34 results about "Airmanship" patented technology

There are a sort of predictive filtering and the self-demarcation of the UPF spaceflight, it relates to the spaceflight airmanship field. It applies to the self-demarcation of the spaceflight peg-top, especially it relates to a sort of spaceflight self-demarcation method of the inertia / starlight which bases the predictive filtering and the UPF (Unscented Particle Filter) information coalescence, thereby it applies to the navigation determining gesture of the spaceflight. First it establishes the self-demarcation state equations of the spaceflight, and then it makes the gesture information which is observed by the star sensing device to become the measuring equations, finally it adopts the self-demarcation arithmetic which bases the predictive filtering and the UPF spaceflight to estimate and amend the drift error of the peg-top, thereby it obtain the high exact gesture of the spaceflight.

The invention discloses an unmanned aerial vehicle formation performance system based on UWB location and an implementation method thereof. An ultra broadband wireless communication technology and a time division TDoA technology are utilized to establish a three-dimensional location system applied to indoor and outdoor small areas; varieties of technologies of micro quadcopter formation navigationflight technology, a full-color LED light dimming technology and the like are combined to be applied to an indoor / outdoor small area performance system. In a three-dimensional location area, an aircraft colony performing navigation flight according to planned tracks, and color change of dimmable LED lamps arranged on a plurality of micro aircrafts is controlled to construct varieties of static and dynamic flight patterns, and stronger visual effect can be generated. As the time division TDoA technology based on UWB, a computer simulation micro aircraft colony flight pattern technology, an unmanned aerial vehicle colony flight pattern distribution storage technology and a PC coordinator synchronization and self synchronization combined technology are utilized, price of the whole system canbe reduced.

The invention discloses an input-limited finite time attitude cooperative tracking fault-tolerant control method, and belongs to the technical field of multi-spacecraft formation flight. In order to reduce communication paths and avoid resource waste, a communication topological structure which has less communication traffic, comprises a directed spanning tree taking a navigator as a root node andonly has a part of followers capable of obtaining navigator information is adopted among spacecraft formation members. In order to enable a following spacecraft which cannot obtain pilot informationto obtain reference information, a distributed finite time state observer is designed to observe the pilot information. Considering communication bandwidth limitation, actuator fault and saturation, system uncertainty and external interference, based on a finite time algorithm, a redundant fault-tolerant algorithm, an adaptive algorithm and a saturation function, a finite time attitude cooperativetracking fault-tolerant control strategy is perfected, and the robustness and practicability of the control system are further improved.

The invention provides an approach section flight technology error estimation method based on multi-source information fusion. According to the method, the measurement information of main navigation sources of an aircraft in a current approach section is acquired, wherein the main navigation sources includes an inertial navigation system, a satellite navigation system and an instrument landing system; time registration and space registration are performed on the acquired measurement information; information fusion is carried out by taking federated filtering as a framework, different filteringmethods are selected according to the characteristics of the different navigation sources, and position information with relatively high accuracy is obtained; sensor fault detection is carried out, isolation processing is carried out on fault signals, and the integrity of signals is guaranteed; and finally, vector calculation is conducted on the due flight path of the aircraft and the position information of the aircraft obtained through filtering according to the position information of the aircraft, so that a flight technology error estimation value is obtained. With the method of the invention adopted, flight technology error real-time estimation can be realized; the precision of an estimation result is higher, and the precise approaching operation of the aircraft can be ensured.

The invention discloses a small coaxial aircraft ejection device, which relates to the technical field of unmanned aerial vehicle flight. The device comprises an ejection shell and a bottom plate protection plate arranged at the bottom of the ejection shell. A spring energy storage assembly and an automatic unhooking mechanism are installed in the ejection shell. A positioning connection cone is arranged at the ejection connection part; the positioning connection cone is used for fixing the coaxial aircraft in an energy storage state, the spring energy storage assembly is used for compressingand storing energy of the positioning connection cone, the automatic unhooking mechanism can achieve automatic unhooking of the positioning connection cone, then the positioning connection cone is ejected out under the energy storage effect of the spring energy storage assembly, and ejection of the coaxial unmanned aerial vehicle is achieved. By arranging the energy storage ejection mechanism, kinetic energy is initially provided for the coaxial aircraft, the take-off speed of the coaxial unmanned aerial vehicle is increased, rapid reaction take-off and landing are achieved, and the device issuitable for rapid reaction flight in some special scenes and high in reliability.

