31results about How to "Reduce launch preparation time" patented technology

The invention provides a multi-cylinder synergistic erecting hydraulic system. The multi-cylinder synergistic erecting hydraulic system comprises an erecting loop, a launcher loop and a locking loop.The multi-cylinder synergistic erecting hydraulic system is composed of a hydraulic source (1), a reversing valve bank (2), a rodless cavity valve bank (3), a rod cavity valve bank (4), a launcher valve bank (5), an erecting oil cylinder (6), a locking oil cylinder (7) and a launcher oil cylinder (8). The multi-cylinder synergistic erecting hydraulic system is characterized in that double-acting hydraulic cylinders are adopted for an erecting mechanism and a launcher correspondingly and used for achieving separate motion of the erecting mechanism and the launcher; meanwhile, rapid linkage erecting and releveling of the erecting mechanism and the launcher can be achieved, the erecting speed is increased by 20% compared with the former practice, and the releveling speed can be increased by 30%; launching preparation time is shortened; safety of the linkage erecting process is improved; the chattering phenomenon generated in the oil cylinder grade changing process is eliminated; and steadiness of the erecting process is improved.

The invention discloses an autonomous orientation device. The autonomous orientation device comprises a north seeking system, a laser self-collimation system, an automatic leveling system and a translation system; the laser self-collimation system and the north seeking system are fixed, and the laser self-collimation system coincides with a plumb axis of the north seeking system; the north seekingsystem is disposed above the automatic leveling system, and the automatic leveling system can perform leveling on the north seeking system and the laser self-collimation system; the automatic leveling system is disposed on the translation system and can horizontally move along with the translation system; and the translation system performs translational motion when the laser self-collimation system sends a translation command to the translation system. The invention further discloses a control method of the autonomous orientation device. The autonomous orientation device and the control method can realize full-automatic autonomous orientation.

The invention discloses an estimation and compensation method of an inertial navigation initial benchmark. The estimation and compensation method has the advantages that inertial navigation initial benchmark errors are estimated through the position and speed information provided by satellite navigation and the position and speed information obtained by inertial navigation calculation and by using a Kalman filtering manner, attitude angles are corrected according to attitude control requirements and by using program angle attitude regulating, speed and positions are corrected at the same time, attitude angle calculation precision is increased, and guidance and terminal guidance shift accuracy is increased.

The invention discloses a wireless test emission control system and method for an aircraft, and relates to the field of spaceflight test emission control, the system comprises a ground device and an aircraft device, and the ground device is provided with a first communication assembly and an electric energy emission assembly; the aircraft device is provided with a second communication assembly andan electric energy receiving assembly, and the second communication assembly is used for wirelessly receiving a test emission control instruction of the first communication assembly of the ground device and transmitting the test emission control instruction to other equipment of the aircraft device; other equipment of the aircraft device completes autonomous test emission control according to thetest emission control instruction and forms a test emission control result, and the second communication assembly wirelessly sends the test emission result to the first communication assembly; and the electric energy receiving assembly is used for wirelessly receiving the electric energy of the electric energy transmitting assembly. According to the invention, the problems that the existing testemission control system and method adopt wired connection, the number of wires and cables is large, and manpower, material resources and time are consumed can be solved.

A rocket launching pad supporting leg locking system comprises a supporting leg cylinder with one end arranged on a rocket launching pad and the other end provided with a supporting disc, four pushing cylinders sequentially arranged on the supporting disc at 90-degree intervals and pressing blocks arranged on moving parts of the pushing cylinders. The limiting seat is arranged on the switching disc and used for being attached to and pressing the pressing blocks arranged on the pushing cylinders, and the control system is in communication connection with the supporting leg cylinders and the pushing cylinders. The control system is used for remotely controlling the supporting leg cylinders and the pushing cylinders to work. After the rocket is erected, the control system controls the supporting leg cylinders to ascend so that the pressing blocks can make contact with the limiting bases in place, then the control system is used for controlling the pushing cylinders to stretch out, the pressing blocks and the corresponding limiting bases are matched for pressing, and the rocket launching end is locked to the supporting leg cylinders. After the rocket is launched, the control system controls the pushing cylinders to retract, the matching relation between the pressing block and the limiting base is relieved, and then the control system is used for controlling the landing leg cylinders to descend, so that the pressing block is separated from the limiting base.

