74 results about "Flight level" patented technology

The present invention is directed to a traffic display for an aircraft, which includes a vertical traffic indicator. The vertical traffic indicator includes flight levels, depicted utilizing differing visual patterns to represent the current flight level as well as available and unavailable flight levels for transit. The vertical traffic indicator includes aircraft indicators positioned in relation to flight levels to indicate attitude. The aircraft indicators may also include status indicators indicating separation standards, vertical trend, intent, or whether an aircraft is a reference aircraft for an ITP. The traffic display provides clear and intuitive means of understanding the flying environment related to the performance of the ITP, increasing situational awareness and simplifying the ITP. The traffic display is specifically advantageous for performance of an ITP, but may be integrated with displays including terrain, weather, flight plan waypoints, or TCAS (Traffic Collision Avoidance System) traffic.

Systems and methods are disclosed for generating a digital flight path within complex mission boundaries. In particular, in one or more embodiments, systems and methods generate flight legs that traverse a target site within mission boundaries. Moreover, one or more embodiments include systems and methods that utilize linking algorithms to connect the generated flight legs into a flight path. Moreover, one or more embodiments include systems and methods that generate a mission plan based on the flight path. In one or more embodiments, the generated mission plan enables a UAV to traverse a flight area within mission boundaries and capture aerial images with regard to the target site. Furthermore, in one or more embodiments, systems and methods capture digital aerial images of vertical surfaces of a structure by generating a reference surface and flight legs corresponding to the reference surface.

Provided are methods and systems for the automatic calculation and presentation of data on a display device alerting a pilot that a change in flight plan is desirable, possible and administratively compliant under air traffic control protocol. The methods and systems may automatically request the flight clearance over a data link or the pilot may override the data link.

An avionic system and ground station for aircraft out of route management and alarm communications composed of an avionic device, which is fitted onboard the aircraft, with a memory unit for storing the flight paths data, runways, orography, and obstacles; processors to compute the stored or received data, available from sensors monitoring the onboard situation. Processors will compute commands to be sent to the aircraft's autopilot to temporarily take over the aircraft control and return it to pre-set flight levels or spatial positions; communication devices suitable for transmitting the real time onboard situation to ground control stations when potentially dangerous events occur.

Embodiments of a flight deck display system for deployment onboard a host aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display, a wireless communication module, and a controller operatively coupled to the cockpit display and to the wireless communication module. The controller is configured to generate a vertical In-Trail Procedure (ITP) window on the cockpit display, which includes graphics representative of the current position of the host aircraft, the current position of an intruder aircraft when present within a predetermined distance of the host aircraft, and a plurality of flight levels. The controller is further configured to receive data from which the current flight path of the intruder aircraft can be derived; and periodically update the vertical ITP window to include flight path symbology indicative of the current flight path of the intruder aircraft.

This device providing assistance to aircraft crew for a flight level change of the aircraft in air traffic, comprising means for viewing the position of the aircraft in the vertical plane, is wherein the viewing means comprise: display means capable of displaying an image comprising at least one zone corresponding to a target altitude (FL) for the aircraft, and in that it comprises: selection means for selecting said zone in the image.

The invention is suitable for the technical field of unmanned aerial vehicles, and provides an unmanned aerial vehicle management and control method and an unmanned aerial vehicle management platform. The method comprises the steps that the flight level of an unmanned aerial vehicle is set; and the unmanned aerial vehicle is managed and controlled according to the flight level. Hierarchical management and control of the unmanned aerial vehicle are realized, flight authority of the unmanned aerial vehicle can be opened to the owner of the unmanned aerial vehicle to the largest extent under the condition of guaranteeing flight safety of the unmanned aerial vehicle, and flight safety of the unmanned aerial vehicle is enhanced so that sound development of the unmanned aerial vehicle industry is facilitated.

Systems and methods for improving situational awareness on an in-trail procedures display. The present invention provides a display with visual identification and indication for aircraft that do not meet the ITP criteria. In the in-trail procedures display, feedback is provided when a pilot selects an invalid ITP flight level, unambiguous feedback is provided to the pilot upon selection of a valid flight level, and valid inter-target aircraft located in intervening flight levels after selection of a valid flight level are positively identified and invalid target aircraft for selection are uniquely identified.

An aircraft (1000) includes multiple servicing levels (1014, 1016) and a flight deck level (1040) that is isolated from the servicing levels (1014, 1016). An aircraft security system (1001) includes a passive system (1030) and an active system (1032) that is in operation with said passive system (1030). The passive system (1030) includes a service opening (1050) for both passengers and cargo and the flight deck (1040) that is isolated from the service opening (1050).

