13 results about "Flight level" patented technology

The invention discloses a flight training quality evaluation method based on DTW and K-means clustering, and belongs to the technical field of pilot training, and the method comprises the following steps: S1, data collection and processing; s2, data preprocessing and standard template generation; s3, DTW similarity measurement and mahalanobis distance weighting are carried out; s4, performing similarity measurement and clustering analysis; s5, generating a personalized training scheme; therefore, the invention provides a scientific, objective and efficient flight trainee quality evaluation method, the landing process of the pilot is subjected to comprehensive quantitative analysis in a data-driven manner, a more accurate and personalized flight training scheme is provided, the flight level of the flight trainee is finally improved, and the risk of flight accidents is reduced.

The invention provides a low-altitude traffic operation control method and system based on moving block. The method comprises the following steps: layering an airspace according to aircraft type performance and service types for the vertical take-off and landing aircraft, and distributing corresponding entering and leaving areas according to flight height layers of the aircraft; quasi-moving block is introduced into a low-altitude traffic system, an air route network and operation rules are designed, a free area-buffer area-block area three-level space structure of an aircraft is dynamically constructed according to the state of the aircraft, when the front aircraft occupies a certain block area, the first area in front of the block area is a buffer area, and the second area in front of the block area is a block area. The second zone in front of the blocking zone is a free zone, the aircraft flies in the free zone according to the current speed, and the aircraft is selected for braking in the buffer zone according to the braking distance obtained through calculation. According to the method, the braking curve is generated by dynamically dividing'free area-buffer area-block area 'and combining the braking performance, so that the safety redundancy is increased, and the safety and airspace utilization rate is improved.

The invention provides a busy waypoint traffic capacity simulation evaluation method based on a release interval. The method comprises the following steps: step 1, preprocessing flight track data of a flight; step 2, extracting waypoint operation characteristic parameters; step 3, waypoint traffic capacity evaluation simulation; according to the method, traffic flow distribution conditions of different height layers at waypoints, passing-point flight release time interval distribution, aircraft model hybrid ratio and other characteristic data are counted based on historical data, a waypoint topological structure is combined, a busy flight height layer of a busy waypoint serves as an experimental scene, and the simulation evaluation method is constructed.

The application provides a kind of probability load design method of space vehicle, comprising: step one, collect the historical measured high altitude wind data of single wind field as input, generate quasi-real-time wind correction trajectory according to wind data;Step two, obtain active load shedding control law by using active load shedding control scheme based on acceleration feedback;Step three, carry out six-degree-of-freedom Monte Carlo shooting flight simulation based on quasi-real-time wind correction trajectory, add active load shedding control law in simulation, calculate the static load of each section of space vehicle corresponding to each second point, obtain the axial force, shear force and bending moment load of each station;Step four, map the static load to several space vehicle flight altitude layers, count the load probability distribution under different flight altitudes, and obtain the load envelope of each station along the axial direction of space vehicle under the condition of single wind field. This method realizes multidisciplinary collaborative optimization, reduces design margin while ensuring reliability.

A system and method for calculating a flight plan and a precision release point for an aircraft carrying a payload includes supplying, from a four-dimensional (4D) wind measurement system, 4D wind data indicative of atmospheric wind velocity and direction (i) at and within a first threshold distance around a current flight level of the aircraft, (ii) at and within a second threshold distance around a drop zone for the payload, and (iii) at and within a third threshold distance around a plurality of different altitudes. The 4D wind data is continuously sampled, in a processing system, and is iteratively processes, in the processing system, to calculate, using a release point model implemented in the processing system, a flight plan for the aircraft and a precision release point for the payload.

This invention provides a low-altitude logistics multi-UAV collaborative delivery method based on deep reinforcement learning, comprising: acquiring delivery tasks and multi-level dynamic airspace information, and allocating delivery tasks to idle UAVs according to a task allocation mechanism; constructing an airspace scheduling mechanism based on the multi-level dynamic airspace information, wherein the airspace scheduling mechanism includes an airspace scheduling altitude layer selector and a multi-UAV collaborative pathfinding solver; the airspace scheduling altitude layer selector determines the flight altitude layer of the UAVs according to the delivery tasks and multi-level dynamic airspace information, obtaining altitude layer decisions; the multi-UAV collaborative pathfinding solver performs horizontal range collaborative path planning at each altitude layer, obtaining path decisions; and the UAVs execute delivery tasks according to the altitude layer decisions and path decisions. This invention's method achieves high throughput and low latency delivery goals in complex urban scenarios and reduces operational risks caused by airspace conflicts.

