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).

The invention discloses an unmanned plane flight direction modifying method, a control method and an unmanned plane, mainly solves the existent problem in the prior art that the modifying method is complicated. The method comprises the following steps: in a direct flight line section, acquiring the position of the unmanned plane for one time in the preset time T; according to the previous obtained unmanned plane position, the current obtained unmanned plane position and the termination point position of the current unmanned plane position located in the direct flight line section, modifying the flight direction of the unmanned plane. The provided unmanned plane flight direction modifying method is capable of, according to the previous obtained unmanned plane position, the current obtained unmanned plane position and the termination point position of the current unmanned plane position located in the direct flight line section, judging the offset situation of the current position and adjusting the flight direction of the unmanned plane. The modification of the flight direction can be realized by itself, and the double-end control is used. The method is simple, the adjustment is efficient, and the accuracy is high.

The invention comprises a system for predicting transmission of an infectious agent via air travel, comprising: a) a database, the database containing air passenger travel data for air travel between origin cities and destination cities, the air passenger travel data including: frequency of flights from origin cities to destination cities, number of passengers traveling from origin cities to destination cities, number of direct non-stop flights from origin cities to destination cities, total passenger traffic for origin and destination cities, and corresponding date stamps for all air passenger travel data; b) a modeling engine operative to map the air passenger travel data with the infectious agent to determine the probability of infection of an individual destination city from an individual origin city via air travel; and c) a reporting engine operative to produce a probability of infection of the individual destination city from the individual origin city at a given time based on said map.

The invention provides a direct flight path predicting method and a direct flight method in an airborne flight management system to solve the technical problem that an existing direct flight method cannot obtain a direct flight predicted path. The predicting method comprises: determining a circle center through a turning radius R and a current flight heading to make an arc and determine a turningend point P, thereby obtaining a direct flight predicted path of the direct flight to a target waypoint; determining a circle center through a turning radius R and a current flight heading to make anarc, and determining a tangent slope of the arc according to the cutoff angle phic to determine a turning end point P, thereby obtaining a direct flight predicted path of the direct flight to a targetcutoff segment. According to the direct flight path predicting method and the direct flight method in the airborne flight management system, a whole direct flight predicted path capable of realizinga direct flight function can be obtained, and the aircraft can be guided to fly along the predicted path based on the obtained direct flight predicted path.

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 discloses a method for extracting the cruise section of a flight path from a three dimensional position sequence of an air craft, including: (1) reading atmospheric pressure height data of the air craft and recording the time of the data; (2) calculating the flight level at which the air craft is located currently; (3) cutting off climbing and descending sequence section in level flight section to obtain the level flight sequence section of the cruise section; (4) reading GPS longitude and latitude data and recording the time of the data; (5) intercepting the GPS longitude and latitude sequence into direct flight sequence section and cutting off turning sequence section to obtain the direct flight sequence section of the cruise section of the air craft; (6) solving an intersection of the level flight sequence section and the direct flight sequence section over time; calculating the difference of atmospheric pressure height data with lower sample rate in the sequence duration of which meets the duration requirement to extract the cruise section of the flight path is extracted. The method realizes analysis and processing on the three dimensional position sequence of the air craft, effectively removes climbing, descending and turning sections and extracts the cruise section of the flight path.

The invention relates to a travel transfer planning method based on airline ticketing. The travel transfer planning method is characterized by comprising the following steps: firstly, selecting an optimal transfer site; then, collecting the travel data of a first travel and a second travel, and selecting superior resources in the travel data; then, enabling the superior resources to correspond to different marketing channels, putting on the market, and returning the price combination of corresponding channels. Thus, after the travel transfer planning method is adopted, a series of problems such as inconvenience in subsequent travels caused by no direct flight, no airplane or relatively early or late takeoff and landing time can be solved, and a diversified traffic combination solution can be provided for customers.

The invention provides an integrated alignment method based on speed trial error estimation of a doppler velocity log on a geographical system under a constant-speed direct flight condition. The projection of a speed trial error of the doppler velocity log on the geographical system is expanded into a state variable, and a doppler velocity log/strapdown inertial navigation integrated alignment system is established on the basis. Compared with a method for only expanding the speed trial error of the doppler velocity log into the state variable, the method provided by the invention can be used for improving the observability level of the speed trial error of the doppler velocity log, effectively estimating the speed trial error and overcoming the influence on precision caused by the speed trial error of the doppler velocity log.

A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.

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.

