14 results about "Rolling angle" patented technology

This invention provides a high-dynamic space-based cooperative guidance method and system for multi-level virtual target points, relating to the field of aircraft control technology. It involves acquiring initial flight state data of each aircraft and position data of the target point; generating at least one virtual target point based on the initial flight state data and position data, using a zero heading angle constraint; generating roll angle control command data for each aircraft based on the initial flight state data and the virtual target point, using a two-sided azimuth error corridor; and adjusting the attitude of each aircraft according to the roll angle control command data to ensure that each aircraft meets the terminal heading angle constraint and reaches the target point. This method enables precise control of the terminal heading angle of high-dynamic aircraft in complex dynamic environments, thereby enabling multiple aircraft to perform cooperative strike missions from different spatial orientations.

This invention relates to a 4D millimeter-wave radar roll angle calibration system. A roll angle calibration value is configured by placing left and right corner reflectors on the upper and lower sides of an assumed horizontal plane of the millimeter-wave radar, respectively. Then, a host computer triggers a calibration program. Upon receiving a command, a slave computer controls the millimeter-wave radar to send test signals to the left and right corner reflectors, thereby detecting their position information. Based on the position information of the left and right corner reflectors, the roll angle measurement value of the millimeter-wave radar can be further calculated. Finally, the roll angle calibration value and the roll angle measurement value are used to calibrate the roll angle of the millimeter-wave radar. This application demonstrates that the host computer controls the radar to automatically complete the roll angle calibration function and derives a method for calculating the radar roll angle based on the angular position information measured by the radar.

This invention provides a method for automatically leveling and attitude measurement of a three-degree-of-freedom support system in a low-speed wind tunnel. The method includes: installing a dual-axis accelerometer on the support system's strut, such that its first sensitive axis is parallel to the pitch axis of the aircraft model and its second sensitive axis is parallel to the roll axis of the model; controlling the roll motor and angle-of-attack motor of the support system so that the output values ​​of both the first and second sensitive axes are zero, thus achieving automatic leveling of the model; during wind tunnel testing, comparing the roll angle measured by a first encoder (detecting the roll angle) and the angle of attack measured by a second encoder (detecting the angle of attack), using a first threshold and a second threshold, selecting the roll angle detected by the first sensitive axis or the measurement value of the first encoder as the actual roll angle of the model, and selecting the angle of attack detected by the second sensitive axis or the measurement value of the second encoder as the actual angle of attack of the model, thereby improving the measurement accuracy of the aircraft model's attitude angle during wind tunnel dynamic testing.

The application discloses a method for calibrating a roll angle of an emergency anti-solar time of a satellite on the earth, which is beneficial to reestablishing a three-axis attitude of the satellite on the earth. Firstly, an angle between a projection of a sun vector on an orbit plane and an orbit system-X axis is calculated; then, whether a current orbit position meets a requirement is determined according to the angle between the projection of the sun vector on the orbit plane and the orbit system-X axis, and whether an absolute attitude reference is available at present is determined, if the current orbit position meets the requirement and the absolute attitude reference is available at present, the roll angle is calibrated at a current control beat; otherwise, the roll angle is not calibrated at the current control beat; if the roll angle is calibrated at the current control beat, the roll angle is calculated based on the absolute attitude reference; if the roll angle is not calibrated at the current control beat, the roll angle is calculated by using gyro inertia angular velocity integration. The application can provide high-precision and reliable attitude information for reestablishing the attitude of the satellite on the earth.

This invention discloses an intelligent control method and system for the roll angle of a nozzle in one-button de-icing of a de-icing truck. The control method comprises the following steps: S1, acquiring the relative distance between the distance sensors on both sides of the nozzle and the wing; S2, calculating the difference θ between the nozzle roll angle and the wing's dihedral angle using a geometric method; S3, the controller, based on the angle difference, controls the rotation direction and pulse number of the motor adjusting the nozzle roll angle; S4, identifying the wing's dihedral angle δ; S5, anti-collision control, controlling the relative distance between the nozzle and the wing to prevent collisions. This invention solves the shortcomings of one-button wing de-icing technology in steam jet de-icing trucks, greatly improving the efficiency and safety of steam jet de-icing of wing ice.

The application provides a hull inclination angle measurement method, device, equipment and product, comprising: arranging three ranging modules on the hull which are not in the same straight line; determining the distance value between two different ranging modules based on the known arrangement positions of the three ranging modules on the hull; determining the original side length of the original triangle formed by the arrangement positions of the three ranging modules according to the distance value; determining the height difference value between two different ranging modules based on the current ranging value of the three ranging modules; determining the projection side length of the projection triangle projected onto the static water surface from the original triangle according to the distance value and the height difference value; determining the side length contraction value and the angle deviation value according to the original side length and the projection side length; establishing the binary equation set about the roll angle and the pitch angle of the hull based on the side length contraction value and the angle deviation value; and solving the binary equation set to obtain the roll angle and the pitch angle of the hull.

