30 results about "Unpowered flight" patented technology

The invention discloses a design method for an approach landing track of an unpowered aircraft. When the flareout landing track is designed, assumed that the height of a flareout landing initial point is known, then, expressions of all track parameters are derived according to a geometrical relationship, and the flareout landing track is designed. In order to design the ideal flareout landing track, the proper height of the flareout landing initial point is found out through an optimization algorithm, track deduction is conducted along the landing track, and therefore the grounding dynamic pressure becomes the ideal grounding dynamic pressure. A deep glide landing track and the ideal flareout landing track form the optimal approach landing track. According to the design method, the aerodynamic force and the aerodynamic moment borne by the aircraft are taken into consideration, and the influences on the design of the landing track of aerodynamic data of deflecting of an aerodynamic control plane and putting of an undercarriage are also taken into consideration. The design method for the approach landing track is simple in principle, computer software is adopted for conducting optimization design, and the design efficiency is improved.

A launching system may include a multirotor platform that includes a plurality of motors and propellers. The multirotor platform may be launched from a launch tube and actuated to transition from a storage state to a flight state where the propellers are operable via the motors. The multirotor platform may include pivotable pivoting motor arms that are connected between the main flight body and the propellers. After the multirotor platform is deployed from the launch tube, the pivoting motor arms may be actuated to extend from a retracted position against the main flight body and enable operation of the motors and the propellers for powered flight of the multirotor platform. The multirotor platform may include motor pylon wings connected to the motors and retractable nose gears for deploying the motor pylon wings and enabling unpowered flight or gliding movement of the multirotor platform.

The invention relates to a demonstration device for powerless flying devices and, in particular, flying sport devices such as jumping skis (9) or parasails and for bird-human costumes (20, 23). The inventive device has the following features: a suspending device (11) for the individual(s), which holds the individual(s) in a position that would be assumed during an actual flight using the respective flying device, and; a support (30, 31, 32) that is connected to the suspending device in such a manner that the trajectory of the individual(s) located in the suspending device is essentially determined by the movement of the support and not by the flying device connected to the individual(s).

The invention discloses a large-diving-depth underwater unpowered aircraft transmitting system and method. The transmitting system comprises an underwater autonomous measuring and control system, a transmitting cylinder with a front cover, a catapult arranged in the transmitting cylinder, and an aircraft arranged in the transmitting cylinder, wherein the transmitting cylinder, the catapult, the aircraft and the measuring and control system integrally adopt an axial deflection design; compared with a mass center, the axial buoyant center is closer to the front cover of the transmitting cylinder; the transmitting system is fixed to an underwater platform, after the transmitting system is separated from the underwater platform, the situation that upward buoyance is greater than the sum of gravity and floating resistance is changed into the situation that the upward buoyance and the sum of the gravity and floating resistance gradually tend to be balanced; the aircraft is fixed on one side of a sealing bottom plate in the transmitting cylinder, and the other side of the sealing bottom plate is connected with the catapult; and after the front cover is opened, the catapult produces thrust to push the aircraft to slide in the direction from the transmitting cylinder to the front cover, and the aircraft slides from the transmitting cylinder. According to the large-diving-depth underwater unpowered aircraft transmitting system disclosed by the invention, the maximum transmitting depth of the transmitting system is not less than 200 meters; and in the transmitting system, the aircraft does not bear water pressure limit directly, so that the aircraft is low in design condition requirements, and high in portability.

The present invention relates to an unmanned aerial vehicle parachute landing recovery method based on the accurate measurement of a wind field, and applied to the parachute landing fixed point recovery of medium-and-small sized unmanned aerial vehicles. The method comprises: prior to the landing of the unmanned aerial vehicle, an airborne sensor is employed to measure the track ground speed, the air flow air speed, the track slant angle, the yaw angle, the sideslip angle and the track azimuth of the unmanned aerial vehicle in real time; the size and the direction of the wind speed are calculated; the recovery motion points of the unmanned aerial vehicle are calculated according to the wind field information, and the flight course of the unmanned aerial vehicle is regulated; and after the unmanned aerial vehicle enters a recovery course by facing the wind to arrive an expected recovery point, the unmanned aerial vehicle emits a stop instruction, makes unpowered flight, emits a recovery instruction and opens a parachute in order, and the unmanned aerial vehicle slides slowing down and drifts close to an assigned point of fall. The unmanned aerial vehicle parachute landing recovery method based on the accurate measurement of the wind field is able to effectively improve the precision and the reliability of the parachute landing point recovery of the unmanned aerial vehicle on the basis of the measurement of the wind field.