The invention discloses a modeling method of a trial flight maturity model. The trial flight maturity model is formed on the basis of a maturity model according to aircraft trial flight experience anddifferent stages of weapon equipment development; the trial flight maturity model is divided into six maturity levels including a non-trial flight level, a first flight level, an adjustment trial flight level, a setting trial flight level, a verification trial flight level and an acceptance trial flight level from low to high, and each level in the six maturity levels is used for evaluating the aircraft trial flight working condition through key state dimensions so as to form a step-type trial flight maturity improvement route. According to the method, the maturity model is introduced, relevant states and requirements of the aircraft trial flight are described in detail in stages and levels, a scientific method is provided for the level-transfer evaluation in the trial flight process, anda more powerful, more scientific and more systematic support is provided for improving the trial flight task completion efficiency and the trial flight safety control.

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 discloses a terminal area approach and departure air route optimizing method considering environmental impact. The method comprises the steps that (1) the generation trend of aviation pollutant discharge is judged, and the discharge index of a pollutant generated by an aircraft under each flight level is determined; (2) a terminal area airspace model is constructed, and the available airspace range of a terminal area is determined; and (3) a terminal area approach and departure air route optimization model is constructed to reduce aviation pollutant discharge and the impact of aviation noise, so as to acquire the optimal flight segment combination. According to the invention, safe and efficient operation of a departure air route is ensured, and aviation pollutant discharge and the impact of aviation noise are effectively reduced.

The invention relates to an unmanned aerial vehicle (UAV) control method and a UAV control device. The method comprises the steps as follows: when a UAV is in a first flight state, acquiring meteorological data of the current location of the UAV, wherein the first flight state is a state showing that the UAV is flying stably or is about to take off; determining the current dangerous flight level of the UAV according to the acquired meteorological data, wherein the dangerous flight level represents the level of danger caused by different weather conditions to the flight of the UAV; and if the dangerous flight level is a first preset level, switching the UAV to a second flight state, wherein the first preset level is a level at which the UAV is unable to fly safely, and the second flight state is a state showing that the UAV flies under emergency or stops flying. According to the technical scheme, a UAV can acquire meteorological data automatically and in real time and perform emergency treatment, so physical damage to the UAV caused by dangerous weather is avoided.

The invention relates to a landing device, in particular to a landing platform for a flight device. The landing platform comprises a frame and three or more supporting legs arranged at the bottom of the frame. The landing platform further comprises steering engines, a sensor and a controller. The sensor detects the tilting direction and tilting angle of the landing platform, receives signals of the sensor and controls different steering engines to conduct transmission at corresponding angles. Rotation of the steering engines causes bending of the supporting legs so as to control the corresponding adjustment height of the supporting legs in the vertical direction and keep the landing platform horizontal in real time. By the application of the landing platform for the flight device, the landing range of a rotor craft such as a four-axel aircraft applied quite widely currently can be greatly expanded; the landing platform can be applied to such fields as aerial photography, plant protection and engineering surveying.

The invention provides a aircraft conflict resolution method and equipment. The method includes: building an aircraft conflict resolution model in a control sector according to integer programming, wherein the conflict resolution model includes a preset target function and constraint conditions; acquiring the flying data of aircrafts, wherein the flying data includes the current position, the flying speed, the heading angle and the flying level of the aircrafts; acquiring the integer solution of the conflict resolution parameters of the aircrafts according to the conflict resolution model and the flying data, wherein the conflict resolution parameters include the flying speed adjusting amount, the heading angle adjusting amount and the flying level adjusting amount of the aircrafts; performing conflict resolution on the aircrafts in the control sector according to the conflict resolution parameters. By the method, conflict resolution of a large amount of aircrafts in an airspace can be achieved, high calculation precision is achieved, the flying speed, the heading angle and the flying level of the aircrafts can be adjusted, and actual requirements are satisfied.

The invention discloses a linear-interpolation-based cloud image profile projection method. The method comprises the following steps of performing east-west and south-north projection on an echo data matrix of each flight level in a matrix trace extraction way to obtain a matrix; performing linear interpolation on each column to obtain a continuous profile projection pixel map. The method is mainly used for an automatic air traffic control system for an airport, and the meteorological data of a weather radar and an air traffic situation are fused for display.