The invention discloses an aircraft formation flight guide device. For a long aircraft, the aircraft formation flight guiding device comprises a high-precision satellite navigation antenna, a satellite navigation reference station, a data link antenna, data transmission equipment, a data processor and display control equipment, each wing plane comprises a high-precision satellite navigation antenna, a satellite navigation moving station, a data link antenna, data transmission equipment, a data processor and display control equipment. The satellite navigation reference station provides single-point positioning information of the high-precision satellite navigation antenna; the satellite navigation moving station provides single-point positioning information of the high-precision satellite navigation antenna and relative position information relative to the long machine; the data transmission equipment uses the same channel to broadcast and receive data with other data transmission equipment through the data link antenna; and the data processor processes the data, sends the information to the display control equipment for display and sends the information to the data transmission equipment for broadcasting. According to the invention, the aircraft formation can fly in more diverse environments, and the formation flight technology can be widely applied to performance and even actual combats.

The invention relates to a ground sweeping flight technology applied to a short-range supersonic cruising bomb, which inherits and optimizes a fixed-height flight technology applied to the short-range supersonic cruising bomb, ensures the stability of a flight attitude through an inner ring, generates a guide instruction of fixed-height flight through an outer ring, and improves the flight speed of the short-range supersonic cruising bomb. The inner ring controls the aircraft to track the guide instruction of the outer ring so as to achieve the purpose of fixed-height flight. Wherein the proportionality coefficient before the height item of the outer ring has certain adaptability to the height difference, the smaller the height difference is, the larger the coefficient is, and the cruise height error can be reduced to a large extent. When sweeping cruise at the height of 30 m is carried out, the cruise height error can be reduced to about + / -3 m from about + / -22 m (the fixed-height error of a fixed-height flight technology applied to a short-range supersonic cruise missile) under the limit pulling deviation condition, and therefore the method can be applied to sea sweeping cruise or sweeping cruise of the supersonic cruise missile within a short time.

The invention discloses a super-orbit speed flight technical scheme assisted by aerodynamic force, and belongs to the technical field of aircraft design. According to the basic principle of the technical scheme, aerodynamic lift force pointing to the earth center and generated by the aircraft with the high lift-drag ratio serves as supplement of centripetal force, super-orbital speed flight is achieved without centrifugal motion, meanwhile, thrust is used for offsetting aerodynamic resistance, and continuous flight at the super-orbital speed is maintained. The method specifically comprises thefollowing steps: firstly, establishing a flight dynamics model of a super-orbital-velocity aircraft based on a high-lift-drag-ratio aircraft; secondly, based on equal-height and equal-speed assumptions, calculating a super-orbit flight speed which can be reached by the aircraft; then establishing a burnup calculation method of the super-orbital-velocity aircraft; and finally, solving orbit parameters of the optimal fuel consumption flight scheme by adopting an optimization method. The ultra-high-speed flight technology has important application potential in the fields of global fast arrival,spaceflight emergency rescue and the like.

The invention belongs to the technical field of multi-aircraft collaborative formation flying, and provides a distributed relative navigation method oriented to multi-airplane collaborative formationflying. A MEMS-SINS navigation system and a GPS navigation system of a lead aircraft respectively output INS data and GPS data of the lead aircraft, the INS data and the GPS data of the lead aircraftare subjected to Kalman filtering processing to obtain INS output data of the lead aircraft after GPS correction, and the INS output data is fed back to a wing aircraft through a data chain; an MEMS-SINS navigation system and a GPS navigation system of a wing aircraft respectively output INS data and GPS data of the wing aircraft, and the INS data and the GPS data of the wing aircraft are subjected to Kalman filtering treatment to obtain INS output data of the wing aircraft after GPS correction; the INS output data of the lead aircraft and the wing aircraft after GPS correction is subjected torelative navigation calculation to obtain relative distance and relative position of the lead aircraft and the wing aircraft. The obtained relative distance and relative position can be provided fora multi-aircraft collaborative formation flying system in real time, thereby providing more accurate data source for realizing the formation aggregation, formation maintenance and reconstruction and like functions.

