35 results about "Launch angle" patented technology

The embodiment of the invention discloses an erecting control system for a rocket launched on the sea. The erecting control system for the rocket launched on the sea comprises a control module, a tilt angle sensor, a rotary encoder and an erecting frame. The first input end of the control module is in communication connection with the output end of the tilt angle sensor; the second input end of the control module is in communication connection with the output end of the rotary encoder; the input end of the tilt angle sensor is in communication connection with the erecting frame; the input end of the rotary encoder is in communication connection with the erecting frame; the marine launching angle is adjusted through the tilt angle sensor and the rotary encoder, relying on a launching ship is not needed, the launching cost is reduced, the launching maneuverability is improved, the launching period is shortened, the device can be suitable for different types of rockets, and high marine launching flexibility, good task adaptability and high launching economical efficiency are achieved.

A remote launcher includes a base frame, a cradle, a cradle actuator, and a launch control system. The cradle is pivotably coupled to the base frame and includes one or more skids that are configured to receive and support an unmanned water-based deployable. The cradle actuator is coupled to the base frame and to the cradle. The launch control system includes a communication interface, a processor, and memory having instructions. The instructions direct the launch control system to receive, via the communication interface, one or more wireless launch signals and then, in response thereto, generate at least one cradle control signal to enable the cradle actuator to incline the cradle to a launch angle.

The invention provides a mechanical boomerang launching device and a using method thereof, and belongs to the technical field of boomerang launching. The launching device comprises a base, a rotating device, a dart body adapting device, a power output device and an angle adjusting device. A sliding rail, a descending groove and a buckle are arranged on the upper surface of the base, a plurality of grooves are formed in the lower surface of the base at intervals, and the grooves are matched with an angle adjusting device to achieve angle adjustment of the base. The rotating device is used for generating an angular velocity before the boomerang is launched; the dart body adapting device is used for installing and limiting the boomerang; the power output device is used for providing linear speed; the angle adjusting device is used for adjusting the launching elevation angle, and accurate setting of the launching elevation angle is achieved. Through mechanical angular velocity, linear velocity and launching angle control, the rotation success rate, launching stability and safety of the boomerang can be remarkably improved, and the boomerang is suitable for test and competitive occasions.

The present invention relates to the field of construction engineering technology, and discloses a building slope deformation monitoring device and a monitoring method thereof, comprising a slope, a laser generating assembly fixedly mounted on the top of the slope, a dustproof assembly fixedly mounted on the bottom of the slope, and a driving assembly fixedly mounted on the laser generating assembly. The present invention rotates a laser emitter using a rotating support plate and a slope top mounting bracket. When monitoring is required, it is only necessary to start the cylinder to push the main push rod to the left at the right end of the tee pipe 1, and push the hydraulic oil at the right end of the tee pipe 1 to the left between the rack 1 and the movable plate, thereby driving the rack 1 to move upward, and through engagement with the gear, the emitting end of the laser emitter can be driven to rotate downward. By rotating the emitting end of the laser emitter downward so that the laser is irradiated on the laser receiving plate, the emission angle of the laser can be automatically adjusted during the monitoring process, with a high degree of automation.

The present invention relates to a rope net launch device with adjustable launch angles. It comprises a rope net bag, a hot knife mechanism, a net bag tether, a net silo, an adjustable launch mechanism, and a chamber base. The silo is a columnar structure with a hyperbolic main line. The silo wall is provided with multiple evenly distributed weight-reducing holes. The rope net bag is disposed within the silo. A hot knife mechanism is provided on the silo's outer wall. The net bag tether is wound around the silo's periphery in an interlaced manner, and the hot knife mechanism is used to secure the rope net bag and cut the net bag tether. The adjustable launch mechanism comprises four assembled launch tubes evenly disposed around the silo. A chamber base is provided at the bottom of the silo. The chambers within the chamber base are connected to the assembled launch tubes. The ends of the assembled launch tubes are connected to the chamber base via a cap to adjust the launch angle. The present invention enables the launch of a rope net traction body at multiple angles with a wide adjustment range, enabling the capture and removal of space debris.

