8results about How to "Improve drop point accuracy" patented technology

The invention relates to the technical field of ink-jet printing, and discloses a nozzle coordinate compensation method, device and equipment and a storage medium, and the method comprises the steps: obtaining the coordinate information of a nozzle; performing data processing on the nozzle coordinate information to obtain coordinate information before compensation; constructing a nozzle plane equation according to the coordinate information before compensation; performing rotation matrix solving on the nozzle plane equation to obtain a coordinate transformation matrix; performing coordinate transformation on the coordinate information before compensation according to the coordinate transformation matrix to obtain coordinate information after compensation; generating nozzle coordinate compensation information according to the coordinate information before compensation and the coordinate information after compensation; according to the method, the nozzle coordinate compensation information is generated by performing fitting processing on the nozzle plane, the coordinate position of the nozzle is adjusted by using the nozzle coordinate compensation information, and the ink-jet printer is controlled to perform delayed or lagged jet processing on the ink droplets at different heights, so that the drop point precision of the printing ink droplets is improved, and better ink-jet printing precision is obtained.

The utility model discloses a kind of 48 millimeter detonation bomb of deterrent type hand-throwing type riot, including firing mechanism and medicine box mechanism, firing mechanism includes fuse body, grip piece and needle prick delay detonator, still movably connected with pin shaft and split pin on fuse body, still connected with spring and firing pin block assembly on pin shaft, firing pin block assembly includes firing pin and turnover block, firing pin block assembly has first position and second position, when first position, spring is in compression state under the action of turnover block, and spring reset can drive firing pin block assembly to rotate from first position to second position;Split pin is connected with pull ring;Medicine box mechanism includes shell, inner medicine box and end cover, inner medicine box is filled with detonating agent, needle prick delay detonator extends into detonating agent, filling chamber is opened in shell, filling chamber is filled with paraffin wax.This scheme can emit greater sound and strong light, suitable for use in vast space, and can carry out more accurate strike.

The application discloses a rail polishing unit and a rail polishing trolley, and the rail polishing unit comprises a suspension assembly, a unit frame assembly, a motor mounting platform, a motor guide assembly, a polishing motor, a polishing grinding wheel, a lifting driving mechanism and a deflection driving mechanism. The suspension assembly is connected with a trolley frame, and the unit frame assembly is slidably connected with the suspension assembly. The motor mounting platform is hinged with the lower part of the unit frame assembly, and the motor guide assembly is connected with the motor mounting platform. The polishing motor is slidably connected with the motor guide assembly, and the polishing grinding wheel is connected with the output shaft of the polishing motor. The two ends of the lifting driving mechanism are respectively hinged with the polishing motor and the motor mounting platform. The two ends of the deflection driving mechanism are respectively hinged with the trolley frame and the motor mounting platform. The application can solve the technical problems of the existing rail polishing unit, such as large space occupation, large lifting resistance, low polishing efficiency and poor maintainability.

The invention relates to the technical field of fire fighting and extinguishing, in particular to a forest fire extinguishing rocket projectile with a racemization empennage, which comprises a projectile head, a projectile body, a solid rocket engine, the racemization empennage and a baffle ring, the bomb body is provided with a shell, a superfine dry powder extinguishing agent, a front sealing plate, a rear sealing plate and an initiating explosive column, the solid rocket engine provides power for flight, the rotation eliminating empennage can rotate around the axis of the bomb body to eliminate airflow interference, and the baffle ring axially limits the rotation eliminating empennage; according to the forest fire extinguishing rocket projectile with the racemization empennage, long-distance launching is achieved through the solid rocket engine, accurate spreading of the fire extinguishing agent is guaranteed through the infrared proximity fuze, the superfine dry powder fire extinguishing agent is environmentally friendly and efficient, the racemization empennage improves the drop point precision, the forest fire extinguishing rocket projectile is suitable for fire extinguishing of large-area fire sources such as forests and grasslands, the casualty risk is reduced, and the forest fire extinguishing rocket projectile is suitable for large-area fire extinguishing. And the fire extinguishing timeliness and effectiveness are effectively improved.