The invention discloses a tilt rotor unmanned aerial vehicle. The rear end of a front fuselage is detachably connected with the front end of a rear fuselage; the upper side of the front fuselage is detachably connected with a central wing; the two ends of the central wing are rotationally connected with outer wings correspondingly. A driving motor is arranged in the outer wing; propellers are arranged on output shafts of the driving motors, tilting steering engines are arranged in the outer wings, rotating shafts of the tilting steering engines are connected with the central wing through firstswinging assemblies, the tilting steering engines drive the two outer wings to be switched between a horizontal rotating state and a vertical rotating state, and two full-motion horizontal tails arearranged at the end, deviating from the front fuselage, of the rear fuselage; and the rotating shafts of the tilting steering engines are horizontally arranged. The purpose is to solve the problem that in the prior art, a fixed wing flight mode and a rotor wing flight mode cannot coexist on the same unmanned aerial vehicle. The tilt rotor unmanned aerial vehicle has the technical effects that vertical take-off and landing and horizontal high-speed direct flight can be achieved, vertical take-off and landing, rotor wing tilting and modular design are achieved, operation is easy, and reliabilityis remarkably improved.

The invention discloses a method of construction and fault tolerance of front and back flights. The method comprises following steps of step 1, arranging flights in a real-time and orderly manner: according to real-time changing conditions of the flights, carrying out time normalization on the flights with the same flight number according to time zones, actual departure time, estimated departure time and planned departure time, and according to the normalized time, carrying out ascending ranking; step 2, constructing a bidirectional chain table: according to the ordered flight data, firstly filtering all non-stop flights, and sequentially adding the flights into the chain table so as to construct a front and back flight bidirectional chain table in the region communication state between local parts; and step 3, error redundancy of access: searching the front flights according to four conditions: flight numbers, departure places, destinations and departure time. According to the invention, a problem of obstructed flight chain tables caused by errors or missing of related data of flight numbers and time of certain flight data.

The invention provides an airspace configuration method and equipment for cooperative operation of an early warning aircraft and a jammer. The method comprises the steps: obtaining the foremost array position of the early warning aircraft and the straight flight route of the early warning aircraft, and obtaining the self-defense distance of the early warning aircraft according to the straight flight route of the early warning aircraft; obtaining the foremost array position of the jammer and the direct flight route of the jammer, obtaining a distance set between the early warning aircraft and the jammer and a directional angle of the jammer in the direction of the early warning aircraft according to the coordinates of the early warning aircraft and the coordinates of the jammer, and obtaining an angle set between the early warning aircraft and the jammer according to the distance set between the early warning aircraft and the jammer; according to the early warning aircraft self-defense distance, the pointing angle of the jammer in the early warning aircraft direction and the angle set of the early warning aircraft and the jammer, obtaining the maximum self-defense distance set of the early warning aircraft; and performing cooperative operation airspace configuration on the early warning aircraft and the jammer according to the maximum self-defense distance set of the early warning aircraft, the distance set of the early warning aircraft and the jammer, the foremost array position of the jammer and the jammer array position. The array positions of the early warning aircraft and the jammer can be configured.

The invention discloses a real-time route planning method based on a decision tree. The method comprises the following steps: firstly, a low-altitude airspace probability model is established, a three-dimensional continuous space is expressed by using a discrete two-dimensional space, namely, a planning space is expressed as a discrete grid chart with a certain longitude difference and latitude difference, a dangerous area is divided into a no-fly area and a high-risk area, and then the cost value of each node in the model is calculated; secondly, initial route planning is carried out, a direct flight path and a fly-around path are planned for a high-risk area, only the fly-around path is planned for a no-fly area, a route decision tree is generated, and an initial route set is determined; according to the actual situation in flight, the planned route set is selected, and the planning result is updated in real time. Threatening factors such as terrain obstacles and severe weather are comprehensively considered, and the method is safer; the route decision-making tree comprising a plurality of routes is planned in consideration of uncertainty of prior information of a dangerous area, and the method is more practical; and according to the actual situation in flight, the planning result is updated in real time, which is more flexible.

