. In control structure, a traditional mature three-loop overload tracking mode with pseudo attitude angle is adopted; three dominant poles of the automatic pilot are superposed on a real axis, and the superposed position is far from an imaginary axis on the basis of guaranteeing system stabilization margin and super small reverse overshoot so as to improve rapid response capability. On the basis of existing control system, the rapid response capability of the automatic pilot is lifted as much as possible, and any positive overshoot is avoided at the same time so as to realize overload instruction smooth tracking, reduce unfavorable influence to the strapdown seeker object identification algorithm by the automatic pilot substantially, and lift final hit precision greatly; in addition, the method also has the advantages of simple algorithm and easy engineering realization.

A method for integrating a large-calibre gun on a ship, including connecting a turret having an armament of a lad gun with a calibre >127 mm in a modular configuration to an adaptor plate and a shock-absorbing mounting, and installing the turret on the ship so that an existing steel structure of the ship withstands increased recoil forces from the armament.

The invention discloses a multi-effect integrated kinetic energy bomb with hierarchical dissipation of impact energy. The multi-effect integrated kinetic energy bomb comprises a multi-effect bomb head assembly, a bomb body assembly and a launching assembly; and the three assemblies are mechanically inserted front and back. During extremely high-speed impact, the multi-effect bomb head assembly generates two-stage shear failure, buffer spring limit compression and first-stage impact failure, and an extremely large amount of impact energy is dissipated; during high-speed impact, the multi-effect bomb head assembly generates two-stage shear failure and compression of most of buffer springs, and a large amount of impact energy is dissipated; therefore, hierarchical dissipation of impact energy is achieved, i.e. the function of achieving high energy dissipation during short-distance high-speed impact and low energy dissipation during long-distance low-speed impact; and the kinetic energy bomb has triple non-fatal effects of kinetic energy striking, lacrimation dispersing and dyeing marking at the same time under different impact conditions, and the problems that an existing kinetic energy bomb is excessively large in short-distance power and insufficient in long-distance efficiency is fundamentally solved.

The invention relates to a multi-rotor fire extinguishing unmanned aerial vehicle (UAV) system, comprising a chassis, engine arms, an undercarriage, motor bases, motors, quick release propeller seats,propellers, a flight control system, a battery pack and a fire extinguishing pod, wherein the engine arms are installed at the periphery of the undercarriage by means of engine arm folding connectionpieces; the undercarriage is installed under a main body of the chassis by means of a connection piece; the motor bases are respectively installed at terminals of the engine arms; the motors are installed on the motor bases; an electronic speed controller is also installed on each motor base; the quick release propeller seats are respectively installed on the motors; the propellers are installedon the quick release propeller seats; the flight control system is installed at the central position of the top of the chassis; the battery pack is installed on the top of the chassis; the fire extinguishing pod is installed under the chassis and is internally filled with fire extinguishing bullets. The multi-rotor fire extinguishing UAV system has the advantages of being simple in structure, easyto manufacture, practical and efficient.

The invention discloses an aircraft composite guidance method based on a non-linear sliding mode and preposition, and belongs to the technical field of aircraft flight guidance. The method comprises the following steps: firstly, measuring a sight angle of an aircraft by adopting seeker equipment, and measuring a yaw angle of the aircraft by adopting a gyroscope; constructing a sight angle approximate differential signal by adopting a first-order filter, and forming a nonlinear sliding mode signal by the sight angle approximate differential signal and the sight angle signal; meanwhile, settinga precondition to obtain a preangle, comparing the preangle with a sight angle and a yaw angle to obtain a preerror signal and a sight attitude error signal, conducting integration to obtain an integral signal, and then forming a nonlinear sliding mode signal based on errors; finally, conducting nonlinear recombination on the two types of nonlinear sliding mode signals based on the sight angle andthe error, and obtaining a final nonlinear sliding mode and front comprehensive guiding signal and transmitting to an attitude angle stabilizing system to achieve precise guiding. The method has theadvantages of being high in guiding precision, good in robustness and high in adaptability.

The invention discloses an airborne fire-extinguishing bomb device for an unmanned aerial vehicle, a fire-fighting unmanned aerial vehicle, and a launching control method. The airborne fire-extinguishing bomb device for the unmanned aerial vehicle comprises an N-linked launching canister unit, a three-axis servo stabilization unit, a fire control unit, and a fire-extinguishing bomb launching controller, wherein the N-linked launching canister unit is mounted on an unmanned aerial vehicle body; the three-axis servo stabilization unit is used for isolating attitude disturbance during the flightor hovering of the unmanned aerial vehicle body, so that the stability of the N-linked launching canister unit is ensured; the fire control unit generates the coordinates of impact points of fire-extinguishing bombs under a current flight attitude condition, meanwhile, a launching wave gate is arranged, and when the impact points fall into the launching wave gate, automatic launching signals for the fire-extinguishing bombs are generated according to a set launching sequence; and the fire-extinguishing bomb launching controller is used for generating fire-extinguishing bomb ignition launchingaction according to the automatic launching signals for the fire-extinguishing bombs, so that launching for the fire-extinguishing bombs is realized. According to the airborne fire-extinguishing bombdevice for the unmanned aerial vehicle, the fire-fighting unmanned aerial vehicle, and the launching control method, the disturbance is isolated through the three-axis servo stabilization unit, so that the aiming and firing accuracy, and the intelligent degree are increased.

The invention discloses a spinning projectile attitude angle computing method based on a state observer. The spinning projectile attitude angle computing method based on the state observer comprises the steps that the angular speed of a spinning projectile relative to a navigation coordinate system at the current time is obtained, and components of the angular speed on all axes of a projectile body coordinate system are determined; the roll angle correction component, the roll angle measurement component, the pitch angle and the yaw angle of the spinning projectile at the current time are obtained; an attitude angle updating matrix is built by utilization of the components of the angular speed, the roll angle correction component, the roll angle measurement component, the pitch angle and the yaw angle; a feedback gain matrix is computed by utilizing the attitude angle updating matrix; and according to the attitude angle updating matrix, the feedback gain matrix and the attitude angle of the spinning projectile at the current time, the attitude angle of the spinning projectile at the next time is computed. The spinning projectile attitude angle computing method based on the state observer can achieve real-time alignment of the high-speed spinning projectile in air and improve the hit precision of the high-speed spinning projectile.

A back recess balance weight structure for golf club heads is located on a back side of a golf club head relative to the striking face and includes a back recess body and a sealing cap. The back recess body has a back recess with a plurality of cavities formed therein. The sealing cap covers the back recess by bonding. The structure consists of simple elements. The sealing cap is made from a material of a smaller specific gravity to move the weight of the club head to the optimal position. The adhesive can absorb shock and vibration to form a tight sealing of the sealing cap and the back recess body. Thereby optimal stability and striking accuracy can be achieved during swinging of the golf club.

A device comprised of bubble level inserted into and secured within a cavity located above the rifle grip and behind the barrel to facilitate the measurement and compensation of the rifle's cant while lining up the rifle's sights. The device is precision machined to allow the bubble to be aligned with the axis of the barrel to produce a true “zero-cant” condition. Graduation markings are placed on either left or right of the bubble level to allow the user to better judge the relative degree of cant. Methods of using the embedded cant indicator for precision shooting are presented.