This application discloses a beam configuration method, apparatus, and computer program product. The beam configuration method includes: determining a horizontal beam and a vertical beam, as well as the antenna's horizontal angle of arrival and vertical angle of arrival, based on each sampling point and SSB beam information in a measurement report; determining downlink simulated transmit angle information, including simulated downlink horizontal transmit angle and simulated downlink vertical transmit angle, based on the vectors of the horizontal and vertical beams; and determining the beam configuration based on the difference between the simulated downlink horizontal transmit angle and the antenna's horizontal angle of arrival, and the difference between the simulated downlink vertical transmit angle and the antenna's vertical angle of arrival. This application's embodiment, based on the sampling point data and SSB beam information in the measurement report data reported by the terminal, ensures greater accuracy of the data, thereby identifying whether the beam configuration is reasonable and improving the accuracy and adaptability of the beam configuration.

This invention discloses a high-speed parallel water entry experimental launching device and method for a vehicle, belonging to the field of hydrodynamic experiments. It includes a supporting base, a parallel controller, a parallel launching assembly, and a power unit. The parallel launching assembly is mounted on the supporting base via the parallel controller, and the power unit provides launching power and adjusts the water entry velocity. The parallel launching assembly includes a first launching device and a second launching device arranged side-by-side, enabling parallel launching of two projectiles and adjustment of the launching angle. The parallel controller includes a parallel control mechanism and a spacing adjustment mechanism. The parallel control mechanism ensures the relative parallelism of the first and second launching devices, while the spacing adjustment mechanism adjusts the launching distance between the first and second launching devices. This invention has a simple and practical structure, is easy to assemble, has high reliability and durability, and exhibits good repeatability and safety, providing experimental assurance for studying the hydrodynamic characteristics of structures at the moment of water entry.

An experimental apparatus and method for investigating the Magnus effect are disclosed. The base includes a launching mechanism, an air compression mechanism, and an air volume adjustment mechanism. The launching mechanism includes an angle indicator disk with a launching angle adjustment mechanism at its bottom. A launching tube is connected to the center of the angle indicator disk via a power air intake pipe. A suspension seat connected to the wall of the launching tube is located inside the launching tube above the power air intake pipe. An air guide pipe is located at the center of the suspension seat, and the upper end of the power air intake pipe is inserted into the air guide pipe. The launching object is placed on the suspension seat. A suspension air intake pipe is located on the lower side wall of the power air intake pipe. A left-handed and a right-handed air intake pipe, symmetrical about the centerline, are located in the middle of the side wall of the launching tube. A reflective photoelectric speed sensor is installed on the side wall of the launching tube below the right-handed air intake pipe. The air compressor is connected to the left-handed and right-handed air intake pipes, the power air intake pipe, and the suspension air intake pipe via the air volume adjustment mechanism. This invention clearly and intuitively demonstrates the principle of the influence of the Magnus effect on the flight trajectory of the launching object.

According to the centering and leveling device for the anchor plate, through the combined design of the base part, the horizontal detection part and the laser emission part, high-precision centering and leveling in the anchor plate installation process are achieved. The base part can quickly and stably fix the device to a preset mounting point of an anchor plate, the horizontal detection part monitors the horizontal state of the device in real time to ensure that the levelness of the anchor plate meets the requirement, and the laser emission part accurately adjusts the emission angle of a laser emitter through an angle adjustment mechanism to enable laser to point to a preset target position, so that the accuracy of the device is improved. Therefore, accurate centering of the anchor plate is realized. The device has the advantages of being simple in structure, convenient to operate and high in adjusting precision, the construction efficiency can be remarkably improved, and errors caused by manual operation are reduced.

The invention discloses an anti-falling safety control method with field angle constraint. The anti-falling safety control method comprises the steps of control time sequence binding before launching, guide module initial value binding before starting control, attitude angle instruction amplitude limiting after starting control, control parameter serialization and rudder resource dynamic allocation. The control time sequence binding means that the starting control time of the aircraft is judged according to the initial launching angle, and when the launching angle is lower than a specific angle, the aircraft is advanced before engine ignition; the initial value binding of the guiding module before starting control refers to optimizing an attitude angle instruction according to a detector constraint, optimizing control parameters before and after thrust establishment, and preventing parameter jumping; the dynamic allocation of rudder resources refers to preferentially allocating the rudder resources of the pitching-off channel, and transition to rolling channel priority is performed after the falling risk is released, so that subsequent overload instruction access is facilitated. According to the method, the emission safety requirement and the detector constraint are comprehensively considered, the control time sequence and the initial control parameters are selected according to the emission state, the emission safety problem is solved, meanwhile, it is guaranteed that the detector normally locks the target, and the overall performance of the system is improved.