This disclosure relates to a method and system for localizer tracking control. A method for localizer tracking control includes: calculating a reference roll angle command based on the aircraft's track angle deviation relative to the runway and its sideslip distance to the runway centerline; calculating a longitudinal overload compensation command for the aircraft's roll angle based on the aircraft's heading angle, track angle, pitch angle, and longitudinal overload; adding the reference roll angle command to the longitudinal overload compensation command to obtain a final roll angle command; and using the final roll angle command as a target roll angle command in a localizer approach mode to perform localizer tracking control.

A movable platform and a control method and apparatus therefor, a control device, and a storage medium. The method comprises: acquiring control parameters inputted by a user, the control parameters comprising a moving distance of a movable platform and a roll angle set corresponding to an attitude adjustable mechanism of the movable platform, wherein the roll angle set comprises an initial roll angle and a final roll angle, or the control parameters comprising a moving speed of a movable platform and a roll angle set corresponding to an attitude adjustable mechanism, wherein the moving speed is used for determining a moving distance of the movable platform (S101); and on the basis of the control parameters, controlling the movable platform to move according to the moving distance, and controlling the attitude adjustable mechanism to rotate according to a rotation interval indicated by the initial roll angle and the final roll angle, wherein the movable platform comprises an aircraft, the moving distance comprises a flight distance, and the moving speed comprises a flight speed (S102).

This invention relates to an apparatus for determining a control protocol for controlling a C-arm system including a radiation source. The control protocol includes a sequence of roll angles and a sequence of propeller angles. The apparatus includes: a tilt plane providing unit for providing a tilt plane tilted relative to a vertical plane; and a control protocol determining unit for determining the control protocol by determining the sequence of roll angles and the sequence of propeller angles, such that the radiation source follows a trajectory including a circular component in the tilt plane and allowing the C-arm system to acquire projection data for image reconstruction. The apparatus allows for the acquisition of computational images, such as tomographic images, with improved quality and reduces radiation in radiation-sensitive areas.

The application discloses a method for solving a target roll angle based on linear vector space reconstruction, which comprises the following steps: selecting a characteristic linear vector under a target body coordinate system to form a characteristic plane representing the change of the roll angle before and after rolling, reconstructing the selected linear vector in space, and then reconstructing the characteristic plane; and solving a rotation matrix before rolling by using the roll-off characteristic of a central axis vector, then solving the state of the characteristic plane before rolling, and directly representing the normal line angle between the characteristic planes before and after rolling as the change of the roll angle. The roll angle is converted into a dihedral angle between the planes before and after rolling, the roll information is completely decoupled from the pitch and yaw information, and the method is suitable for non-contact roll angle transient measurement under a dynamic visual angle.

Systems and methods are provided for detecting and warning of aircraft rollover conditions. The systems include one or more sensors onboard the aircraft and a controller onboard the aircraft that is in operable communication with the one or more sensors. The controller is configured to, by one or more processors: receive input data from the one or more sensors and, optionally, one or more other sources, process the input data to dynamically determine a roll angle of the aircraft, an angular roll rate of the aircraft, and a critical rollover angle of the aircraft, determine whether current or potential static or dynamic rollover conditions of the aircraft exist based, at least in part, on the roll angle, the angular roll rate, and the critical rollover angle, and generate an alert in response to determining that the current or potential static or dynamic rollover conditions exist.

This application provides an aerial alignment method, apparatus, device, and medium for an aircraft, relating to the field of aircraft alignment technology. The method includes: acquiring inertial measurement data and velocity of the aircraft during its flight phase; inputting the inertial measurement data and velocity into a pre-trained roll angle error prediction model to obtain the roll angle error corresponding to the inertial measurement data; performing phase calculation on the inertial measurement data to obtain the aircraft roll angle; and calibrating the aircraft roll angle using the roll angle error to obtain the target aircraft roll angle, thereby completing the aerial alignment. This application, by real-time acquisition of inertial measurement data and velocity data during the flight phase, combined with a pre-trained roll angle error prediction model to accurately output error values, and then obtaining a high-precision target roll angle through phase calculation and error calibration, effectively overcomes the alignment bottleneck of traditional methods in high-rotation, low-weightless environments, significantly improving the real-time performance and accuracy of aerial alignment.