The invention discloses a flight recommendation method based on a user consumption level. The method comprises the steps of obtaining query conditions input by a user and a user ID, wherein the queryconditions comprise a departure place, an arrival place and a departure date; Acquiring a characteristic attribute of a user according to the user ID; Calculating the consumption level of the user according to the characteristic attribute of the user; Searching flights meeting query conditions, and calculating the levels of the flights according to the characteristic attributes of the flights; Andreturning a minimum price air ticket of the flight level matched with the user consumption level to the user. The flight information of different levels can be recommended to the users of different consumption levels, so that the ticket buying requirements of the users of all the consumption levels are met. The problem that in the prior art, only the lowest price ticket is pushed, and the requirements of high-end users cannot be met is solved.

The present invention is directed to an AOA (angle of attack) vertical control function for an AFCS (automated flight control system) for an aircraft. The AOA vertical control function of the AFCS causes the aircraft to climb or descend while maintaining the aircraft at a constant AOA. The AFCS may maintain the constant AOA despite changing air data parameters by increasing or decreasing the thrust of the aircraft, the pitch angle of the aircraft, or the angle of incidence of the aircraft wing. By utilizing AOA, an aircraft can be safely directed to automatically climb or descend to any altitude the aircraft is capable of reaching without the risk of stall (unlike Vertical Speed Mode) or the irritation of the FLCH (Flight Level Change) Mode erratic climb.

A method and system for determining in real time a vertical trajectory of an aircraft is provided. The method includes a step for providing an initial vertical trajectory comprising an initial phase for changing flight level according to a first slope, between a first point at a first altitude, and a second point at a second altitude, at least one step for modifying the vertical trajectory, comprising a phase for detecting a triggering element when the aircraft is at the first altitude, when said triggering element is detected, and a phase for determining a modified vertical trajectory, said modified vertical trajectory comprising a modified phase for changing flight level according to a second predefined slope, from a modified point at said first altitude, distinct from said first point, to said second altitude.

The invention relates to a dynamic sight point system on the basis of a kinect sensor for flight simulators. The dynamic sight point system is characterized in that a data line of the kinect sensor is connected with a computer host, the computer host of an instrument panel is linked with auxiliary units by network communication harnesses, and the various auxiliary units are respectively connected with an upper television screen, a front television screen, a right television screen and a left television screen by 3D (three-dimensional) graphic output harnesses. The dynamic sight point system for the flight simulators has the advantages that projection matrixes can be updated in real time by the dynamic sight point system for the flight simulators when the locations of the eyes of pilots are changed relative to the screens, and then screen images can be changed by the flight simulators by the aid of change of the projection matrixes; contents in actual sight ranges can be shown on the screens by the aid of the dynamic sight point system when the pilots observe environments via windows, accordingly, the pilots can have good immersion and presence, simulation training on the pilots is close to reality, and the flight levels of the pilots can be upgraded.

The invention provides a flight parameter regulating method and system. According to the technical scheme, the flight parameter regulating method and system are used for realizing that flight parameter data recorded by a flight recorder during flight of a flight device is invoked; internal storage of the flight recorder is subjected to blocked processing to save the flight parameter data correspondingly; the recorded flight parameter data is unloaded to a ground station to be processed; the ground station performs transcription treatment on the flight parameter data, wherein the transcriptiontreatment comprises resolving, compression and packaging; and the flight parameter data after being subjected to transcription treatment is subjected to interpretation, and corresponding data is searched according to requirements. The flight parameter regulating method and system have the beneficial effects that through ways of a classifying saving method, a rapid unloading method, reasonable dataresolving and packaging and the like, traditional complex and tedious steps are subjected to order adjustment and procedure simplification, repeated operation is avoided, the efficiency is improved,the interpretation speed of flight parameters of a plane is greatly accelerated, the problem that the flight releasing speed is limited due to fact that current domestic flight parameter interpretation time is excessively long is solved, and the operationally responsive ability of the plane is greatly improved.

The invention discloses a flapping wing flight device with an adjustable flapping wing. The device comprises a flapping wing 1, a connecting structure 2, an inner boundary guide pipe 3, an outer boundary guide pipe 4, a gas pump 5 and gas inflating guide pipes 6. The flapping wing flight device with the adjustable flapping wing, which is provided by the invention, is simple in structure, can adjust the shape and the area of the flapping wing through the gas pump and the guide pipes, achieves the simple flight control of an aircraft, and does not use a complex flight control system; the weight of the whole flight device is not increased obviously because gases are used in the guide pipes.