The invention relates to a rapid compass alignment method for an underwater vehicle before launching on a mobile carrier platform, which is suitable for the rapid alignment method for a strapdown inertial navigation system of the underwater vehicle before launching on the mobile carrier platform. According to the method, a reverse compass alignment control loop is provided, inertial navigation data are stored, forward compass alignment and reverse compass alignment are combined, and forward compass alignment and reverse compass alignment are carried out repeatedly and alternately until the difference between two times of alignment is within a given allowable range. According to the algorithm, repeated alignment is performed by using the stored data, so that the compass alignment time is effectively shortened and the launching preparation time of the underwater vehicle is shortened on the premise of the same alignment precision.

A single-side fast opening and closing control system of a large double-top-cover mechanism of a launching platform comprises a front top cover, a rear top cover, a front top cover hydraulic oil cylinder for driving the front top cover to move, and a rear top cover hydraulic oil cylinder for driving the rear top cover to move. Hydraulic pipelines connected with the front top cover hydraulic oil cylinder and the rear top cover hydraulic oil cylinder are respectively provided with a proportional flow valve, a proportional overflow valve and an electromagnetic directional valve. A valve micro-processing controller is connected with the proportional flow valves, the proportional overflow valves and the electromagnetic directional valves. A main controller is connected with the valve micro-processing controller and photoelectric encoders through a CAN bus. The photoelectric encoders are arranged on a front top cover mechanism and a rear top cover mechanism respectively. Double-loop individual control is performed on the front top cover and the rear top cover, and the flow of a front top cover loop and the flow of a rear top cover loop are controlled through the proportional flow valves respectively; the movement speed of the front top cover and the movement speed of the rear top cover are kept consistent, the front top cover mechanism and the rear top cover mechanism do not interfere with each other, damage to the front top cover mechanism and the rear top cover mechanism is prevented, the top covers are fast opened and closed in a double top cover linkage mode when the launching platform carries out movements of the top cover mechanism, and the launching preparation time is shortened.

The invention relates to a sigma-delta type AD-based quartz watch acceleration acquisition system and acceleration acquisition method. The quartz watch acceleration acquisition system provided by theinvention is a quartz watch acceleration acquisition system applied to a platform system, in particular to a quartz watch acceleration acquisition system adopting a sigma-delta type AD. The acquisition system comprises a switching circuit, a wide-range sampling resistor, a medium-range sampling resistor, a small-range sampling resistor, a pre-amplification circuit, a sigma-delta type AD acquisition circuit, a temperature control circuit, an FPGA control circuit, a serial port output circuit and a system power source. According to the acquisition system, the response speed of the system to micro current is improved, so that the platform can identify the acceleration state of a current position in real time, leveling time in the platform system is reduced, and launching preparation time is shortened.

A single-side fast opening and closing control method of a large double-top-cover mechanism of a launching platform includes the top cover opening step and the top cover closing step. The single-side fast opening and closing control method is characterized in that the top cover opening step and the top cover closing step are the top cover linkage opening step and the top cover linkage closing step in which PI closed-loop control is adopted. According to the single-side fast opening and closing control method of the large double-top-cover mechanism of the launching platform, based on the characteristics that double top covers are large mechanical structures and large in mass and inertia, corresponding speed reduction angles are set for a front top cover switch and a rear top cover switch in order to avoid that the top covers shake severely when being opened or closed to the stop angles, when the top covers reach the speed reduction angles, the output of a proportional valve is reduced by a control system so that the top covers can be slowed down, and thus the top covers can be opened and closed smoothly and stably.