The invention discloses a laser optical fiber sheath and a laser vaporization ablation operation device, and relates to the technical field of medical instruments. The laser optical fiber sheath comprises an optical fiber, a positioning piece, a reflecting piece and a rotating piece, and the positioning piece is arranged on the outer side of the optical fiber and used for fixing the emission angle of the optical fiber; the reflecting part is close to the transmitting end of the optical fiber, one side, close to the transmitting end, of the reflecting part is provided with a reflecting inclined surface, and the reflecting inclined surface is obliquely arranged relative to the laser transmitting direction and is used for reflecting laser emitted by the optical fiber; one end of the rotating piece is connected with the reflecting piece and used for driving the reflecting piece to rotate with the laser emitting direction as the axis. Based on the technical scheme disclosed by the invention, not only can the temperature rise of laser energy be improved to meet the surgical requirements of coagulation necrosis and vaporization ablation of specific target tissues, but also the control and light path design can be effectively simplified, and the operation difficulty of the laser ablation surgery is reduced.

Described here are optical sampling architectures and methods for operation thereof. An optical sampling architecture can be capable of emitting a launch sheet light beam towards a launch region and receiving a detection sheet light beam from a detection region. The launch region can have one dimension that is elongated relative to another dimension. The detection region can also have one dimension elongated relative to another dimension such that the system can selectively accept light having one or more properties (e.g., angle of incidence, beam size, beam shape, etc.). In some examples, the elongated dimension of the detection region can be greater than the elongated dimension of the launch region. In some examples, the system can include an outcoupler array and associated components for creating a launch sheet light beam having light rays with different in-plane launch positions and / or in-plane launch angles.

The invention relates to the technical field of moving target positioning and tracking, and discloses a target positioning and tracking method and system for space-time hysteresis compensation, and the system comprises a data collection module, a prediction module, a calculation module, an optimization module, and a control module. The data acquisition module is used for acquiring motion state parameters of a carrier and track parameters of a moving target; the prediction module is used for predicting and supplementing the motion state parameters and the track parameters; the calculation module is used for calculating the disturbance offset of the laser; the optimization module sets the target emission time based on the disturbance offset and calculates the hysteresis compensation amount of the laser; and the control module controls the laser to be emitted at the target emission time based on the hysteresis compensation amount. According to the invention, by identifying the disturbance mode of laser emission, optimizing the emission opportunity and carrying out the space-time hysteresis compensation of the emission angle, the hit precision and environmental adaptability of the laser emission system to the high-speed moving target are improved.

The invention provides a lateral light guide optical fiber and an optical imaging mechanism with the same, the lateral light guide optical fiber comprises a first optical fiber, two ends of the first optical fiber are a light source end and an emergent end respectively, the light source end is used for receiving an external light source, and a fiber core and a first cladding guide the external light source from the light source end to the emergent end in an internal reflection mode. An included angle is formed between the first inclined plane and the extension direction of the first optical fiber, a second cladding is arranged on the surface of the first inclined plane, and a third cladding is arranged on the surface of the side, opposite to the first inclined plane, of the first optical fiber, so that light reflected by the interface of the fiber core and the second cladding is irradiated outwards through the interface of the fiber core and the third cladding. According to the scheme provided by the invention, the emission angle of the light beam is optimized through the inclined plane design, the adjustment of the light output angle and intensity can be realized, the light signal intensity of the received light is ensured, and greater design freedom degree and flexibility are provided, so that the light source can better meet the requirement of detecting the detected tissue.