The invention provides an unmanned plane parachuting method which comprises the steps that an unmanned plane preset landing point is selected; a recycling stage is divided into an unpowered flying stage, a gliding stage and a drifting stage; according to measured wind speed and an known plane state, the parking distance between a plane and the preset landing point, the parachute-opening moment and direction are computed quickly; the unmanned plane is controlled to enter a recycling air line; and a ground control station sends stopping and parachute-opening instructions to the plane according to the computing results and the plane state. According to the method, the best stopping and parachute-opening moment of the small unmanned plane during landing on an expected point can be computed, the used flight course and the pitch angle requirement can be computed, cost is low, and safety is high.

The invention discloses a transverse flight energy management method of an unpowered aircraft, and relates to the technical field of aircraft flight control. The method comprises the following steps:calculating a transverse deviation amount according to a transverse position deviation and a transverse speed deviation of an aircraft for a standard flight path, and obtaining a direction cumulant through calculation, wherein the direction cumulant represents a position deviation direction of the aircraft; according to the direction cumulant and a speed deviation amount, calculating a transversespeed guide amount; performing an inertial link and a proportional link on the transverse position deviation to obtain a transverse position guide amount; and performing weighted summation on the transverse speed guide amount and the transverse position guide amount to generate a transverse guide instruction, and controlling transverse flight of the unpowered aircraft. According to the method disclosed by the invention, the transverse speed deviation and the transverse position deviation are comprehensively considered based on the standard flight path; transverse guide is fused with speed control; and excess fuel is consumed in a maneuvering manner transversely, so that over-adjustment is avoided, and energy management of the aircraft is realized.

The invention discloses a trajectory prediction and value filtration method for a rocket launching unpowered flight segment. An instant orbit injection Kepler parameter of a trajectory is calculated according to a set of credible trajectory measurement data or two sets of position-speed vector data, and then trajectory data after the moment is predicted according to the orbit parameter. A trajectory data result is calculated according to multiple sets of the predicted data and credibility weighting, and the result can be used for displaying the trajectory and measuring anomalous point filtration of the trajectory data in real time. By adopting the trajectory prediction and value filtration method for the rocket unpowered flight segment on the basis of a spacecraft orbit determination method, the display effect and precision of the trajectory are significantly improved.

Disclosed is an unpowered flying vehicle, which enables people to fly breezily and arbitrarily like bird in the sky. The unpowered flying vehicle can not only be used for high altitude and stimulated and recreational fly in the recreation ground, but also can be used for long distance fly for flying lovers to realize the dream of flying. The essential method of the invention is that the flying vehicle uses the buoyance of a hydrogen bag to support the flying vehicle and the body of flyer to offset some gravity, namely, uses the addition of the gravity of the flying vehicle and the body of flyer to substract the buoyance of the hydrogen bag, and then gravity difference forms. The flying vehicle is a flying vehicle with gravity difference. The size of the gravity difference is designed according to the purpose of enabling flyer to flap the wings breezily and the driving airscrew and the tail vane fly regularly. Generally, if the gravity difference is small, then the speed is slow but a little effort is needed, on the contrary, if the gravity difference is large, then the speed is fast but great effort is needed, thereby the proper gravity difference can be designed according to the different body force, hobby and skill of flyer. For example, if the gravity difference is large and the flying vehicle can fly, then the flying vehicle is usually used for climbing and gliding with high speed and little effort. According to the design, the flying vehicle can be used for single, two, or more flyers to enjoy the pleasure of flying by oneself or share the pleasure commonly.

