257 results about "Flight duration" patented technology

An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

The invention provides a rotated quadrotor, and belongs to the technical field of aircraft design. The rotated quadrotor comprises flying rotor wings, brushless direct current motors, a fuselage, a canopy, undercarriages, a power supply unit, a flight control system, fixing tubes, a rotated rocker arm, a connecting rod, a rotated steering engine, rotor wing arms, and round heads. According to the rotated quadrotor, rotating angles of the four flying rotor wings in the front-back direction are controlled to as to realize forward flying or backward flying; installation angles of the flying rotor wings are changed so as to realize forward flying of the four flying rotor wings, maintain level condition of the fuselage, ensure that the best aerodynamic performance of the quadrotor is maintained all the time, and the maximum lifting force of the fuselage is induced, increase flying speed of the quadrotor, prolong flight duration, and improve wind resistance, operation capability, and efficiency.

The invention provides a system and method for multi-power integrated flight control applied in a micro air vehicle. The system comprises a flight control computer, a flight parameter sensor, a PID controller, a yaw propeller power system, a posture propeller power system and a main propeller power system, wherein an output end of the flight parameter sensor is connected to an input end of the flight control computer, and an output end of the flight control computer is separately connected to the yaw propeller power system, the posture propeller power system and main propeller power system by the PID controller. The system and method provided by the invention have the advantages that (1) a layout manner of a main propeller, a posture propeller and a yaw propeller is applied, so that a load of the posture propeller can be effectively reduced during a flight course, efficiency of a power system of the air vehicle can be effectively increased, and flight duration of the air vehicle can be increased; and (2) integrated control is carried out to the multiple sets of power systems of the air vehicle, so that the problem that lift force of the main propeller of the air vehicle is unstable and the problem about reverse torque balance of the main propeller can be solved, and finally autonomous flight of the multi-rotor air vehicle with the new layout can be realized.

The embodiment of the invention provides an unmanned aerial vehicle base station site selection and patrol path optimization method and device. The method includes allocating target points according to Euclidean distance between the target points reconnoitered by unmanned aerial vehicles and base stations, then according to neighboring point search, planning an unmanned aerial vehicle flight path, using unmanned aerial vehicle flight duration to constrain and define an unmanned aerial vehicle patrol path, and defining upper and lower limits of the number of unmanned aerial vehicles that each base station configures, thereby obtaining an initial scheme for unmanned aerial vehicle base station site selection and patrol flight path; performing neighborhood search on the initial scheme, so as to obtain a new scheme for unmanned aerial vehicle base station site selection and patrol path after neighborhood search adjustment; calculating the total cost of the new scheme for unmanned aerial vehicle base station site selection and patrol path; and if the total cost of the new scheme is judged to be reduced compared with the total cost of the original scheme, storing the new scheme, and performing next-step iteration on the basis of the new scheme, otherwise abandoning the new scheme. The abovementioned technical scheme has the following beneficial effects: the unmanned aerial vehicle base station site selection and patrol path cost is minimized, the unmanned aerial vehicle patrol cost is greatly reduced, and the scheme is very low in time consumption.

Identification of the tee-off bay (52;53) from which a golf ball landing on a golf-range target (51) originated, is made by calculating an estimate of flight duration (Edurk) of the descending ball as a function of the measured angle (β) of descent in elevation, and, in respect of each ball launched from the bays (52,53), comparing this estimate for a match with a measured interval between the launch of the respective ball and descent of the descending ball. The originating bay (52;53) of the launched ball for which there is the closest match is identified as the origin of the descending ball, and ambiguity or uncertainty between which bay (52,53) is identified is resolved through comparison of the measured angle (αdes) of descent in azimuth of the descending ball with estimates (Edirk) of it calculated for each launched ball, and through similar comparison in respect of a calculated decelaration ratio (Edeck) and flight duration (Durk).

Methods and systems for performing three dimensional LIDAR measurements with an integrated LIDAR measurement device are described herein. In one aspect, a return signal receiver generates a pulse trigger signal that triggers the generation of a pulse of illumination light and data acquisition of a return signal, and also triggers the time of flight calculation by time to digital conversion. In addition, the return signal receiver also estimates the width and peak amplitude of each return pulse, and samples each return pulse waveform individually over a sampling window that includes the peak amplitude of each return pulse waveform. In a further aspect, the time of flight associated with each return pulse is estimated based on a coarse timing estimate and a fine timing estimate. In another aspect, the time of flight is measured from the measured pulse due to internal optical crosstalk and a valid return pulse.

