5 results about "Terminal velocity" patented technology

The application relates to an online planning method for a hypersonic variable shape aircraft based on sequence convex optimization and belongs to the field of trajectory planning of a hypersonic variable shape aircraft. The application is realized by the following steps: analyzing the influence of variable shape characteristics on the aerodynamic characteristics of the aircraft, constructing a three-degree-of-freedom dynamics model of the hypersonic variable shape aircraft for trajectory planning; taking the maximum of a weighted function of a terminal height and a terminal speed at the end of a task as a performance index, simultaneously considering initial boundary constraints, terminal boundary constraints and control quantity constraints, combining the aircraft dynamics model to construct an initial trajectory optimization problem of the hypersonic variable shape aircraft; performing convex processing and discretization processing on the trajectory planning problem of the variable length aircraft to obtain a trajectory planning convex problem; constructing a sequence convex optimization solving method based on a variable time domain rolling planning considering multi-stage continuous solving to solve the trajectory planning problem of a gliding section with a terminal time freedom, and realizing online planning of the hypersonic variable shape aircraft according to the solving result.

The application discloses a kind of multi-constraint terminal velocity optimal midcourse guidance methods suitable for long-range glider, including the following steps: launch platform plans the midcourse guidance trajectory of terminal velocity optimization;Launch platform extracts track point from midcourse guidance trajectory, and passes to aircraft;Aircraft generates midcourse guidance instruction according to received track point;According to midcourse guidance instruction, the flight process of aircraft is controlled.The multi-constraint terminal velocity optimal midcourse guidance method suitable for long-range glider provided by the application can meet time, angle and other terminal constraints simultaneously, and ensures that the kinetic energy loss of midcourse guidance section is minimum, and the maximum gliding distance of aircraft is enhanced.

A relative motion control planning method considering terminal velocity constraint comprises the following steps: step one, determining the feasible interval range of control planning transfer time; step two, according to the feasible interval range of control planning transfer time, determining the traversal time interval to obtain the trial point of iterative predictive control planning calculation; step three, according to the obtained trial point, using the method of iterative predictive control planning to traverse all results in the feasible interval range to obtain the terminal state after relative motion control at each trial point; step four, in the series of terminal states obtained in step three, according to the terminal optimization condition, determining one group as the optimal solution. The present application optimizes the optimal control planning position meeting the terminal velocity constraint condition through the iterative predictive comparison in a certain feasible control planning time interval, and calculates the corresponding control planning quantity, which can be applied to various spacecraft on-orbit space rendezvous and docking and other task scenarios.

An intelligent CTU rack and an anti-shake control method and apparatus therefor, and a terminal. The method comprises: acquiring a goods placement instruction for controlling the operation of an intelligent CTU rack, and on the basis of the goods placement instruction, controlling a retractable structure to clamp a rack body, wherein the goods placement instruction comprises an initial velocity, a terminal velocity and the maximum acceleration for the operation of the intelligent CTU rack; processing the initial velocity, the terminal velocity and the maximum acceleration, so as to obtain a velocity curve; and on the basis of the velocity curve, controlling the operation speed and operation time of the extension of a fork in the rack body, so as to obtain a goods release instruction when the fork in the rack body is extended in place. In the method, the retractable structure is first controlled, on the basis of the goods placement instruction, to clamp the rack body, so as to stabilize the rack body of the intelligent CTU rack, and then the operation speed and operation time of the extension of the fork in the rack body are controlled by means of the velocity curve, such that the fork in the rack body is extended in place, and thus impact forces generated during the extension and retraction of the fork in the intelligent CTU rack are both reduced.

The invention provides a proportional guidance method based on a neural network. The method comprises the following steps: for the current moment, acquiring position and attitude information of a target and an aircraft; based on the position and attitude information of the target and the aircraft, respectively using a neural network and a proportional guidance law to generate control quantities; performing weighted summation on the control quantity generated by using the neural network and the proportional guidance law to obtain the control quantity required at the current moment; wherein the weighting coefficient is at least related to the height of the aircraft. Compared with an existing proportional guidance method with angle constraint, the method gives consideration to the ballistic end velocity, planning real-time performance and impact angle satisfaction under the condition of considering high dynamic.