The invention discloses an unpowered aircraft trajectory tail end position and attitude smoothing control method comprising the following steps: in step S1, according to precision requirements for aircraft tail end, a position control loop circuit and an attitude control loop circuit of three passageways are respectively designed; in step S2, needed smoothing time is calculated; in step S3, for rudder instruction output of the position control loop circuit and the attitude control loop circuit, linear smoothing operation is conducted according to the smoothing time and smoothing distance, and rudder instructions that needs to be executed are output. The method disclosed in the invention is advantaged by simple principles, easy-to-implement property, high control precision and the like.

The invention discloses an energy management trajectory design method for a powered reusable aircraft, and belongs to the technical field of trajectory design and guidance. The method comprises the following steps: determining parameters of the reentry vehicle, and establishing a flight dynamics model of the reentry vehicle; designing a lateral flight trajectory of the aircraft; designing a longitudinal flight track of the aircraft; and deducing according to the remaining voyage, determining an attack angle, obtaining a whole-course control quantity, and completing trajectory design. The method is suitable for the energy management landing problem when the aircraft is insufficient in energy to return to the airport, the trajectory design thought of the energy management section is that the trajectory is designed firstly, the change of the state quantity is obtained under the condition that longitudinal and lateral movement is known, and therefore the needed control quantity is obtained. An existing unpowered aircraft energy management section trajectory design method is improved, and the method for designing the energy management section trajectory of the powered reusable aircraft is obtained.

The invention belongs to the flight control technology, and proposes a speed tracking control method for an unpowered aircraft, which can expand the speed tracking control range of the unpowered aircraft to improve the ability to adjust the speed, so that the unpowered aircraft can adapt to greater uncertainty. The technical solution adopted by the present invention is: during the flight deceleration process of the unpowered aircraft, when the required resistance is greater than the resistance provided by the maximum opening angle of the resistance plate, the left and right ailerons deflect in the same direction on the basis of the original deflection angle. This method can also be applied to manned fighter jets to improve the survival rate.

The invention provides a piece of grid blade cloth, a paragliding and a windmill, and belongs to the field of layered products. The grid blade cloth comprises an upper layer rope and a lower layer rope, wherein the lower layer rope comprises a plurality of first ropes which are arranged in parallel; the upper layer rope comprises a plurality of second ropes; the second ropes are paved on the upper sides of the first ropes in a cross manner; one end of each blade is adhered between the corresponding first rope and the corresponding second rope; the other end of each blade functions as a moveable end and is positioned below the corresponding first rope. The grid blade cloth can be applied to a plurality of fields such as the surface of the flight umbrella, the blade surface of the windmill rotating horizontally, and water sports shoes disclosed by the invention. The paragliding and the windmill comprise the grid blade cloth, and the paragliding can fly without power and can be also driven to fly by engines. According to the technical scheme, the invention provides the grid blade cloth through which fluid can only pass in one direction, relatively large pressure difference can be formed between two sides of the grid blade cloth, the lifting power can be effectively provided by virtue of the pressure difference, and the grid blade cloth is simple in principle and low in manufacturing cost.

The invention discloses a design method for an approach landing track of an unpowered aircraft. When the flareout landing track is designed, assumed that the height of a flareout landing initial point is known, then, expressions of all track parameters are derived according to a geometrical relationship, and the flareout landing track is designed. In order to design the ideal flareout landing track, the proper height of the flareout landing initial point is found out through an optimization algorithm, track deduction is conducted along the landing track, and therefore the grounding dynamic pressure becomes the ideal grounding dynamic pressure. A deep glide landing track and the ideal flareout landing track form the optimal approach landing track. According to the design method, the aerodynamic force and the aerodynamic moment borne by the aircraft are taken into consideration, and the influences on the design of the landing track of aerodynamic data of deflecting of an aerodynamic control plane and putting of an undercarriage are also taken into consideration. The design method for the approach landing track is simple in principle, computer software is adopted for conducting optimization design, and the design efficiency is improved.