The invention relates to an independent flight safety monitoring and information management system for a UAV (unmanned aerial vehicle). The system is characterized by mainly comprising a UAV status monitoring unit, a UAV status display unit and a UAV status storage and analysis unit, wherein the UAV status monitoring unit adopts an independent built-in rechargeable battery, and a built-in completesensor group is used for monitoring the UAV flight status and transmitting the UAV flight status back to the UAV status storage and analysis unit; the UAV status display unit can query UAV status information of a corresponding account after logging in, receive maintenance and alarm information pushed by the UAV status storage and analysis unit and trigger alarm information of the UAV status monitoring unit to help find the UAV when the UAV is lost; the UAV status storage and analysis unit receives and stores the UAV status information returned by the UAV status monitoring unit, analyzes and counts flight information such as UAV flight duration, engine start time, flight hotspots and whether it violates rules on the basis of built-in UAV flight information data and machine learning by an artificial intelligence algorithm, and pushes information including flight area selection, UAV maintenance and UAV flight violation alarm to the UAV status display unit.

The invention discloses a laser radar ranging system and a ranging method thereof. The laser radar ranging system comprises: a transmitting module for transmitting laser pulse signals to a target areato be measured; a receiving module for receiving echo signals reflected from the target area to be measured; and a control and processing circuit for controlling the transmitting module to transmit laser pulse signals with alternating time intervals to the target area to be measured, controlling the receiving module to receive the echo signals reflected from the target area to be measured, judging the number of echo signals received within the alternating time intervals and the sizes of corresponding flight times, and calculating the distance information of the target area to be measured according to a judgment result. The laser radar ranging system disclosed by the invention improves the ranging range of a laser radar system, solves the problem of distance aliasing, and improves the anti-interference ability of the system at the same time.

Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.

A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and / or a predicted intercept point. An iterative process may be used in adjusting the aim point and / or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and / or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.

The invention relates to a time of flight apparatuses and an illumination source. The apparatus includes a detector circuit configured to receive a modulated electromagnetic wave signal from an illumination source and to provide a detection signal having a frequency dependent on a modulation frequency of the modulated electromagnetic wave signal. The apparatus further includes a reference circuit configured to generate a reference signal based on the detection signal. The apparatus further includes a sensor circuit configured to generate based on the reference signal a sensor signal based on reflected modulated electromagnetic waves emitted by the illumination source and reflected by an object. The apparatus further includes a processing circuit configured to determine distance information related to the object based on the sensor signal.

The invention relates to the field of captivity, aims at the defect that existing grazing management systems based on unmanned aerial vehicles are poor in using effect and discloses a free-ranging grazing management system based on unmanned aerial vehicles. The free-ranging grazing management system comprises a hangar, a control station and at least three beacons in wireless connection with the control station, and a sensing module is arranged on each beacon and used for positioning and collecting livestock position information and transmitting the same to the control station; an expelling unmanned aerial vehicle and a tracking unmanned aerial vehicle in wireless connection with the control station are arranged in the hangar, the expelling unmanned aerial vehicle is used for expelling livestock back to a foraging area, and the tracking unmanned aerial vehicle is used for tracking livestock leaving the foraging area; the control station comprises a host and an alarming device connected with the host, the host receives the position information of the livestock from the beacons and transmits a control instruction to the expelling unmanned aerial vehicle and the tracking unmanned aerial vehicle; each sensing module comprises an infrared camera and a distance sensor, a parking plate is arranged beside each beacon, and a to-be-charged area is arranged in the hangar. Compared with the prior art, the free-ranging grazing management system has the advantages of long flight duration and good management effect.

The invention relates to a hybrid power unmanned aerial vehicle. The hybrid power unmanned aerial vehicle is characterized by comprising at least two lifting rotors, control rotors, a load frame and a rack, wherein the lifting rotors, the control rotors and the load frame are all mounted on the rack; the lifting rotors are symmetrically arranged in pairs and are arranged on two sides of the central axis of the unmanned aerial vehicle, and the rotor faces of the lifting rotors are perpendicular to the central axis of the unmanned aerial vehicle; and the lifting rotors are driven by fuel motors, and the control rotors are driven by motors. According to the hybrid power unmanned aerial vehicle, the lifting rotors provide the main lifting force; the control rotors keep the attitude of an aircraft; during advancement, retreatment and selective movement in a plane, the control rotors are accelerated or decelerated to change the attitude of the aircraft; the control algorithm of the unmanned aerial vehicle is similar to that of the multiple rotors, and a matched control structure of a helicopter is omitted, so that the structure and the control algorithm are greatly simplified, and further, the stability, the load, the flight duration and the controllability of the aircraft are improved.