The invention provides a novel aircraft and an aircraft system, and relates to the technical field of flight. The novel aircraft comprises a fuselage, a pitch-control motor, a roll control motor, a transverse adjusting mechanism, two longitudinal adjusting mechanisms and a four-propeller-supporting-wing adjusting dual-output-shaft motor. The two longitudinal adjusting mechanisms are symmetrically arranged on the two sides of the fuselage. The pitch-control motor is arranged on the longitudinal adjusting mechanisms to control movement of the longitudinal adjusting mechanisms. The roll control motor is arranged on the fuselage and connected with the longitudinal adjusting mechanisms through the transverse adjusting mechanism. The transverse adjusting mechanism controls the longitudinal adjusting mechanisms to move in the transverse direction of the aircraft. Two output shafts of the four-propeller-supporting-wing adjusting dual-output-shaft motor are in transmission connection with four propeller supporting wings to control axial movement of the propeller supporting wings. According to the novel aircraft, the technical problems that a shooting scene is not comprehensive, the aircraft crashes easily in a complex space, and the aircraft takes off and lands on all terrains are solved.

The invention relates to the technical field of safe flight, in particular to a deep learning-based aircraft type identification and undercarriage extension and retraction detection method. The methodcomprises the following steps: respectively designing a YOLOv3 target tracking thread and a KCF target tracking thread, and sending detected category information and extension and retraction information to the KCF target tracking thread after the YOLOv3 target tracking thread detects extension and retraction of an aircraft or an undercarriage; carrying out target position detection on target position information detected by the YOLOv3 target tracking thread by utilizing the KCF target tracking thread, calculating a response between samples, finding out a detection box with a maximum responsevalue as a target box, and obtaining confidence information of the detection box; and fusing and comparing the data of the two times, and if the calculated position difference is within a set threshold value, outputting the mean value of the position information and the confidence coefficients of the two threads. According to the method, the good tracking performance of the KCF is exerted, so thatfalse detection of the YOLOv3 algorithm due to sudden change of the environment is reduced, and the defect that the YOLOv3 algorithm excessively depends on training samples is overcome.

The invention belongs to the technical field of safe flight of unmanned aerial vehicles, and discloses an electronic fence, a control system and method thereof, a medium, an unmanned aerial vehicle formation and a terminal. The control system is used for wirelessly controlling a flying unmanned aerial vehicle group; a communication link system is used for realizing data transmission and communication between the control system and the unmanned aerial vehicle group; and a recognition system is installed on each unmanned aerial vehicle and automatically calculates data information to the boundary of the electronic fence. According to the regular electronic fence provided by the invention, a ground station sends the information of the electronic fence to each aircraft, the aircraft automatically calculates the distance to the boundary of the electronic fence, the algorithm is simple, and the real-time performance is good; and the irregular electronic fence is set by a user at the ground station, the ground station calculates the distance from each aircraft to the boundary of the electronic fence in real time through the coordinate position of each aircraft, an algorithm is needed to be real-time and accurate, and compared with a regular electronic fence, the irregular electronic fence is wider in practical application.

The invention relates to the technical field of aviation navigation and flight verification, and discloses an aviation navigation equipment data acquisition system and method based on an unmanned aerial vehicle. The system comprises an unmanned aerial vehicle flight control system, a navigation equipment test antenna array, a multipath signal processing module, a signal acquisition module, an ADS-B emission module, a GNSS receiver, a UHF data link receiver, a power supply module and a ground station. The unmanned aerial vehicle carries a corresponding module, receives a signal of ground navigation equipment, carries out corresponding processing and storage, transmits data to the ground, receives a control instruction sent by the ground, and completes corresponding monitoring analysis and verification. Based on the flight technology of the unmanned aerial vehicle, the system and the method for acquiring the data of the aviation navigation equipment based on the unmanned aerial vehicle can reduce the flight verification cost and improve the flight verification efficiency, are effective supplementation of the existing flight verification of the manned aerial vehicle, and are also the development trend of the future flight verification.