A unilateral rapid switch control system for a large-scale double roof mechanism on a launch platform, including front and rear roofs, front and rear roof hydraulic cylinders that drive the movement of the front and rear roofs, and hydraulic pipelines connected to the front and rear roof hydraulic cylinders There are proportional flow valves, proportional overflow valves and electromagnetic reversing valves. The controller is connected with the photoelectric encoder; the photoelectric encoder is arranged on the front and rear top cover mechanisms. In the present invention, the dual circuits of the front and rear top covers are separately controlled, and the flow rate of the front top cover circuit and the rear top cover circuit are respectively controlled by using a proportional flow valve; When the launch platform performs the action of the top cover mechanism, the double top cover linkage method is used to realize the quick switch of the top cover and shorten the launch preparation time.

The invention provides a multi-cylinder synergistic erecting hydraulic system. The multi-cylinder synergistic erecting hydraulic system comprises an erecting loop, a launcher loop and a locking loop.The multi-cylinder synergistic erecting hydraulic system is composed of a hydraulic source (1), a reversing valve bank (2), a rodless cavity valve bank (3), a rod cavity valve bank (4), a launcher valve bank (5), an erecting oil cylinder (6), a locking oil cylinder (7) and a launcher oil cylinder (8). The multi-cylinder synergistic erecting hydraulic system is characterized in that double-acting hydraulic cylinders are adopted for an erecting mechanism and a launcher correspondingly and used for achieving separate motion of the erecting mechanism and the launcher; meanwhile, rapid linkage erecting and releveling of the erecting mechanism and the launcher can be achieved, the erecting speed is increased by 20% compared with the former practice, and the releveling speed can be increased by 30%; launching preparation time is shortened; safety of the linkage erecting process is improved; the chattering phenomenon generated in the oil cylinder grade changing process is eliminated; and steadiness of the erecting process is improved.

The invention relates to a random attitude MEMS (Micro Electro Mechanical System) combined attitude determination method without initial alignment. The method comprises the following steps of: 1) defining and correcting Rodrigues parameters; 2) establishing a nonlinear attitude error state equation based on the corrected Rodriges parameters; 3) establishing a nonlinear observation equation of themagnetometer; 4) performing linearization processing on the nonlinear attitude error state equation and the observation equation of the magnetometer to obtain a state error linearization state error model and a magnetometer linearization observation model; 5) utilizing the obtained nonlinear state error equation and observation equation; and combining the linear state model and the observation model, obtaining the optimal estimation of the corrected Rodrigues parameters by utilizing an extended Kalman filtering method, and taking the optimal estimation as an attitude result for guidance control, thereby realizing the MEMS and magnetometer combination attitude determination of any attitude.

The invention discloses a horizontal segmented assembly method of a multi-stage rocket, which belongs to the technical field of aerospace ground support equipment. In this method, firstly, the longitudinal axis of the transport support vehicle is adjusted to be parallel to the axis of the core-level rocket body; secondly, the core-level rocket body is hoisted horizontally to the four-degree-of-freedom horizontal docking device on the transport support vehicle, and the four-degree-of-freedom horizontal docking device is used to adjust The attitude of the core first-stage arrow body reaches the predetermined attitude and is fixed; then the core second-level arrow body is hoisted horizontally to another set of four-degree-of-freedom horizontal docking devices, and the attitude of the core second-stage arrow body is adjusted through the docking device to make it consistent with the core-one arrow body. The first-level rocket body is accurately docked and then fixed to complete the assembly of the core-level rocket body and the core-level second-level rocket body; repeat the above-mentioned process to complete the docking assembly between the core-level rocket bodies in turn, and finally fix the core-level rocket body on the car body. transportation. The invention simplifies the complexity of the whole rocket launch preparation process and shortens the launch preparation time.