An Extra Electric Energy System that supplies electrical power to an aircraft of the continuous flight duration day / night cycle solar powered type is described where the extra electric energy is generated as static charge by collisions of the aircraft with particles existing in the earth's atmosphere. The manner in which the static charge is collected, stored and used immediately to meet present or future aircraft power needs is considered. An example of the application of the system to a high altitude solar powered Helios type aircraft is offered along with a discussion of how its structure is modified to store static charge.

Identification of the tee-off bay (52;53) from which a golf ball landing on a golf-range target (51) originated, is made by calculating an estimate of flight duration (Edurk) of the descending ball as a function of the measured angle (β) of descent in elevation, and, in respect of each ball launched from the bays (52,53), comparing this estimate for a match with a measured interval between the launch of the respective ball and descent of the descending ball. The originating bay (52;53) of the launched ball for which there is the closest match is identified as the origin of the descending ball, and ambiguity or uncertainty between which bay (52,53) is identified is resolved through comparison of the measured angle (αdes) of descent in azimuth of the descending ball with estimates (Edirk) of it calculated for each launched ball, and through similar comparison in respect of a calculated decelaration ratio (Edeck) and flight duration (Durk).

The present invention provides a measurement device used for space ions and neutral atoms. The measurement system comprises an ion deflection system, a neutral atom ionization deflection system, an electrostatic analyzer, a flight time system, an electronics processing unit and a device shell. The back-end electrostatic analyzer, the flight time system and the electronics processing unit are shared to measure the ions generated by ionizing the neutral atoms and the ions radiated from the space directly, the measurement of the space ions and the neutral atoms is integrated in a probe, and the as much as possible measurement parts are shared, so that the weight and the power consumption of the device are reduced furthest, the requirements for the satellite platform resources are also reduced, and the fields to which the device is applied are expanded. The measurement device of the present invention has the wide application demands both in the terrestrial space field and the deep space exploration field.

The invention discloses a flight arrival time prediction method and system based on data mining analysis. The flight arrival time prediction method comprises the steps of S1, carrying out flight historical operation data matching fusion and standardization processing; s2, carrying out historical operation data feature screening and correlation analysis; 3, constructing a prediction model; and S4,inputting the characteristic variable data of the predicted flight into the regression prediction model, and performing calculation to obtain a prediction value of the remaining flight time of the flight. According to the invention, flight historical data is collected from an ADS-B system, an ACARS system and other devices; firstly, data is subjected to association and standardization processing;Pearson correlation coefficient calculation is performed according to feature variable screening and feature value calculation, and a regression prediction model based on an XGBoost algorithm is constructed; the parameter optimization model is continuously adjusted to obtain the regression prediction model with the optimal accuracy, the predicted arrival time of the flight can be predicted after the characteristic variable data of the predicted flight is input into the model, and the prediction precision of the arrival time of the flight is improved.

The present invention provides a computer-implemented method of generating an aircraft intent description expressed in a formal language that provides an unambiguous four-dimensional description of an aircraft's intended motion and configuration during a period of flight. A flight intent description is parsed to provide instances of flight intent that span a flight segment, the flight segments together spanning the period of flight. The parsed flight intent is enriched with objectives and constraints according to user preferences, operational context and aircraft performance. The resulting enriched flight intent is converted into a parametric aircraft intent description by ensuring that each flight segment closes all associated degrees of freedom of motion and of configuration of the aircraft. At least some instances of aircraft intent contain a parameter range, and the method further comprises optimising the parametric aircraft intent by determining an optimal value for the parameter of each parameter range.

A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and / or a predicted intercept point. An iterative process may be used in adjusting the aim point and / or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and / or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.

Disclosed is a system to forecast a supply of online advertising demand contracts having day parting targets. The system may receive an online advertising demand contract having a flight duration and a day parting target. The received online advertising demand contract may be processed by converting the day parting target into an hour-of-week day parting target vector. If a first day of the flight duration would generate a conflict in view of the hour-of-week day parting target vector, then the system may generate a new first day contract for the first day of the flight duration.