The invention discloses a small-sized coaxial aircraft ejection device, which relates to the technical field of unmanned aerial vehicles, and comprises an ejection shell and a bottom plate guard plate arranged at the bottom of the ejection shell, and a spring energy storage component and an automatic decoupling mechanism are installed in the ejection shell, and the ejection is connected The positioning connecting cone is set at the position, the positioning connecting cone is used to fix the coaxial aircraft in the state of energy storage, the spring energy storage component is used for the compression energy storage of the positioning connecting cone, and the automatic decoupling mechanism can realize the automatic positioning of the positioning connecting cone. Unhooking, and then the positioning connection cone is ejected under the energy storage effect of the spring energy storage component, so as to realize the ejection of the coaxial UAV. The invention provides initial kinetic energy for the coaxial aircraft by setting an energy storage and ejection mechanism, thereby enhancing the take-off speed of the coaxial drone, realizing rapid response take-off and landing, suitable for rapid response flight in some special scenarios, and high reliability.

The invention relates to high speed aircraft flight technologies. A hypersonic propulsion engine comprises: a turbine engine comprising a compressor section, a combustion section and a turbine sectionarranged in serial flow order, the turbine section defining a turbine engine inlet upstream of the compressor section and a turbine engine exhaust downstream of the turbine section; a ducting assembly defining a bypass duct having a substantially annular shape and extending around the turbine engine, an afterburning chamber located downstream of the bypass duct and at least partially aft of the turbine engine exhaust, and an inlet section located at least partially forward of the bypass duct and the turbine engine inlet; and an inlet precooler positioned at least partially within the inlet section of the ducting assembly and upstream of the turbine engine inlet, the bypass duct, or both for cooling an airflow provided through the inlet section of the ducting assembly to the turbine engineinlet, the bypass duct or both.

The invention relates to the technical field of training device, and discloses a system for intelligently correcting the flight actions of a student pilot. The system comprises a control console, wherein a display screen is fixedly mounted on the top of the control console; a height adjusting device is fixedly mounted on the top of the control console; an operating device is fixedly mounted on thetop of the control console; and an indicating device positioned on one side of the operating device is fixedly mounted on the top of the control console. According to the system for intelligently correcting the flight actions of the student pilot, through the mutual matching of the control console with the display screen, the height adjusting device, the operating device and the indicating device, whether a baffle plate is lifted to a specified height or not can be detected by utilizing a correlation sensor, an airplane can be smoothly landed, and the rotating angle of an operating rudder canbe marked by utilizing the indicating device and a scale mark on the top of the operating rudder, so that the student pilot can quickly master the operating skill of the operating rudder, the training time of the student pilot is shortened, and the student pilot masters the flight technology more accurately.

The invention relates to the technical field of bionic flight, and particularly relates to an aircraft. The aircraft comprises an aircraft body structure, wing structures detachably connected with theaircraft body structure, an empennage structure, a head structure and a support structure, wherein the head structure includes a head body connected with the aircraft body structure; the support structure is completely or partially located in the head body, and a distance between the support structure and a front end of the head body is smaller than the maximum plastic deformation value of the head body. When the front end of the head body is impacted, the support structure makes contact with the head body before the head body reaches the maximum plastic deformation. The support structure canapply a counter force to the head body so that an impact force on the head structure and the counter force applied by the support structure are mutually counteracted, the head body can be prevented from being broken, and a head is not prone to damage; and due to a fact that the support structure is located in the head body, when the head body deforms due to impact, other positions, except a frontend, of the head body are not prone to deformation due to supporting of the support structure.

There are a sort of predictive filtering and the self-demarcation of the UPF spaceflight, it relates to the spaceflight airmanship field. It applies to the self-demarcation of the spaceflight peg-top, especially it relates to a sort of spaceflight self-demarcation method of the inertia / starlight which bases the predictive filtering and the UPF (Unscented Particle Filter) information coalescence, thereby it applies to the navigation determining gesture of the spaceflight. First it establishes the self-demarcation state equations of the spaceflight, and then it makes the gesture information which is observed by the star sensing device to become the measuring equations, finally it adopts the self-demarcation arithmetic which bases the predictive filtering and the UPF spaceflight to estimate and amend the drift error of the peg-top, thereby it obtain the high exact gesture of the spaceflight.