The invention relates to a trajectory design method for energy management of a powered reusable aircraft, which belongs to the technical field of trajectory design and guidance. The method comprises the following steps: determining the parameters of the re-entry vehicle, establishing a flight dynamics model of the re-entry vehicle; designing the lateral trajectory of the flight of the vehicle; designing the longitudinal trajectory of the flight of the vehicle; determining the angle of attack after deduction according to the remaining voyage, and obtaining the whole process control amount to complete the trajectory design. The present invention is applicable to the energy management landing problem when the energy of the aircraft is not enough to return to the airport. The trajectory design idea of ​​the energy management section is to design the trajectory first, and obtain the change of the state quantity under the condition of known longitudinal and lateral motion, so as to obtain amount of control required. The trajectory design method for the energy management section of the unpowered aircraft is improved, and a trajectory design method for the energy management section of the powered reusable aircraft is obtained.

The invention discloses a longitudinal control flight energy management method and a longitudinal control flight energy management system for an unpowered aircraft, electronic equipment and a computer readable storage medium. The longitudinal control flight energy management method comprises the steps of calculating a dynamic guidance quantity, calculating a normal guidance quantity of a longitudinal speed, calculating a normal guidance quantity in a steady phase and calculating a longitudinal guidance command of the aircraft. The longitudinal control flight energy management method and the longitudinal control flight energy management system utilize the current attitude and the range-to-go of the aircraft to estimate current energy of the aircraft, design a control strategy, calculate the longitudinal guidance command of the aircraft, cannot be trapped in solving an optimal solution since the solution of an extremum is not involved in the whole calculation process and can effectively converge energy of the aircraft. The longitudinal control flight energy management method has relatively simple calculation process, and is easy to implement.

The invention discloses a longitudinally controlled flight energy management method, system, electronic equipment and computer-readable storage medium of an unpowered aircraft. The method includes the following steps: calculating the dynamic guide amount, calculating the normal guide amount of the longitudinal velocity, Calculate the normal guidance amount in the stable stage, and calculate the longitudinal guidance command of the aircraft. The present invention estimates the current energy of the aircraft by using the current state of the aircraft and the remaining range, designs the control strategy, and obtains the longitudinal guidance command of the aircraft. During the entire calculation process, it does not involve solving the extreme value, so it will not fall into the optimal solution, and can Effectively converge the energy of the aircraft. The calculation process of this method is relatively simple and easy to implement.

The invention relates to an integrated unpowered aerial photograph adjusting bracket which comprises three connection supporting structures and a camera fixing structure. One ends of the connection supporting structures are connected with a main skeleton of an unpowered aircraft while the other ends are connected with the camera fixing structure, the three connection supporting structures form the tripodal adjusting bracket, and more than two movable degrees of freedom can be realized by the connection supporting structures. The integrated unpowered aerial photograph adjusting bracket has the advantages that a central gravity adjuster is matched with the central gravity of the unpowered aircraft, thereby being high in stability, small in size and light in weight, and the problem about low-frequency disturbance generated during aerial photographing with a suspension type split adjusting bracket is solved.

The invention belongs to a non-electrical variable control system and also belongs to the technical field of ground facility design, and particularly relates to a control method for recycling an unmanned aerial vehicle, which comprises the following steps: when the unmanned aerial vehicle arrives at a predetermined engine parking position, controlling to close an engine, so that the unmanned aerial vehicle is decelerated in unpowered flight; when the unmanned aerial vehicle is decelerated to a predetermined unmanned aerial vehicle recovery area in unpowered flight, whether the flight speed of the unmanned aerial vehicle is smaller than a predetermined safe landing speed or not is judged, and if yes, the unmanned aerial vehicle is controlled to land into the predetermined unmanned aerial vehicle recovery area; if not, the height of the unmanned aerial vehicle is controlled to be kept unchanged, the unmanned aerial vehicle hovers until the flight speed of the unmanned aerial vehicle is smaller than the preset safe landing speed, and the unmanned aerial vehicle is controlled to land in the preset unmanned aerial vehicle recovery area. In addition, the invention relates to a control system for recovering the unmanned aerial vehicle, and the control system comprises an unmanned aerial vehicle unpowered flight deceleration control module and an unmanned aerial vehicle landing control module, and can be used for realizing the control method for recovering the unmanned aerial vehicle.