The present invention provides a method and system for evaluating a pilot's flight performance based on flight parameter data. The present invention includes: obtaining the flight parameters of a pilot and parsing the flight parameters into flight data; analyzing according to the flight performance envelope data of the aircraft driven by the pilot and the specified manipulation data characteristic rules to determine that the flight data is within the flight envelope data; establishing a standard matrix according to the flight performance envelope data; performing interval interpolation on the flight data and curve-fitting the standard matrix for data boundary analysis; evaluating the pilot's flight level according to the results of the data boundary analysis and the flight data based on the performance evaluation criteria. The present invention solves the technical problem in the prior art that it is impossible to comprehensively evaluate, by means of informatization means, the passing criteria such as the training subjects, flight sorties, comprehensive technical level and mission execution ability of a pilot.

The present application relates to a thrust control system in an FLCH mode, comprising: an upper branch comprising: a height difference calculation module configured to calculate a height difference between a target height and a current height of an aircraft; the latching module is configured to be used for latching the numerical value of the height difference according to the manual operation response time delay and the industry requirement; the vertical speed calculator is configured to be used for calculating a corresponding expected vertical speed according to the latched height difference output by the latch module; a thrust calculator configured to calculate a corresponding thrust from the desired vertical velocity; the lower branch comprises a selector which is configured to be used for selecting an integration rate according to an integration rate judgment condition; an integrator configured to perform integration by time according to the selected integration rate to output a compensation thrust; and an adder configured to add the thrust from the upper branch and the compensation thrust from the lower branch to output a thrust command.

A control method for a flight level change mode, and an automatic flight system. The control method comprises: on the basis of a signal acquired from engines regarding whether the engines operate in a dual-engine mode or a single-engine mode, selectively setting respective different vertical speed thresholds during climb and descent processes in a flight level change mode.

The present invention discloses a method for strategic trajectory conflict management in free-route airspace. The method comprises the following steps: S1, based on the weather forecast provided by the ensemble forecast system, performing ensemble trajectory prediction taking into account the time-varying nature of meteorological elements; S2, using a conflict detection method based on a four-dimensional grid to measure the conflict risk between trajectory points; S3, using the rerouting waypoints selected by each flight and the altitude and Mach number at each waypoint as decision variables, minimizing the total conflict risk of all trajectories, the total deviation of all flights from the user's preferred trajectory, and the total unpredictability of all flights as the objective function, and using flight altitude constraints, Mach number constraints, and restricted area constraints as constraints to construct a strategic conflict management model; S4, optimizing the constructed strategic conflict management model, and adjusting the trajectory using the obtained optimized trajectory. The present invention can provide a solution with high robustness and coordination with the needs of all parties for trajectory conflict management in the strategic stage.

A control method for a pitch axis in a flight level change (FLCH) mode of an aircraft, the method comprising: generating a target vertical control signal based at least in part on an energy state integrated control, wherein the energy state comprehensive control deduces a potential track angle by calculating the sum of kinetic energy and potential energy of an aircraft in real time; selecting an amplitude limiting strategy according to the current state of the FLCH mode; and performing dynamic amplitude limiting processing on the target vertical control signal according to the amplitude limiting strategy. The invention further discloses a flight control system which comprises a processor and a sensor for executing the control method, and numerous other aspects.

The invention discloses an autonomous operation flight plan rapid generation method. The method comprises the following steps: firstly, based on airport, waypoint and route topological data, taking a great circle distance as a weight, and constructing an undirected weighted route network diagram; secondly, adopting a self-adaptive optimal search algorithm, generating an initial path through a Dijkstra algorithm, and generating an efficient and reasonable flight path in combination with redundant waypoint removal and course anomaly detection; then, based on the take-off time, the flight segment distance, the flight speed and the course angle, the estimated time of passing through (ETA) of each waypoint is calculated, and a flight height layer is distributed to each waypoint through a dynamic height layer distribution strategy; and finally, integrating the waypoint sequence, the ETA and the altitude layer information to generate a structured flight plan, and carrying out feasibility verification. According to the method, the efficiency and autonomy of flight plan generation are remarkably improved, the path smoothness and the rationality of height distribution are optimized, and key technical support is provided for autonomous, collaborative and efficient operation of an air traffic management system.

This invention provides a method and system for low-altitude traffic operation control based on moving block. The method includes: stratifying airspace according to aircraft type and service type for vertical takeoff and landing (VTOL) aircraft; allocating corresponding approach and departure areas based on the aircraft's flight altitude layer; introducing quasi-moving block into the low-altitude traffic system; designing the airway network and operational rules; and dynamically constructing a three-level spatial structure of free zone – buffer zone – block zone based on the aircraft's status. When an aircraft occupies a block zone, the first zone before that block zone becomes the buffer zone, and the second zone before that block zone becomes the free zone. The aircraft flies at its current speed in the free zone and brakes at the appropriate time in the buffer zone based on the calculated braking distance. This invention increases safety redundancy and improves safety and airspace utilization by dynamically dividing the "free zone – buffer zone – block zone" and generating braking curves based on braking performance.