The present invention relates to a secure terminal (1) for the aerial transport of passengers whose technical and operational infrastructure makes it possible to ensure the physical security of the building, of the aircraft, of the goods, of the passengers and of the flight, technical and administrative personnel and the confidentiality of the passengers and of their goods, noteworthy in that it comprises at least one building (2) having a globally V-shaped horizontal section and comprising two branches (3) extending from a mid-zone (4), constituting parking hangars for aircraft and determining between them an uncovered central zone (7), called "ramp", physically isolated from the exterior environment of the secure terminal (1) by a barrier (8), named "shield", joining the free ends of thebranches (3) and then transforming the building (2)-ramp (7) assembly into a secure enclosure, the shield (8) also participating in safeguarding confidentiality.

The invention discloses a distributed unmanned aerial vehicle formation change method, relates to the technical field of unmanned aerial vehicle flight, solves the problems of high communication overhead and low reliability of formation change information transmission and the problem of distributed formation synchronization, and enhances the safety of distributed formation change. According to thespecific scheme, the method comprises the following steps: S1, presetting related instructions of all formation patterns on all unmanned aerial vehicles, and sequentially performing numbering according to the number of the formation patterns; s2, sending serial number signals of the formation needing to be changed to all the unmanned aerial vehicles through a control station; s3, enabling all theunmanned aerial vehicles to receive the serial number signals in the S2, automatically generating a leader plane according to instructions of the unmanned aerial vehicles in the S1, wherein the otherunmanned aerial vehicles are wing planes; and S4, enabling the lead aircraft to adjust the position of the lead aircraft according to the instruction of the lead aircraft, and enabling all the wing aircrafts to adjust the positions of the wing aircrafts according to the instruction of the lead aircrafts. According to the invention, the idea of instruction number mapping formation is adopted, so that the communication overhead caused by directly sending the formation matrix can be greatly reduced.

The invention relates to the technical field of simulated flight, in particular to a spatial orientation obstacle simulator which comprises a transmission supporting system, a rotating arm system, a rolling frame system, a yawing frame system and a cockpit system, wherein the transmission supporting system supports the rotating arm system and drives the rotating arm system to rotate in the horizontal plane; the rolling frame system is arranged on the rotating arm system and rotates around a connecting point of the rolling frame system and the rotating arm system; the rotating center line of the rolling frame system is located in the horizontal plane; the yawing frame system is arranged in the rolling frame system and rotates around a connecting point of the yawing frame system and the rolling frame system; and the cockpit system is arranged in the yawing frame system and rotates around a connecting point of the cockpit system and the yawing frame system. The spatial orientation obstacle simulator has the advantages that a main shaft rotates to generate overload acceleration, three degrees of freedom of yawing, pitching and rolling relative to a human body coordinate system are generated at the tail end of a rotating arm, a trained pilot sits in a cockpit system and bears centrifugal overload acceleration and spatial three-attitude-angle movement, and spatial orientation obstacle simulation training is achieved.

The invention discloses an integrated neural network-based aircraft gliding section flight range online prediction method, and belongs to the technical field of aircraft flight. The method comprises the following steps: before an aircraft takes off, selecting sample points on a predetermined standard trajectory and randomly and equally dividing into multiple groups; calculating a trajectory drop point longitude and a trajectory drop point latitude; the input of the sample library is a ballistic calculation initial value, and the output of the sample library is the maximum value and the minimum value of the ballistic drop point longitude and latitude; training each group of sample points to obtain a flight range prediction neural network; and inputting the current flight state of the aircraft, performing flight range prediction by adopting a flight range prediction neural network, performing integrated neural network prediction on a prediction result, and then obtaining a flight prediction result. According to the method, the prediction accuracy is improved, the strong nonlinear dynamic process of the gliding section of the aircraft is considered, the maximum flight range can be obtained according to the current state of the aircraft, the flight range is calculated in real time by adopting a neural network offline training and online use mode, and the method has good engineering practicability.

The invention discloses a flight control capability simple evaluation method, and belongs to the technical field of civil aviation flight. Flight actions are determined based on flight training essence, index evaluation and weight are clear, an evaluation calculation formula is formulated, and the method is simple, convenient, feasible, high in applicability and scientific and objective in result.The method does not need to use a complex mathematical model, does not need to change frequently after determining the flight action and the evaluation index weight, is simple and convenient in calculation, is suitable for various different flight subjects, is high in generalization, is scientific and objective in evaluation result, and is high in credibility.