A safety system seeking to avoid an undesirable event while piloting a helicopter. According to the invention, the system is remarkable in that it comprises a computer making it possible at any instant t to generate a three-dimensional envelope of fallback paths for the helicopter, the envelope being obtained by calculating, at the instant t, a set of positions that can be reached by the helicopter during a predetermined flight duration, the computer having parameters previously set with data relating to the flight capabilities of the helicopter and including at least one of the following capabilities: maximum speeds and accelerations in all three spatial directions, minimum turning radii for yaw, nose-down, and / or nose-up movements, maximum weight of the transported load, and maximum stresses.

A system and method for flight planning determines an optimal route by setting an initial departure weight or range of such weights for an aircraft traveling from a departure airport to a destination airport, defining a network of nodes for potentially legal routes, labeling each node with a graph of fuel needed to reach that node either as a function of flight duration or as a function of flight duration and departure weight, selecting or discarding routes when conditions at a node of that route are favorable or violated, selecting a preferred route, departure weight and duration for the desired payload and minimizing fuel for the desired route and payload.

A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

The invention discloses an impact monitoring and energy assessment technology for a composite material structure and belongs to the technical field of intelligent detection and assessment of the composite material structure. According to the technology, a new two-step impact positioning method including an energy distribution smooth filtering method and a TOF (time of flight) based four-side central positioning method is applied in the aspect of impact positioning; in the aspect of impact energy assessment, a multipath integrated energy distribution assessment method for imaging processing based on pixel grid optimization is proposed and assessment for the absorbed energy distribution condition of the structure is realized. With the adoption of the technology, whole-layout impact positioning and energy assessment are realized; by means of the new two-step impact positioning method, precision, timeliness and reliability of impact positioning are improved; influence of structural complexity and composite anisotropy on the impact positioning and impact energy assessment performance is inhibited, effective impact positioning and energy assessment in a severe external environment are also improved, and wide application of the technology in technical fields of intelligent detection and assessment of the composite material structure is promoted strongly.

A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.

The invention discloses a power planning method for flight control of a small unmanned helicopter. In the power planning method, on the premise of keeping the stable flight state of the small unmanned helicopter unchanged, the total demand power is analyzed and optimized; through optimizing match between a rotor rotation speed and a manipulated variable, the total demand power is minimized, and the corresponding best engine rotation speed under the minimum demand power is obtained; an engine constant speed controller is designed to track the best rotation speed under the corresponding stable flight in real time, the engine thus constantly works at the best working point under the current stable state, the mobility of the helicopter is ensured, the flight duration time is increased, fuel oil consumption is reduced, and the target for power planning of the engine is achieved.

The invention discloses a multi-missile time cooperative missile guidance method and system. The method comprises the following steps that (1) a guidance kinematics model of each missile in a missile group is established; (2) for the established guidance kinematics model of each missile, CPN guidance laws for a stationary target and a maneuvering target are given respectively, and missile guidance based on the CPN guidance laws is completed; wherein when the CPN guidance laws are determined, the missile group consistency expected remaining flight time is calculated based on a weighted average consistency method; and based on a multi-agent depth deterministic strategy gradient algorithm, the missiles learn and decide CPN guidance law correlation coefficients. According to the method, the multi-agent DRL is applied on the basis of the existing time cooperative guidance law CPN to endow the missile group with the intelligent sensing and decision-making ability, the guidance precision can be improved, the cooperative time error can be reduced, and effective attacks can be achieved for static and maneuvering targets respectively.

An amphibious unmanned rotorcraft comprises a rotorcraft body, wherein transverse supporting rods are arranged on two sides of the rotorcraft body; motors are arranged below the supporting rods, and connected with lifting rotor blades; and a propulsion motor is connected with one end of the rotorcraft body and propulsion rotor blades. Through adoption of the amphibious unmanned rotorcraft, the problem that a conventional UAV (unmanned aerial vehicle) is short in flight duration can be solved; and the amphibious unmanned rotorcraft is simple and practical in structure, convenient to repair, low in cost and very high in value of market popularization.

The invention relates to a method of measuring a distance between two radio-communication devices (1, 2), consisting in measuring a radio signal exchange delay. According to the invention, the time-of-flight of the signals is calculated from the exchange delay and subsequently corrected using an analysis of a single channel measuring frame that is transmitted between the two devices. The corrected time-of-flight corresponds to the shortest propagation path followed by the radio signals. In the majority of radio transmission medium configurations, the corrected time-of-flight is a straight line measurement of the distance separating the two devices (1, 2).