The invention relates to an unpowered flight mechanism. The unpowered flight mechanism comprises a fuselage, wherein a nose is arranged at the front side of the fuselage, an empennage is arranged at the rear side of the fuselage, the left side and the right side of the fuselage are each provided with a wing, the nose is provided with a leading-in hole for allowing air to enter the fuselage, the fuselage is provided with a communicating hole communicating with the outside, a leading-out hole is formed in the rear side of the fuselage, and a flow guide channel used for enable the leading-in hole, the communicating hole and the leading-out hole to intercommunicate with each other is arranged inside the fuselage. For the unpowered flight mechanism, through the design of the flow guide channel,when the unpowered flight mechanism is ejected to the air and flies, air can enter the fuselage through the leading-in hole, by utilizing the design that the flow guide channel communicates with thecommunicating hole and the exporting hole, air can be diverted and leaves from the position above the fuselage and the tail end of the fuselage simultaneously, thus two different paths of airflow is formed, then the flight stability of the unpowered flight mechanism is stabilized, and the shaking probability of the fuselage is greatly reduced.

The invention relates to an unpowered aerial photography integrated adjustment bracket, which includes a connecting support structure and a camera fixing structure, one end of the connecting supporting structure is connected to the main frame of the unpowered aircraft, and the other end is connected to the camera fixing structure, so that The number of the connecting support structures is three, and the three connecting supporting structures form a tripod adjustment bracket, and the connecting supporting structures can realize more than two degrees of freedom of movement. The beneficial effects of the invention are: the center of gravity adjuster is used to match the center of gravity of the unpowered aircraft, which has the characteristics of high stability, small size and light weight, and solves the problem of low-frequency disturbance during aerial photography of the suspended split adjustment bracket.

The invention discloses a mining intrinsic safety type airship which aims to solve the problems that an existing rotor type unmanned aerial vehicle technology cannot meet the requirements of coal mineunderground explosion prevention and long-time continuous flight. The mining intrinsic safety type airship comprises a central control unit, a helium air bag airship body, a lifting driving unit, anadvancing-steering drive unit and a compressed air storage tank. The airship body is of a helium air bag structure so as to provide suspension lifting force for the airship, and the driving power of the airship is greatly reduced; and the driving unit is driven by compressed air. The airship can realize downwind flow unpowered flight by utilizing ventilation airflow in an underground roadway, andcan also be driven by the driving unit to fly and change the flight attitude. The mining intrinsic safety type airship can meet the requirements of coal mine underground explosion prevention and long-time continuous flight, and can be used for monitoring of various underground environmental parameters and post-disaster rescue under a coal mine.

The invention discloses a terminal guidance method with controllable terminal speed in a three-dimensional space, and belongs to the field of aircraft guidance and control. The implementation method comprises the steps that terminal speed controllable guidance laws are designed in a longitudinal plane and a lateral plane respectively, wherein the terminal speed controllable guidance laws comprise a longitudinal guidance law and a lateral guidance law; the longitudinal guidance law adopts two-section guidance of 'proportional guidance + offset proportional guidance', and the terminal speed is controlled by controlling the switching time of two sections and an offset term coefficient; the lateral guidance law adopts two-section guidance of 'lateral fly-around and proportional guidance', and the terminal speed is controlled by controlling the time of lateral fly-around; according to the terminal speed controllable guidance laws, attack angle and sideslip angle guidance instructions are output, and then terminal speed controllable terminal guidance of an unpowered aircraft in a three-dimensional space under the multi-constraint condition is achieved. The method further has the advantages of high guidance efficiency and strong robustness.

The invention discloses an unpowered aircraft trajectory tail end position and attitude smoothing control method comprising the following steps: in step S1, according to precision requirements for aircraft tail end, a position control loop circuit and an attitude control loop circuit of three passageways are respectively designed; in step S2, needed smoothing time is calculated; in step S3, for rudder instruction output of the position control loop circuit and the attitude control loop circuit, linear smoothing operation is conducted according to the smoothing time and smoothing distance, and rudder instructions that needs to be executed are output. The method disclosed in the invention is advantaged by simple principles, easy-to-implement property, high control precision and the like.