An altitude monitoring system for an aircraft, comprising an input unit that makes it possible to receive or enter cleared flight level and cleared maximum and minimum altitudes into the system, and interfaces or other means to gain access to present altitude and speed, said system being provided with a calculator unit for calculating a future altitude and a comparator unit that compare said future altitude with said maximum and minimum altitude limits, and / or with a cleared flight level plus / minus a tolerance, and also an alerting unit capable of issuing a warning to an aircraft pilot of said aircraft a certain time before an altitude limit is violated, said certain time being calculated such that an evasive manoeuvre using a specified load factor can be performed within said certain time with no or little margin.

The invention discloses a gas bag type suspending flight device comprising an outer gas bag (1) and an inner gas bag (2) allowing for injecting of hydrogen (4). A plurality of square gratings (3) allowing injecting of inert gas (5) are arranged between the outer gas bag (1) and the inner gas bag (2). Gas inflation valves (6) and a control device (7) are arranged on the outer gas bag (1). The gas inflation valves (6) communicate with the inner gas bag (2). A device (8) for conveying goods is arranged at the bottom of the outer gas bag (1). According to the gas bag type suspending flight device, the inner gas bag (2) fully filled with the hydrogen (4) of the gas bag type suspending flight device is not liable to break because of protection of the outer gas bag (1) and the square gratings (3) fully filled with the inert gas (5), even if one or more square gratings (3) leak gas, flight of the gas bag type suspending flight device is not affected, and therefore the gas bag type suspending flight device has the advantages of being large in carrying capacity, easy to maintain and operate, long in service life, simple in structure, high in safety and speed, low in cost and the like.

The invention discloses a regional sector deployment method capable of reducing condensation tail generation. According to the method, condensation tail generation trends on each flight height layer are determined; with resolving flight conflicts and minimizing the number of condensation tails adopted as objectives, an optimization model is constructed according to flight flow distribution features in a regional sector and based on a regional sector flight conflict detection relief method; a multi-objective regional sector flight deployment optimization algorithm is designed which is corresponding to a flight region control method in actual work; and the regional sector deployment method and control strategy which are capable of reducing condensation tail generation are determined; and therefore, the safe and efficient operation of the regional sector can be ensured, and the number of generated condensation tails and fuel costs are effectively reduced.

The invention provides a processing method for horizontal accelerating and decelerating test flight data of an airplane, which adopts a standard condition, is high in accuracy and is beneficial to improvement of horizontal accelerating and decelerating test flight level of the airplane. The technical scheme includes that the method includes the steps: firstly, obtaining five relational expressions (see the original text) according to a motion equation when the airplane is in horizontal and straight flight, wherein V refers to flight speed, ax refers to longitudinal acceleration, nx refers to longitudinal overload, g refers to gravity acceleration, delta t refers to horizontal accelerating and decelerating speed time of the airplane, and L refers to horizontal accelerating and decelerating distance of the airplane. If the actually measured longitudinal overload nxsj in flight is converted into the longitudinal overload nxbz under a standard condition, then, according to the relational expressions, the horizontal accelerating and decelerating time delta tbz and the horizontal accelerating and decelerating distance Lbz under the standard condition can be represented by: (see relational expressions in the original text).

The invention discloses a wind profile radar signal processing method, which comprises the specific steps: (I) constructing a wind profile radar signal processing system comprising an industrial control computer (1), a digital intermediate-frequency receiver board (2), a system control module (3) and a signal processing module (4); (II) collecting a radar echo signal by the digital intermediate-frequency receiver board (2); (III) carrying out signal processing by the signal processing module (4); and (IV) carrying out spectrum data processing ,displaying and transmitting by the system control module (3) to obtain wind field echo signal power and a signal to noise ratio estimated value on a processed flight level, thereby, wind profile radar signal processing is realized. In the method, the data processing precision is high; the storage capacity is high; the complexity and the cost of hardware are reduced; the performance and the reliability of the system are improved; the expansion and the updating of a signal processing algorithm are convenient; the universality is strong; the product cost performance is high; and the requirement of product lot sizing is ensured.

A system and method is provided for displaying ITP opportunities on an onboard display device of a host aircraft flying at a first flight level. Flight status data of the host aircraft and at least a first neighboring aircraft flying at a second flight level is obtained and processed to determine a first predicted time within which an ITP transition through the second flight level to a desired flight level can be made. A graphical representation of the host aircraft, the neighboring aircraft, and the first predicted time is rendered on the onboard display device.