The invention relates to a random attitude MEMS (Micro Electro Mechanical System) combined attitude determination method without initial alignment. The method comprises the following steps of: 1) defining and correcting Rodrigues parameters; 2) establishing a nonlinear attitude error state equation based on the corrected Rodriges parameters; 3) establishing a nonlinear observation equation of themagnetometer; 4) performing linearization processing on the nonlinear attitude error state equation and the observation equation of the magnetometer to obtain a state error linearization state error model and a magnetometer linearization observation model; 5) utilizing the obtained nonlinear state error equation and observation equation; and combining the linear state model and the observation model, obtaining the optimal estimation of the corrected Rodrigues parameters by utilizing an extended Kalman filtering method, and taking the optimal estimation as an attitude result for guidance control, thereby realizing the MEMS and magnetometer combination attitude determination of any attitude.

The invention relates to a method for rapid initial alignment between travels after the launch of the strapdown inertial navigation system of an underwater vehicle. First, the strapdown inertial navigation system of the underwater vehicle needs to be roughly aligned before launching, then launch, and then navigate. This method is used for precise alignment while performing maneuvering tasks. The specific implementation steps of the method are: storing the gyroscope and accelerometer data of the inertial navigation and the speed data of the Doppler velocimeter, and then using the data of the gyroscope and the accelerometer to alternately perform post-shooting forward compass alignment and post-shooting The reverse compass alignment and the velocity damping using the velocity data of the Doppler velocity meter finally achieve the required alignment accuracy and end the alignment process. The method enables the underwater vehicle to perform precise alignment in the process of performing maneuvering tasks after launch, reduces the launch preparation time of the underwater vehicle, and improves the maneuverability of the underwater vehicle. The stored data is reused to improve data utilization and reduce the precise alignment time.

The invention discloses a horizontal aiming result compensation method under a horizontal state. The method comprises the following steps of S1, measuring to obtain a horizontal aiming angle alphaD'ofa first-level aircraft in the horizontal state by using a collimator; S2, determining an installation error angle delta-zetaz; S3, determining a horizontal aiming angle of a second-level aircraft according to the installation error angle delta-zetaz and the horizontal aiming angle alphaD'of the first-level aircraft. The method can calculate the installation error angles of the first-level aircraft and the second-level aircraft in advance by using an inertial measurement unit and quickly determine the horizontal aiming angle of the second-level aircraft on the basis of measuring to obtain thehorizontal aiming angle of the first-level aircraft before the launch.

The invention discloses a high-precision rapid transposition method suitable for a four-axis inertial platform system, which comprises the following steps of: firstly, calculating the projection of frame angle deviation on a platform body coordinate system according to the corresponding relation between a frame shaft system of a four-axis three-frame platform and the platform body coordinate system, and then distributing rough moment adding open-loop control of moment adding quantity according to the angle difference of each shaft; the angle of the frame is quickly rotated from any position to a target position, meanwhile, the influence of three-axis cross-linking is reduced, and finally coarse moment-increasing closed-loop control and fine moment-increasing closed-loop control are performed near a target, so that the frame is stabilized at the target position. According to the method for rapidly rotating the three axes to the target position at the same time and keeping high precision, the phenomenon of platform cross-linking can be eliminated, and then the purpose of rapidly launching the inertial navigation system is achieved.

The present invention provides a space vehicle transfer docking locking device, comprising: a transfer erection frame, which is configured to erect the space vehicle and is placed on a traveling device, the traveling device provides forward power to transport the transfer erection frame , the lower surface of the transfer erection frame includes a concave guide rail; a platform bracket is configured to support the transfer erection frame transported by the traveling device, the platform bracket is installed on one side of the launch pad, and the platform The upper surface of the bracket includes a convex guide rail; and locking assemblies are respectively disposed on the transfer upright and the platform bracket and configured to lock the transfer upright on the platform bracket. The space vehicle transfer and docking locking device saves manpower, improves the docking efficiency, and shortens the launch preparation time of the space vehicle.

