11results about How to "Improve guidance accuracy" patented technology

The invention belongs to the field of aircraft control, and discloses a composite guidance aircraft guidance control method and system considering flight time falling angle constraint, and the method comprises the steps: inputting target values of flight time and a terminal falling angle according to a specific task requirement; pre-planning a flight path; in the flight process, estimating the current remaining flight time of reaching the target in real time, and performing feedback adjustment on the flight time error; in a flight approaching target stage, calculating a falling angle error in real time according to the attitude and speed of the aircraft, and correcting the flight attitude; through a nonlinear optimal control algorithm, two constraints of flight time and a falling angle are comprehensively balanced; executing mechanisms such as engine thrust, control surface angle and attitude control spray pipes of the aircraft are adjusted in real time according to a composite guidance algorithm instruction; and when the aircraft is about to arrive at the target, final falling angle correction is performed to ensure that the aircraft hits the target at an accurate angle. According to the method, the balance problem between the flight time constraint and the falling angle constraint is effectively solved, and the guidance precision and the task success rate of the aircraft are remarkably improved.

The invention discloses a space-time four-dimensional coordinated guidance method for a dive section of an unpowered high-speed aircraft. The space-time four-dimensional coordinated guidance method comprises the specific steps that S1, a guidance model for dive terminal time and angle control of the aircraft is constructed; s2, diving optimal guidance meeting angle and position constraints; s3, two-stage diving space-time coordination guidance meeting the time constraint is carried out; and S4, carrying out online robustness compensation on the environment and ontology deviation. According to the method, the contradiction between time and space control in a traditional method is solved; the robustness is enhanced by means of a kinetic equation reverse solution technology, and real-time deviation estimation and compensation are achieved; meanwhile, the time control precision is improved by utilizing a two-stage switching logic and numerical integration optimization method based on terminal time prediction; according to the method, the flexibility and adaptability of guidance are improved, the robustness of the system is enhanced, and the strike precision and the overall performance of the aircraft when the aircraft executes complex tasks are remarkably improved.

The invention provides a dialysis displacement liquid preparation guiding method and system for a user, and the method comprises the steps: obtaining the dialyzer information of a dialyzer and the current blood gas detection result of the user, and recognizing the current blood state information and the current blood ion concentration value of the user; on the basis of the dialyzer information, filter permeation information of a dialyzer is recognized, and on the basis of the current blood state information, the displacement liquid ion dispersion speed corresponding to the user is recognized; based on the current blood ion concentration value of the user and preset dialysis replacement liquid information, the initial dialysis replacement liquid ion concentration demand quantity of the user is calculated, and based on the initial dialysis replacement liquid ion concentration demand quantity, the filter permeability information of the dialyzer and the replacement liquid ion dispersion speed corresponding to the user, the dialysis replacement liquid ion dispersion speed is predicted through a replacement liquid prediction model. Predicting an actual dialysis displacement liquid ion concentration demand range required by a user; and taking the actual dialysis replacement liquid ion concentration demand range as the replacement liquid ion concentration configuration guide information of the user. By adopting the scheme, the accuracy of the actually prepared dialysis replacement liquid can be improved.

The application discloses a visual-based contact type measuring robot adaptive measuring point relative guiding method, which comprises a 2D visual-based product image contour matching method, realizes 4-degree-of-freedom measuring point guiding of plane translation, rotation and height scaling, and is suitable for contact type six-axis cooperative measuring robot measuring point guiding measurement of products with local features; the method comprises the following steps: teaching contact type six-axis cooperative measuring robot measuring points of a product to be measured; determining a teaching 2D measuring pose, obtaining a product multi-scale contour image template under the teaching 2D measuring pose and a multi-scale image of the current product, and performing contour matching of corresponding scale levels; based on the contour matching result, calculating a first pose deviation under the teaching 2D measuring pose, transforming the first pose deviation to all teaching point positions of the teaching 2D, performing pose transformation, performing iterative updating on all measuring point positions, and obtaining all updated first measuring point poses. The application better realizes adaptive contact type measuring point measurement of products.

The application provides an improved closed-loop guidance method suitable for a reusable rocket, and relates to the technical field of rocket recovery guidance. The method comprises the following steps: determining the velocity and position in the launch inertial system at the engine shutdown time of the power deceleration stage according to the initial value of the remaining flight time of the active stage, the real-time gravity acceleration and the initial value of the program angle of the power deceleration stage; determining the absolute longitude difference between the position in the launch inertial system at the engine shutdown time of the power deceleration stage and the target point; determining the remaining flight time of the passive stage; and determining the required velocity and program angle calculation value of the closed-loop guidance. According to the application, the calculation method of predicting the state of the shutdown point can be used to calculate the required velocity, the program angle change rate of the power deceleration stage is reduced, the control effect is optimized, and the stability is improved. Moreover, the calculated required velocity can reach the position constraint and velocity direction constraint of the passive stage end point after the rocket is shut down, the structure is simple, the operation efficiency is high, and the method is convenient to run on different hardware.