The embodiment of the invention discloses an analysis method for the existence of chaotic motion in a space tether system, relates to the field of spacecraft flight technology, can effectively predict the occurrence of chaotic motion, and avoids the impact of irregular chaotic motion on the space tether system. The invention includes: collecting the state parameters of the in-orbit spacecraft and the terminal load, and obtaining the space tether system according to the state parameters; obtaining the parameter plane according to the orbit inclination and orbit height of the space tether system; using the The parameter plane is used to detect the existence of chaotic motion in the space tether system through a judgment model. The invention is applicable to the flight attitude monitoring of the space tether system.

The invention provides a propeller, a power assembly and an aircraft, relates to the technical field of flight, and aims to solve the technical problems of high noise and resistance increase caused by the fact that a wing tip of the propeller is easy to generate vortexes and cavitation bubbles. The propeller comprises a central column and at least two blades, the wing root of each blade is arranged on the central column, each blade is provided with two blade sections and a blade tip transition section, the wing root of each blade section is connected to the central column, and each blade section is provided with a windward first front edge and a first rear edge opposite to the first front edge; the wingtip transition section is a curved-surface-shaped transition section, the wingtip transition section is provided with a second front edge and a second rear edge opposite to the second front edge, the first front edges of the two blade sections are in transition connection through the second front edge, the first rear edges of the two blade sections are in transition connection through the second rear edge, and the second front edge and the second rear edge are both arc-shaped edges. The propeller provided by the invention is used in the aircraft.

The invention relates to the field of airborne electronic system testing, provides a navigation performance distribution and monitoring method based on FTE estimation, and aims to set navigation parameter performance requirements of a navigation exciter according to a performance distribution method and monitor navigation parameter performance generated by the navigation exciter. Flight technical error fluctuation is estimated in a manual mode and an automatic mode, and the flight technical error is set more accurately by combining a method for setting a fixed flight technical error in an aviation industry standard according to a flight stage, a flight airspace type and a flight mode. Therefore, the performance requirement on the navigation system in the performance-based navigation is obtained; meanwhile, under the performance requirement, the performance of the navigation parameters is monitored. The method is mainly applied to airborne electronic system monitoring occasions.

The invention discloses an aircraft flight performance algorithm based on a linearized incremental equation. The invention belongs to the technical field of aviation flight. The method comprises the following steps: a, performing linearization of a nonlinear kinetic equation: performing linearization processing on the nonlinear kinetic equation to obtain a linear increment equation, performing Taylor series expansion on an equation described in an analysis form at a reference state point, and reserving a first-order reciprocal; linearizing a kinetic equation described in a discrete data form by adopting a numerical algorithm; carrying out dynamic characteristic description through a linearized incremental equation; b, determining calculation conditions and output; c, solving an unknown quantity by utilizing a linearized increment equation; and d, solving performance characteristic parameters. According to the method, efficient and stable calculation of the performance data can be realized, and the method can be applied to various application scenes with relatively high requirements on timeliness and stability.

The invention discloses a passive air valve type double-layer fluttering hovercraft, and relates to the technical field of fluttering hovering flight in an air environment. The passive air valve typedouble-layer fluttering hovercraft comprises a hovercraft rack, a double-layer passive air valve type airfoil structure, a symmetric vibration mechanism and a driving mechanism. The driving system drives the vertical double-layer airfoil structure to achieve vertical periodic vibration through the symmetric vibration mechanism. In the vibration process, a strip-shaped film air valve on the airfoilstructure can be passively opened and closed under the action of inertia force and air resistance, and adaptively coordinates with the periodic vibration of an airfoil, the wind resistance area of the airfoil is changed through the passive opening and closing angle of the air valve, a wind resistance difference is generated to improve take-off force, a new hovering mode is achieved, and the performance of vertical take-off and landing, stable hovering and the like is achieved. The fluttering hovercraft has the characteristics of being ingenious in airfoil design, simple in vibration mode, high in flying efficiency, high in overall stability, low in manufacturing cost and high in practicality.