The invention provides a carrier rocket transfer limiting device which comprises a limiting base. The limiting base comprises an upper extending body, a side body and a lower extending body, the upper extending body is formed by extending from the upper end of the side body to the direction away from a center position, and the lower extending body is formed by extending from the lower end of the side body to the direction close to the center position; and the upper extending body of the limiting base is used for being fixedly connected to a transfer frame carrying a carrier rocket, and the lower extending body of the limiting base is provided with a first hollow structure. A floating limiting block is arranged in a space formed by the lower extending body and the side body, a free floating gap is reserved, and the floating limiting block is provided with a second hollow structure penetrating through the upper side and the lower side of the floating limiting block; a limiting piece is fixed to the side body of the limiting base, and one end of the limiting piece extends into the limiting base; and a limiting pin is used for being clamped in the second hollow structure, and the other end of the limiting pin is used for being fixedly connected to a transport vehicle. By means of the limiting device, butt joint positioning of the transport vehicle and the transfer frame is effective, and manpower can be reduced.

The invention discloses a flame blocking device of an electric plugging and unplugging mechanism of a launcher. The flame blocking device of the electric plugging and unplugging mechanism of the launcher comprises a flame blocking box sliding rail, an electric plug, a four-connecting-rod mechanism, an L-shaped connecting rod, a base plate, a V-shaped connecting rod, a rotary shaft base, a sliding rod, a sliding sleeve, a flame blocking plate and a four-connecting-rod mounting base, wherein the flame blocking box sliding rail is located on the left side of the electric plug, the sliding rod is connected with the flame blocking plate, the sliding sleeve is located below the sliding rod, the four-connecting-rod mounting base is located at the bottom of the L-shaped connecting rod, and the electric plug is mounted on the base plate through the four-connecting-rod mechanism and the four-connecting-rod mounting base; one end of the L-shaped connecting rod is hinged to a rear hinge point of the electric plug, and the other end of the L-shaped connecting rod is hinged to a hinge point at one end of the V-shaped connecting rod; and a hinge point in the middle of the V-shaped connecting rod is hinged to the base plate through the rotary shaft base. According to the flame blocking device of the electric plugging and unplugging mechanism of the launcher, design and mounting can be simplified, so that the reliability is improved, the launching preparation time is shortened, and the launching efficiency is improved.

The invention discloses an estimation and compensation method of an inertial navigation initial benchmark. The estimation and compensation method has the advantages that inertial navigation initial benchmark errors are estimated through the position and speed information provided by satellite navigation and the position and speed information obtained by inertial navigation calculation and by using a Kalman filtering manner, attitude angles are corrected according to attitude control requirements and by using program angle attitude regulating, speed and positions are corrected at the same time, attitude angle calculation precision is increased, and guidance and terminal guidance shift accuracy is increased.

The embodiment of the invention provides launch preparation equipment of a carrier rocket and a launch preparation method of the launch preparation equipment. In the launching preparation equipment provided by the embodiment of the invention, the launching platform is arranged at one end of the supporting structure, and in the transfer process of the carrier rocket, the liftable walking mechanism moves into the first groove of the supporting structure in the erecting system to drive the erecting system to rise, so that the first supporting part and the second supporting part are both separated from the ground; therefore, the erecting system and the launching pad are transported to the target position of the launching area, the process of butt joint of the erecting system and the launching pad can be omitted, the launching preparation time of the carrier rocket can be shortened, and the launching efficiency can be improved; afterwards, the lifting walking mechanism is lowered, so that the first supporting part and the second supporting part are both in direct contact with the ground, the lifting walking mechanism can move out of the first groove, the lifting walking mechanism can independently leave the launching area and can be prevented from being damaged by high-temperature tail flames generated during launching, and therefore the reliability of the launching preparation equipment can be improved.

The invention discloses a rocket thermal insulation protection device capable of being rapidly withdrawn and a method. The protection device comprise a truss barrel capable of being opened and closes,a power device, a sliding rail and a heating thermal insulation device; a hinge is arranged on the vertical surface of the barrel, and an opening is formed in the vertical surface of the barrel, so that the opening and closing function of the barrel is realized; the power device provides power for withdrawing the truss barrel; and the sliding rail is an I-shaped steel rail fixed to the bottom surface, not only can provide convenience for withdrawing the truss barrel, but also can achieve the pulling resistance of the truss barrel through a pulley device, so that the stability of the truss barrel under wind load is achieved. The protection device has the advantages that the construction speed is high, and rocket assembling in extremely cold weather can be completed quickly; and rapid withdrawal can be realized, and the rocket launching preparation time is shortened.

