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.

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 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 an airbag-type suspension flight device, which comprises an outer airbag (1) and an inner airbag (2) for filling hydrogen (4), and an outer airbag (1) and an inner airbag (2) are arranged There are several square grids (3) for filling inert gas (5), the outer air bag (1) is provided with an inflation valve (6) and a control device (7), the inflation valve (6) and the inner air bag (2) In the same way, the bottom of the outer airbag (1) is provided with a device (8) for transporting goods. Due to the protection of the outer airbag (1) and the square grid (3) filled with inert gas (5) of the airbag type suspension flying device of the present invention, the inner airbag (1) filled with hydrogen (4) is not easy to break, and even if there is one or Air leakage from multiple square grids (3) does not affect the flight of the present invention, so the use of the present invention has the advantages of heavy load, easy maintenance, simple operation, long service life, simple structure, high safety, fast speed, low cost, etc. advantage.

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).

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.