41 results about "Direct flight" patented technology

A method and system for making roundtrip air flight reservations includes an end-user receiving a response having departure dates with a lowest cost outbound fare for each date and return dates with a lowest cost inbound fare for each date, outbound flight and inbound flight segments each priced with One Way Combinable fares, the One Way Combinable fares can be priced independently of all other One Way Combinable fares (i.e. restriction on covered segment, fare amount can be doubled to price the Round Trip) and can be combined together with any other One Way Combinable fare (i.e. no combinability restriction) in order to form a guaranteed pricing solution regarding IATA regulation both in domestic and international contexts for complex segments (i.e. based on non-direct flights).

A device includes a database including data related to obstacles, a first determination module for determining at least one obstacle intercepted by a direct flight path connecting an initial point to the target point, a second determination module for determining at least one lateral extreme apex of at least one intercepted obstacle, an evaluation module for assigning a rating to each section corresponding to a segment between a lateral extreme apex and the initial point, a storage module for storing in a memory the section corresponding to the optimum extreme apex having the best rating, the optimum flight path corresponding to all of the sections stored in the memory, the preceding modules being used iteratively, the device further including a transmission module for transmitting the optimum flight path to a user device.

The invention provides a method for simulating the flight process of an aircraft and belongs to the field of general aviation for air traffic management. The method for simulating the flight process of the aircraft specifically comprises the steps that the flight process of the aircraft is divided into four stages firstly, wherein the four stages are a departure stage, an airway stage, a marching-in stage and an approaching stage; all passing points of each stage are obtained, an extrapolation algorithm of each passing point is selected to be a direct flight extrapolation algorithm or a turning extrapolation algorithm according to the characteristics of each stage; real-time flight information of the aircraft is obtained once at the position of each passing point of each stage; extrapolation is carried out according to the selected extrapolation algorithm to obtain the flight attitude of the aircraft at each stage according to the flight information; whether the aircraft reaches a passing point is judged each time when the extrapolation is finished, and the extrapolation algorithm is changed if the aircraft reaches a next passing point; the flight attitudes of the aircraft at the four stages are combined to obtain the flight attitudes of the aircraft in the whole flight process. The method is suitable for being used for simulating the whole flight process of the aircraft.

A multivariate operation information association method suitable for abnormal state information of connecting flights. It includes obtaining flight identification information, flight status information, estimated takeoff / landing time, actual takeoff / landing time based on flight plan, monitoring, and real-time data; judging whether the current flight is a direct flight; calculating the multivariate operation status information association of direct flights Judgment threshold; determine whether the current flight is a connecting flight; calculate the judgment threshold associated with multiple operating status information of the connecting flight; judge whether there is a unique flight plan data within the judgment threshold range at the time of receiving monitoring data; obtain the flight plan data if the judgment condition is met , surveillance data, real-time data associated information, otherwise record flight identification information and judgment threshold. The method of the invention is applicable to the information association when the state information of the connecting flight is abnormal and the actual take-off / landing time is missing, and improves the accuracy of the information association of multiple operating states of global flights.

The invention discloses a quick estimation method for gyro errors in a ship-borne master / sub inertial navigation transfer alignment process, and catering to transfer alignment of ship master / sub combinations, designs a quick estimation method for the gyro errors, which is suitable for mooring / constant-speed direct flight conditions and is used for quickly estimating constant errors of sub inertial navigation gyros. Under the support of a real-time multiple task operating system, a sub inertial navigation system implements the circular navigation resolving and the information fusing for one group of data; and the high-speed performance of a computer is fully used to quickly finish the estimation of the gyro constant errors in the transfer alignment process. The method dose not change the existing algorithm of navigation resolving, dose not change the filter structure and the information matching mode in the transfer alignment information fusing algorithm, fully uses the redundant resources of the existing navigation computer, and quickens the gyro error estimation speed in the transfer alignment process.

In order to solve the technical problem that the existing direct flight method cannot obtain the predicted flight path of the direct flight, the present invention provides a direct flight path prediction method and a direct flight method in an airborne flight management system. Determine the center of the circle by the turning radius R and the current flight heading, and then make an arc and determine the turning end point P, so as to obtain the predicted flight path of the direct flight to the target waypoint; the turning radius R and the current flight heading determine the center of the circle, and then draw a circle arc, and according to the truncated course angle φ c The tangent slope of the arc is determined, and then the turning end point P is determined, so as to obtain the predicted flight path of the direct flight to the intercepted flight segment of the target. The present invention can obtain the entire predicted direct flight track for realizing the direct flight function, and based on the acquired direct flight predicted track, can guide the aircraft to fly along the predicted track.

The invention provides a flapping wing aircraft capable of realizing twisting of inner wings. The flapping wing aircraft comprises a rack, wings, rear drive devices and front drive devices. The rack has mounting positions. The wings are symmetrically arranged on the both sides of the rack. The wing on each side comprises an inner wing main flapping rod and an inner wing auxiliary flapping rod. The inner wing main flapping rods generate lift required during the flapping wing flight process. The inner wing auxiliary flapping rods generate lift and thrust required during the flapping wing flight process. The front drive devices are mounted in the mounting positions of the rack at the front and used for driving the inner wing main flapping rods. The rear drive devices are mounted in the mounting positions of the rack at the rear and used for driving the inner wing auxiliary flapping rods. The inner wing main flapping rods and the inner wing auxiliary flapping rods on the both sides of the rack have phase differences. The flapping wing aircraft has the advantages that the design of front and rear inner wing flapping mechanisms having the phase differences is provided, the flapping wing motions which are in accordance with the flapping wing flight principle are conducted, and the takeoff, direct flight and landing functions can be fulfilled when the left and right wings are synchronized; and when differential motions are conducted, the functions such as pitching, yawing and steering under the asynchronous control of frequencies and amplitudes of the left and right flapping wings can be fulfilled.

The invention provides an airspace configuration method and equipment for cooperative operation of an early warning aircraft and a jamming aircraft, comprising: obtaining the front position of the early warning aircraft and the direct flight route of the early warning aircraft, obtaining the self-defense distance of the early warning aircraft according to the direct flight route of the early warning aircraft; obtaining the front position of the jamming aircraft and the interference According to the coordinates of the AWACS and the jammer, the distance set between the AWACS and the jammer and the pointing angle of the jammer in the direction of the AWACS are obtained, and the angle set between the AWACS and the jammer is obtained according to the distance set between the AWACS and the jammer; The self-defense distance of the early warning aircraft, the pointing angle of the jammer in the direction of the early warning aircraft and the angle of the early warning aircraft and the jammer are combined to obtain the maximum self-defense distance set of the early warning aircraft; and jammer array positions, and carry out collaborative airspace configuration for early warning aircraft and jammers. The present invention can configure the positions of the early warning aircraft and the jamming aircraft.