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 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 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 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.

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 electric multi-rotor aircraft and the control method provided by the invention relate to the technical field of flight. The control method is applied to the electric multi-rotor aircraft. The electric multi-rotor aircraft includes a frame assembly, a lift assembly and a plurality of motor rotors, the lift assembly and the plurality of motor rotors are respectively fixed to the frame assembly, and the motor rotors are uniform and symmetrical around the lift assembly ground distribution. When the electric multi-rotor aircraft is lifted into the air, when people do not participate in the control, the attitude of the entire electric multi-rotor aircraft can be freely balanced and controlled by its own center of gravity. The operation of the pilot is simplified, so that the electric multi-rotor aircraft is easier to control.

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.

A UWB positioning-based UAV formation performance system and its implementation method, using ultra-wideband wireless communication technology and time-divided TDoA technology to construct a three-dimensional positioning system for indoor and outdoor small areas, using micro quadrocopter formation navigation flight technology Combined with various technologies such as full-color LED dimming technology, it can be used as a performance system for indoor and outdoor small areas. In the three-dimensional positioning area, the aircraft cluster conducts navigation and flight according to the planned trajectory, controls the color change of the dimmable LED lights mounted on multiple micro air vehicles, and constructs various static and dynamic flight patterns, resulting in a stronger visual Effect. Due to the combination of time-sharing TDoA technology based on UWB, computer simulation micro-aircraft cluster flight pattern technology, UAV cluster flight pattern distribution storage technology, PC coordinator synchronization and self-synchronization technology, the price of the entire system can be reduced.

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.