The application discloses a one-rocket multi-satellite rocket adapter and a rocket, and belongs to the technical field of spaceflight equipment. The one-rocket multi-satellite rocket adapter comprises a first satellite support, a second satellite support and two main support frames, and has the advantages of simple structure and high assembly efficiency. The first satellite support, the second satellite support and the main support frames are detachably connected, so that the one-rocket multi-satellite rocket adapter can be detached, and is more convenient to transport or install to a rocket body. After the application is applied, the satellite can be fixed on the first satellite support, the adapter can be fully utilized everywhere, meanwhile, the fairing space in the rocket body can be fully utilized, so that the adapter can fix more satellites to a certain extent. Since the satellite can be fixed on the first satellite support, the satellite can be launched towards a second direction, so that the application can be applied to a launch task with various launch angle requirements.

The application discloses a kind of hyperbolic-like front angle remodeling terminal guidance strategy based on relative distance, including the following steps: establishing the kinematic model of missile in two-dimensional plane intercepts stationary target;Design guidance strategy based on hyperbolic equation, solve the geometric parameters of hyperbolic according to the initial conditions of missile and target, obtain the analytical equation of guidance strategy about design parameter;According to the kinematic relationship inverse solution specified angle of different launch angle parameters.The guidance strategy in the application uses equation constraint to front angle information, meets the attack angle constraint under the condition of zero miss distance strike, and end view angle rate converges to 0, and guidance parameters are obtained by numerical integration calculation, without linearization to model, simplify the design of guidance system.The application improves the applicability of guidance system, and the design method is simple and applicable.

The invention discloses a method and a system for predicting simultaneous impact during interval launching of aircrafts, and belongs to the technical field of data prediction processing. The method comprises the following steps: modeling according to an aircraft; changing the initial launching angle and the starting control distance to obtain a launching angle-starting control distance function curve; normalization processing is carried out, and multi-layer image data features are obtained through wavelet decomposition; feature points obtained through wavelet decomposition are used for labeling, and two kinds of wavelets with different parameter coefficients are used for reconstructing an emission angle-starting control distance function; performing difference operation on a function prediction value obtained by prediction and an actual value, and performing multiple rounds of learning to transform parameters of the wavelet itself; reconstructing a prediction function curve by using wavelet transform, and setting miss distance as a trust degree function; and analyzing the obtained wavelet prediction function, setting an initial emission angle and required interval time, and searching a proper interval according to a credibility function. According to the method, the region generated by the minimum value and the maximum value of the overall time can be accurately predicted.

The invention relates to a universal launching device for an unmanned aerial vehicle and an underwater unmanned underwater vehicle, and belongs to the technical field of unmanned equipment launching. The device comprises a launching bin made of a closed stainless steel material, a split type launching tube in the launching bin is matched with a UAV through an inner-layer launching tube, a split type launching tube in the launching bin is matched with an AUV through an outer-layer launching tube, and an outer-layer electromagnetic coil and a propelling column electromagnetic coil are integrated to achieve electromagnetic driving; the release device is linked with the high-pressure gas release bin through the push rod controller to complete ejection; the detection and control unit realizes automatic target identification and emission instruction generation through an optical fiber laser radar and an embedded system; the horizontal adjusting device and the pitching adjusting device cooperatively adjust the launching angle. The method solves the problems of poor compatibility, platform dependence, insufficient automation and weak environmental adaptability in the prior art, has the advantages of rapid multi-task deployment, high-precision adjustment and stable operation in a complex environment, and is suitable for the fields of military reconnaissance, marine exploration and anti-unmanned aerial vehicle.

The present invention relates to the field of mass spectrometry detection technology, and in particular to a laser adjustment component for mass spectrometry detection, the structure of which includes: a fixed seat, a support block, a Z-axis positive and negative motion adjustment device, a horizontal motion adjustment device, a Z-axis tilting motion adjustment device, a slide, a laser connecting column, a cover plate, an adjustment frame, and an optical fiber connector, and the support block is installed on the fixed seat. The component of the present invention is simple and easy to adjust, and the component is compact and does not take up too much space. The positive and negative motion of the X, Y, and Z axes of the laser and the Z-axis tilting at a certain angle are achieved through the Z-axis positive and negative motion adjustment device, the horizontal motion adjustment device, and the Z-axis tilting motion adjustment device, which has the function of being suitable for the adjustment requirements of the laser focusing and emission angle, thereby realizing multi-dimensional adjustment of the laser, which is more conducive to the laser decomposition ion source, and the focusing position accuracy and displacement accuracy can also be effectively guaranteed, thereby facilitating the actual debugging of the laser focusing and emission angle by personnel, and improving the excitation and dissociation effect of the sample.