The invention discloses a multielement running information association method suitable for stop-over flight state information abnormality. The method comprises the following steps: according to flightplan, monitoring and real-time data, acquiring flight identification information, flight state information, estimated takeoff/landing time and actual takeoff/landing time; judging whether the currentflight is a non-stop flight; calculating a non-stop flight multielement running state information association judgement threshold; judging whether the current flight is a stop-over flight; calculating a stop-over flight multielement running state information association judgement threshold; judging whether the received monitoring data time has unique flight plan data in the judgement threshold range; if a judgement condition is satisfied, acquiring association information of the flight plan data, the monitoring data and the real-time data, otherwise, recording the flight identification information and the judgement threshold. The method provided by the invention is used for information association under situations where the stop-over flight state information is abnormal and actual takeoff/landing time is missing, and improves accuracy of global flight multielement running state information association.

The invention discloses a method for realizing remote navigation of a large freight unmanned aerial vehicle. The method comprises the following steps of S1, acquiring the route information through theunmanned aerial vehicle; S2, the unmanned aerial vehicle flying in an air route; S3, calculating a distance between the route segment switching lead and a local target waypoint; S4, judging whether the target distance is smaller than the advance or not; S5, judging whether the current waypoint is the last waypoint or not; S6, taking the next waypoint as a target waypoint; S7, judging whether a current state is direct flight or not; S8, processing waypoint feature words; S9, judging whether the processing time is longer than 3s or not; S10, processing waypoint tasks; and S11, judging whether the task is finished or not. The invention relates to the technical field of unmanned aerial vehicles. The method is advantaged in that problems that the whole remote navigation process of the large freight unmanned aerial vehicle generally needs to be controlled by a worker at a ground control station, the ground control station remotely controls the unmanned aerial vehicle according to a navigation display system of the control station, and the unmanned aerial vehicle is not completely autonomously navigated are solved.

The invention discloses an information providing method, system and device based on airline ticket product search and a medium. The method comprises the steps of obtaining a search request of a user for an airline ticket product; retrieving a database based on the search request to obtain a plurality of target flights; screening a preset number of flights from the plurality of target flights as selected flights according to the plurality of flight features, wherein the flight characteristics comprise price characteristics, direct flight transfer characteristics, take-off and landing time, airline companies and time lengths; and displaying a user interface corresponding to the selected flight on the front-end display page, wherein the user interface comprises ticket information corresponding to each selected flight. According to the invention, the interface corresponding to the selected flight is set on the front-end display page, the selected flight screened from the dimensions of themultiple flight features can help the user to select in the homogenized airline ticket product, the page information load is low, invalid browsing of the user can be reduced, and user selection is facilitated.

In order to solve the technical problem that an existing key type airplane airport management system is inconvenient for human-computer interaction, the invention provides a universal airplane airportmanagement system. The system comprises a default normal display list and function modules, wherein the default normal display list comprises a storage airport display list and a specific airport information list; the storage airport display list comprises an airport searching module for a user to search airport information; the function modules comprise an insertion function module, a deletion function module and a direct flight function module. The software process of each function module is specially designed according to touch screen avionics system equipment, compared with a traditionalkey type flight plan management module, man-machine interaction is more convenient, various possible scenes in the aircraft flight process are fully considered during page content and software processlogic design, and universality is good.

The invention discloses a limited airspace unit identification method based on a DBSCAN clustering algorithm. The method comprises the following steps: firstly, defining an airspace unit; secondly, collecting actual flight operation data and corresponding air route information, and matching the air route information with longitude and latitude coordinate data of an airspace unit to construct an air route network model; then, calculating flight delay data, downsampling the data, and associating the data with an airspace unit to obtain flight delay feature data; and finally, constructing an identification model of the limited airspace unit based on a DBSCAN clustering algorithm in combination with the airway network model and the flight delay characteristics. The limited airspace unit and the limited starting and ending time can be identified, and randomness caused by severe weather, air traffic control and other events can be solved. The starting time and the ending time of airspace limitation are determined, direct flight delay and delay caused by propagation can be separated, the propagation mechanism of flight delay is further explored, and the method has important significance in improving the accuracy of flight delay prediction.

The invention provides a general airplane flight plan management system, and aims to solve the technical problem that an existing key type general airplane flight plan management system is inconvenient for man-machine interaction. The system comprises default normal display lists and function modules. The default normal display lists comprise a flight plan waypoint list and a nearby airport list;and the function modules comprise an insertion functional module, a direct flight functional module, a deletion functional module, an activation/cancellation functional module, a route overturning functional module and a route segment translation functional module. The software process of each functional module is specially designed according to touch screen avionics system equipment, compared with a traditional key type flight plan management module, man-machine interaction is more convenient, various possible scenes in the aircraft flight process are fully considered in page content and software process logic design, and the universality is high.