The invention relates to a reentry stage aircraft attitude control method based on an exponential time-varying second order sliding mode, belonging to the technical field of aircraft control. According to the reentry stage aircraft attitude control method, a plane symmetric unpowered aircraft model is taken as an object, feedback linearization is carried out on an affine nonlinear system of an aircraft, and the attitude control problem of the aircraft when reentering into the atmospheric layer is studied. The aircraft provides operating force and operating torque only through a pneumatic control surface. A control surface deflection angle signal [delta e delta a delta r]T is given through the designed control law, so that an attitude instruction omega c=[alpha c beta c mu c]T given by a guidance loop can be effectively tracked, the attitude angle tracking error can be guaranteed to be asymptotically converged, and strong robustness is generated for tremendous environment change, uncertain pneumatic parameters and external disturbance and the like in the reentry process. Meanwhile, the control law in the method only has integral of a switching function, so that the reaching stage of a sliding mode surface is eliminated, the control quantity is enabled to be a continuous signal, the buffeting phenomenon is effectively reduced, and good control accuracy is achieved.

Provided are blade-like grid cloth and a manufacturing method therefor, and a paraglider and a windmill made of same, falling within the field of laminar products. The blade-like grid cloth comprises an upper thread rope layer (201) and a lower thread rope layer (202), wherein the lower thread rope layer (202) comprises a plurality of first thread ropes which are arranged side by side; the upper thread rope layer comprises a plurality of second thread ropes; the plurality of second thread ropes are crosswise laid at an upper side of the plurality of first thread ropes; and one end of each blade (102) is adhered between the first thread ropes and the second thread ropes, and the other end of each blade is a movable end and is located below the first thread ropes. The blade-like grid cloth can be applied to a plurality of fields, such as paraglider fabric, windmill blade surfaces capable of rotating horizontally and aquatic sport shoes, etc. The paraglider and the windmill respectively comprise the blade-like grid cloth. The paraglider can fly without power and can also be driven to fly by an engine. The technical solution provides a blade-like grid cloth through which fluid can only pass in one direction, so that a relatively great pressure difference can be formed between two sides of the blade-like grid cloth, and the pressure difference can effectively provide a raising force with a simple principle.

The invention discloses a large-diving-depth underwater unpowered aircraft transmitting system and method. The transmitting system comprises an underwater autonomous measuring and control system, a transmitting cylinder with a front cover, a catapult arranged in the transmitting cylinder, and an aircraft arranged in the transmitting cylinder, wherein the transmitting cylinder, the catapult, the aircraft and the measuring and control system integrally adopt an axial deflection design; compared with a mass center, the axial buoyant center is closer to the front cover of the transmitting cylinder; the transmitting system is fixed to an underwater platform, after the transmitting system is separated from the underwater platform, the situation that upward buoyance is greater than the sum of gravity and floating resistance is changed into the situation that the upward buoyance and the sum of the gravity and floating resistance gradually tend to be balanced; the aircraft is fixed on one side of a sealing bottom plate in the transmitting cylinder, and the other side of the sealing bottom plate is connected with the catapult; and after the front cover is opened, the catapult produces thrust to push the aircraft to slide in the direction from the transmitting cylinder to the front cover, and the aircraft slides from the transmitting cylinder. According to the large-diving-depth underwater unpowered aircraft transmitting system disclosed by the invention, the maximum transmitting depth of the transmitting system is not less than 200 meters; and in the transmitting system, the aircraft does not bear water pressure limit directly, so that the aircraft is low in design condition requirements, and high in portability.

The invention discloses a trajectory prediction and value filtration method for a rocket launching unpowered flight segment. An instant orbit injection Kepler parameter of a trajectory is calculated according to a set of credible trajectory measurement data or two sets of position-speed vector data, and then trajectory data after the moment is predicted according to the orbit parameter. A trajectory data result is calculated according to multiple sets of the predicted data and credibility weighting, and the result can be used for displaying the trajectory and measuring anomalous point filtration of the trajectory data in real time. By adopting the trajectory prediction and value filtration method for the rocket unpowered flight segment on the basis of a spacecraft orbit determination method, the display effect and precision of the trajectory are significantly improved.