The utility model relates to a launch canister, ignition device and rocket projectile, launch canister includes barrel body and two first connecting portion, barrel body is equipped with the launch chamber that the projectile body and engine stretch into and place, the two first connecting portion is both provided the side portion of barrel body, and the launch canister is equipped with the launch chamber that the launch body and engine stretch into. The first connecting part is provided with a first end which can be electrically connected with fire control positive and negative electrode wires, and is also provided with a second end which can be used for extending and contacting the connecting ends of the ignition positive and negative electrode wires to realize electric connection, so that the fire control positive and negative electrode wires are electrically connected with the ignition positive and negative electrode wires in a one-to-one correspondence manner respectively. According to the launch canister, the ignition device and the rocket projectile, the problem that the launch angle of the projectile body deviates due to the fact that the initial disturbance of an existing engine ignition mode is large is solved.

The utility model relates to a focusable laser output head comprising a tail end fixing module; one end of the middle adjustable module is connected with the tail end fixing module, the other end of the middle adjustable module is provided with a first adjusting part, and the first adjusting part is movably arranged in the full-length direction of the tail end fixing module; and the front-end adjustable module is arranged at the other end of the middle adjustable module, one end of the front-end adjustable module is fixedly connected with an adjusting part, the other end of the front-end adjustable module is provided with a lens group and a free lens, and the free lens is movably arranged in the full-length direction of the tail-end fixing module through a second adjusting part. According to the utility model, the middle adjustable module and the front-end adjustable module are arranged to freely select focusing to control the size of a light spot or adjust an emission angle, and the arrangement of the double adjustable modules enables the adjustment to be more accurate; compared with a traditional adjusting output head, the structure of the adjustable output head is more attractive.

Described here are optical sampling architectures and methods for operation thereof. An optical sampling architecture can be capable of emitting a launch sheet light beam towards a launch region and receiving a detection sheet light beam from a detection region. The launch region can have one dimension that is elongated relative to another dimension. The detection region can also have one dimension elongated relative to another dimension such that the system can selectively accept light having one or more properties (e.g., angle of incidence, beam size, beam shape, etc.). In some examples, the elongated dimension of the detection region can be greater than the elongated dimension of the launch region. In some examples, the system can include an outcoupler array and associated components for creating a launch sheet light beam having light rays with different in-plane launch positions and / or in-plane launch angles.

The present application relates to the target tracking field, and particularly relates to a full-range point-to-point tracking modulated electronic beacon, which comprises a divergence angle light source A, a modulation monitoring circuit, a driving circuit and a divergence angle light source B; the divergence angle light source A or the divergence angle light source B is used for emitting a light source signal to a target tracking device; the driving circuit has two, which respectively controls the divergence angle light source A and the divergence angle light source B to open and close; the modulation monitoring circuit has two, which respectively connects with the corresponding driving circuit, is used for controlling the corresponding driving circuit to open and close, and monitors the voltage, current and power consumption information when the driving circuit works, and feeds back the coding information to the target tracking device. The divergence angle light source B is a laser light source, the emitting angle of which is small, and the energy density is concentrated, so that the target tracking device can receive enough optical signals when the flying device is in the final stage.

The application provides a mechanical boomerang launching device and a use method thereof, and belongs to the technical field of boomerang launching. The launching device comprises a base, a rotating device, a boomerang body adapting device, a power output device and an angle adjusting device. The upper surface of the base is provided with a sliding rail, a descending groove and a buckle, and the lower surface is provided with a plurality of grooves at intervals. The grooves are matched with the angle adjusting device to realize the adjustment of the angle of the base. The rotating device is used to generate an angular velocity of the boomerang before launching. The boomerang body adapting device is used to install and limit the boomerang. The power output device is used to provide a linear velocity. The angle adjusting device is used to adjust the launching elevation angle and realize the accurate setting of the launching elevation angle. The application can significantly improve the rotation success rate, launching stability and safety of the boomerang through the mechanical control of the angular velocity, linear velocity and launching angle, and is suitable for test and competition occasions.