The invention discloses a repeatable fuze type precise guidance assembly and system and a use method, and belongs to the technical field of communication guidance and flight control. The assembly mainly comprises a shell, a radio frequency antenna, a satellite antenna, a missile-borne controller, a rudder system, a fairing, a folding rotor wing, an explosive rope, an explosive bolt, a compression spring, a slewing bearing type speed reducer, a battery, a rotating disc and a motor. Wherein the radio frequency antenna and the rudder system are both installed on the shell, the satellite antenna is installed on the wall face of the shell, the missile-borne controller and the battery are installed in the shell, the inner ring of the slewing bearing type speed reducer is connected with the battery, and the outer ring of the slewing bearing type speed reducer is connected with the rotating disc; the folding rotor wings are fixed on the turntable, an output shaft of the motor is connected with the turntable, and the compression spring is fixed at the lower end of the motor. The mode that an original fuse is not replaced and a fixed rotor wing is additionally arranged is adopted, and the problems of storage, destruction, maintenance and repeated use of the original fuse are solved.

The present invention discloses a two-stage prediction and correction guidance method and system for entering the Martian atmosphere. The method includes: establishing a dynamic model of a probe for entering the Martian atmosphere; dividing the Martian atmosphere entry stage into an initial entry stage and a later entry stage, and adopting different guidance strategies according to the characteristics of different stages; in the initial entry stage, the probe flies at a constant roll angle without on-orbit guidance and roll angle adjustment; in the later entry stage, combined with the dynamic model, periodic longitudinal guidance and lateral guidance are implemented, the longitudinal guidance instruction is adjusted according to the error between the predicted longitudinal range and the predicted longitudinal range, and whether to adjust the roll angle sign is determined according to the lateral range error. The present invention does not require an additional roll angle model for specific scenarios. In the first stage, the probe flies at a constant roll angle to adapt to the low atmospheric density and hypersonic characteristics of entering the Martian atmosphere; in the second stage, the probe flies at a fixed roll angle, gradually adjusts the entry trajectory, and improves the guidance accuracy.

The utility model discloses a kind of gauze harness frame structures of sheet shuttle loom, including upper beam and lower beam, the both ends of upper beam and lower beam are symmetrically bolted and connected with side frame, to increase the end surface connecting strength of upper beam and lower beam, the opposite surface of upper beam and lower beam is symmetrically bolted and connected with reinforcing rod and is close to middle part position, to cooperate side frame to further strengthen the strength between upper beam and lower beam, the opposite surface of upper beam and lower beam is all provided with threading-in rod, to realize the weaving of machine line.The utility model is reinforced by double reinforcement design of side frame and reinforcing rod, cooperates and connects T block, strengthens the composite connection structure of block and connecting pin shaft, greatly improves the connecting strength and structural stability of harness frame overall frame, effectively resist vibration and tension in weaving process, avoid frame deformation, prolong the service life of harness frame.

The invention provides an intestinal tract cleaning guiding method and system, and the method comprises the steps: obtaining the intestinal tract cleaning preparation information and intestinal tract cleaning record information of a patient, and recognizing the excretion frequency and excrement images of the patient based on the intestinal tract cleaning record information; identifying the preparation adaptation degree of the patient and the excretion degree of the patient corresponding to the excretion state of each excretion picture; based on the excretion degree of the patient corresponding to the excretion state of each excretion picture, predicting a predicted cleaning completion time point of the patient through an excretion prediction strategy, and when the predicted cleaning completion time point exceeds a preset time point threshold value, generating intestinal tract cleaning guide information of the patient; and replacing the new intestinal tract cleaning preparation information with the intestinal tract cleaning preparation information, and returning to execute the steps until the predicted cleaning completion time point does not exceed a preset time point threshold value, and completing the intestinal tract cleaning guidance task. By adopting the scheme, the guiding accuracy of the intestinal tract cleaning process can be improved.

The utility model relates to the field of offshore photovoltaic technologies, in particular to an offshore photovoltaic pile foundation guide frame and an offshore photovoltaic piling device. The guide frame comprises a polygonal frame, the number of edges of the polygonal frame is used for being matched with the number of single-set offshore photovoltaic pile foundations, the shape of the polygonal frame is used for being matched with the shape of connecting lines of the single-set offshore photovoltaic pile foundations, and guide cylinders are arranged at the included angles of the polygonal frame. An inner hole of the guide cylinder is used for being matched with the outer diameter of a pile foundation, and a fixing structure is further arranged on the polygonal frame and used for being connected with the polygonal frame and a pile driving barge. The polygonal frame is used for positioning the piling positions of the pile foundations of a single set of offshore photovoltaic devices, the guide cylinders can be used for pressing, positioning and guiding the pile foundations, the piling stability and accuracy are improved, meanwhile, the perpendicularity of the pile foundations is guaranteed, the construction positioning precision of each pile foundation of each set of offshore photovoltaic devices is guaranteed, and the engineering quality is guaranteed.

The present invention discloses a high-precision auxiliary installation tool and installation method for an aircraft engine turbine support. The installation tool is mainly composed of a support, a precision guide pin, a guide pin and a limit pin. The support is an inverted triangle-arc structure, and the precision guide pin and the guide pin correspond to the precision hole and the ordinary hole on the turbine support respectively. During installation, the support of the high-precision auxiliary installation tool is evenly installed on the rear installation edge of the low-pressure turbine guide on the main engine, and the guide pin is inserted into the support to guide the ordinary hole on the turbine support; then the precision guide pin is inserted from top to bottom to guide the precision hole on the turbine support, and then the limit pin is inserted into the support to lock the precision guide pin and the guide pin; after completing the installation of the tool, the turbine support is vertically hoisted by a crane. The present invention has the characteristics of precise guidance, which improves the assembly efficiency and quality of the engine.