The invention discloses a method for rapidly deploying a stratospheric aerostat through a guidance brake parachute. Relates to the field of high-altitude aerostats. The method comprises the steps that S1, in the ground preparation stage, a floating platform, a floating balloon and a brake parachute which are connected in sequence are contained in a carrying cabin, and the brake parachute is located on the outermost side of the carrying cabin; s2, the carrying cabin body is conveyed to a preset airspace, and then the brake parachute is unlocked and separated from the cabin body; s3, the posture of the brake parachute is changed through an adjusting assembly so as to control the descending track of the carrying cabin body; s4, after speed reduction is completed, the floating air ball is unlocked and pulled out of the carrying cabin, and the floating air ball is inflated through an inflation assembly; s5, after inflation is performed for a preset time, the brake parachute is separated from the floating air ball; s6, after the brake parachute is separated from a certain distance, the carrying cabin is separated from the floating air ball, and the floating air ball and the floating platform are left in the air to work; s7, recovering the brake parachute and the carrying cabin body; according to the system, a guidance speed reduction device, an inflation system and a floating platform are contained in a cabin, and an aircraft or a rocket serves as a carrier to rapidly throw the cabin to the high altitude of a target area; the cabin body decelerates through the guidance brake parachute, the inflation assembly in the cabin completes the inflation process of the floating balloon in the air, the aerostat and the effective load stay in the air through a separation measure, and the time for preparing procedures on the ground is saved.

The present invention discloses a calibration method, system and medium for the acceleration error term coefficient of PIGA, which belongs to the field of rocket launch technology. The uniform acceleration stage of a centrifuge is used to stimulate the output of the acceleration error term to calibrate. The calibration accuracy of the acceleration error coefficient is simulated and analyzed by taking the PIGA output as the observed quantity. Through analysis, it is known that in the specific application of rocket launch, the circular probability error CEP of the rocket landing point during calibration is two orders of magnitude smaller than the circular probability error CEP without calibration, which improves the accuracy and practicality.

The invention discloses an in-atmosphere solid sounding rocket guidance method and system, and the method comprises the following steps: obtaining disturbance factors, determining the values of the disturbance factors, and forming a deviation data table; according to the deviation data in the deviation data table, random targeting simulation is conducted on rocket flight, and nominal, upward deviation and downward deviation trajectory data are obtained and stored; determining an online real-time calculation program angle according to the stored nominal, upward deviation and downward deviation ballistic data; judging whether preset time is reached or not; and if the preset time is reached, carrying out shaft fixing treatment. According to the guidance method, the guidance algorithm is simple in principle, and the amount of data needing to be calculated before injection is small. The whole guidance calculation process is easy to understand, the requirement for the calculation step length is not too high, the requirement for rocket equipment is not high, and the drop point precision achieved through the guidance algorithm provided by the invention is high.

The invention discloses a vertical landing type recoverable solid rocket booster. A combustion chamber comprises a descending section and an ascending section; the descending section comprises a descending section combustion chamber shell, a descending section combustion chamber heat insulation layer is arranged on the inner wall of the descending section combustion chamber shell, descending section charge is arranged in the descending section combustion chamber shell, and a descending section igniter is arranged in the descending section combustion chamber shell; an air rudder is arranged outside the descending section combustion chamber shell; the ascending section comprises an ascending section combustion chamber shell, an ascending section combustion chamber heat insulation layer is arranged on the inner wall of the ascending section combustion chamber shell, and ascending section charge is arranged in the ascending section combustion chamber shell; a soft pulse isolation layer is installed between the descending section combustion chamber shell and the ascending section combustion chamber shell, and the descending section combustion chamber shell and the ascending section combustion chamber shell are connected through flanges. The method is high in drop point precision, small in landing impact and good in environmental adaptability; the booster is simple in overall structure, easy to disassemble and assemble and low in cost of repeated use after being recycled, and better energy distribution is achieved.