The invention discloses an integrated ground barrier breaking launching device. Comprising a launch box, a launch mechanism mounted on the launch box, an environment monitoring unit arranged on the launch box and used for monitoring environment parameters, a launch condition monitoring unit arranged on the launch box and used for monitoring launch conditions, and a controller arranged on the launch box and connected with the launch mechanism. The electric control system is in communication connection with the environment monitoring unit; in the non-working state, the launching mechanism is contained in the launching box, and in the working state, the electric control system controls the launching mechanism to stretch out of the launching box and adjust the launching mechanism to the designated launching angle. The structure is reliable, the use performance is good, the composite motion of compact storage in the box, unfolding and lifting outside the box and forward stretching of the rocket projectile is achieved, the establishment of a launching preparation posture is efficiently completed, the deployment time is greatly shortened, the rocket projectile is stored in the box body in a full state, and the rocket projectile storage box has the advantages of being high in concealment, low in failure rate and rapid in response.

The utility model provides a linear steel pipeline central axis positioning device which comprises a positioning pipe and a front end positioning plate which are respectively fixed at two ends of a pipeline, the front end positioning plate comprises an annular frame and a positioning plate arranged in the annular frame, the center of the positioning plate is provided with a center hole, the positioning pipe is cylindrical, and the positioning pipe is provided with a through hole. A fixing sleeve is fixedly connected to the interior of the positioning pipe, an annular swing frame is arranged in the fixing sleeve, a laser transmitter is fixed in the annular swing frame, and a first adjusting assembly and a second adjusting assembly which are used for adjusting the transmitting angle of the laser transmitter are arranged on one side of the annular swing frame. The device is simple in structure, can quickly test and position the central axis of the pipeline through laser, and is convenient to operate and good in reliability.

The utility model discloses a variable-angle movable underwater pneumatic launching system capable of being installed outside a box, which comprises an experimental water tank, a movable sealing cabin door is arranged on one side wall of the experimental water tank, a movable guide rail group is arranged in the middle of the inner bottom of the experimental water tank, and a damping system is arranged at one end of the movable guide rail group. One end of the bottom of the movable sealing cabin door is connected with the corresponding position of the movable guide rail group, and the other end of the bottom of the movable sealing cabin door is connected with a detachable external mounting platform; a traction driving system is further installed on one side of the outer portion of the experiment water tank, and a launching unit can walk on the rails of the movable guide rail set through a steel wire rope and a guide pulley set. The system can be used for carrying out underwater launching experiments at different launching angles and different launching speeds, and investigating parameters such as the load, the moving posture, the acceleration and the flow field of the projectile out of water.

The application relates to the field of engineering measurement, in particular to a surveying instrument for construction pipeline arrangement, which comprises a two-way leveling assembly, a pipeline positioning assembly and a height adjusting device. The connecting plate of the two-way leveling assembly is adjusted by at least three adjusting pieces, so that the connecting plate can be kept horizontal. The pipeline positioning assembly is arranged on the connecting plate, can emit light and adjust the light emission angle to simulate the pipeline axis. The height adjusting device is used for adjusting the two-way leveling assembly to a set height. The adjusting piece can be a threaded rod or an electric telescopic rod. The pipeline positioning assembly has a rotating plate and other structures. The rotating plate is provided with a laser emitter and a communication positioning module. A bubble level is arranged on the connecting plate. The application can realize two-way leveling and accurate simulation of the pipeline axis, and effectively assist the construction pipeline arrangement measurement.

Disclosed are a solid-state laser and a solid-state laser system, including a laser emitting module, a reflection module, a coupling module and a transmission fiber arranged sequentially along a direction of an optical path. The laser emitting module includes at least four laser emitting units integrated in a same integrated chamber, and the laser beams emitted by each laser emitting unit are parallel and independent to each other. The reflection module includes a first reflection unit and a second reflection unit arranged sequentially along the direction of the optical path. The coupling module and the second reflection unit are coaxially arranged and configured to adjust the emission angle of the laser beams, and couple at least four laser beams adjusted by the coupling module into the transmission fiber.