The invention discloses a target launch control system. The system includes a remote control module, a launch control test system module and a power supply module. The remote control module is respectively connected to the launch control test system module and the power supply module. According to the first command, the second command, the third command and the launch command of the remote control module, the system module treats the launched target missiles respectively, collects the corresponding test results and sends them to the remote control module, and the remote control module respectively receives the data collected by the launch control test system module. The test results of each stage of the test are judged whether the test results of each test stage are qualified. After passing the test, the corresponding instructions of each stage are sent to the launch control test system module. After all the test results are qualified, the launch command is sent to the launch control test system module. The system module sends an ignition command to the target missile to be launched to realize the launch of the target missile to be launched, thereby simplifying the preparation work before the launch of the target missile and reducing the connection cables at the remote end.

The invention provides a carrier rocket transfer limiting device, comprising: a limiting seat, including an upper extension body, a side body, and a lower extension body. The body is formed by extending along the lower end of the side body toward the direction close to the central position, the upper extension body of the limit seat is used to be fixedly connected to the transfer frame carrying the launch vehicle, and the lower extension body of the limit seat has a first hollow structure; The floating limit block is arranged in the space formed by the lower extension body and the side body and leaves a gap for free floating. The floating limit block has a second hollow structure running through its upper and lower sides; the limit piece is fixed on the limit seat The side body and one end extend to the inside of the limit seat; the limit pin is used to engage in the second hollow structure, and the other end of the limit pin is used to be fixedly connected to the transport vehicle. The limiting device makes the docking positioning of the transport vehicle and the transfer frame effective and can reduce manpower.

The invention discloses a packaging structure and method for an electric plugging-pulling mechanism of a launching device. The packaging structure comprises a plugging-pulling mechanism box body mounting plate, an electric plug, a projectile body socket, a projectile body, a launching device cavity, a launching device body and a plugging-pulling mechanism box body set screw; a packaging plate mounting part comprises a blanking plate and a packaging plate set screw; one plugging-pulling mechanism box body is located below the plugging-pulling mechanism box body mounting plate; the plugging-pulling mechanism box body mounting plate is connected with the plugging-pulling mechanism box body set screw; the electric plug is connected with the projectile body through the projectile body socket; the projectile body socket is located on the top of the electric plug; the projectile body is located on the top of the projectile body socket; the launching device cavity is located on the right side of the plugging-pulling mechanism box body; and the plugging-pulling mechanism box body set screw is located at the bottom of the plugging-pulling mechanism box body mounting plate. According to the packaging structure, mounting of the plugging-pulling mechanism and a plugging-pulling mechanism flame-blocking plate can be simplified, so that the launch preparing time is saved, launching efficiency is improved, and the difficult problems of filed installation of the plugging-pulling mechanism and the flame-blocking plate of the launching device are effectively solved.

The invention discloses a wireless test launch control system and method for an aircraft, and relates to the field of aerospace test launch control. The system includes: a ground device and an aircraft device, the ground device is provided with a first communication component and an electric energy transmitting component; the aircraft device is provided with The second communication component and the power receiving component, the second communication component is used to wirelessly receive the test launch control command of the first communication component of the ground device, and transmit it to other equipment of the aircraft device; the other equipment of the aircraft device is controlled according to the test launch The command completes the autonomous test emission control and forms the test emission control result, and the second communication component wirelessly sends the test emission result to the first communication component; the power receiving component is used for wirelessly receiving the power of the power transmitting component. The invention can solve the problem that the existing test launch control system and method adopt wired connection, have a large number of wires and cables, and consume manpower, material resources and time.