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79 results about "Free flight" patented technology
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Free flight is a developing air traffic control method that uses no centralized control (e.g. air traffic controllers). Instead, parts of airspace are reserved dynamically and automatically in a distributed way using computer communication to ensure the required separation between aircraft. This new system may be implemented into the U.S. air traffic control system in the next decade. Its potential impact on the operations of the national airspace system is disputed, however.
Trajectory detection and feedback system
ActiveUS20070026975A1Improve consistencyImprove performanceSki bindingsGymnastic exercisingFree flightMedicine
Owner:PILLAR VISION
Trajectory detection and feedback system
ActiveUS7094164B2Improve consistencyImprove performanceIndoor gamesGymnastic exercisingFree flightMedicine
A trajectory detection and feedback system is described. The system is capable of detecting one or more moving objects in free flight, analyzing a trajectory of each object and providing immediate feedback information to a human that has launched tile object into flight, and / or one or more observers in the area The feedback information may include one or more trajectory parameters that the human may use to evaluate their skill at sending the object along a desired trajectory. A non-intrusive machine vision system may be used to evaluate trajectory parameters for a basketball shot at a basketball hoop by a player. After the system has evaluated a plurality of shots by the player, the system may provide 1) a diagnosis of their shot consistency, 2) a prediction for improvement based upon improving their shot consistency and 3) a prescription of actions for improving their consistency.
Owner:PILLAR VISION
Trajectory detection and feedback system
ActiveUS20070026974A1Improve consistencyImprove performanceSki bindingsGymnastic exercisingFree flightMedicine
Owner:PILLAR VISION
Trajectory detection and feedback system
InactiveUS8622832B2Improve consistencyImprove performanceGymnastic exercisingCharacter and pattern recognitionFree flightSimulation
A disclosed device provides a trajectory detection and feedback system. The system is capable of detecting one or more moving objects in free flight, analyzing a trajectory of each object and providing immediate feedback information to a human that has launched the object into flight, and / or one or more observers in the area. In a particular embodiment, a non-intrusive machine vision system that remotely detects trajectories of moving objects may be used to evaluate trajectory parameters for a basketball shot at a basketball hoop by a player. The feedback information, such as a trajectory entry angle into the basketball hoop and / or an entry velocity into the hoop for the shot, may be output to the player in an auditory format using a sound projection device. The system may be operable to be set-up and to operate in a substantially autonomous manner.
Owner:PILLAR VISION
Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft
ActiveUS20130161447A1Avoid problemsSimple and economical apparatusArresting gearUnmanned aerial vehiclesFree flightFlight vehicle
An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus having one or more rails which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component on the aircraft engages the rails. The teeth restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station. Connections for refueling, recharging, and / or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight.
Owner:AEROVEL CORP
Apparatus and method for identifying and analyzing the free flight dynamics of a body
ActiveUS20130073247A1Reduce impactLess expensiveGymnastic exercisingNavigation by speed/acceleration measurementsFree flightAccelerometer
An apparatus for analyzing free flight of a body including an inertial measurement unit having at least one accelerometer continuously measuring three orthogonal axes of acceleration and outputting data representative thereof and a processing unit operably receiving the data and determining three components of an angular velocity of the body during free flight.
Owner:RGT UNIV OF MICHIGAN
Multifunctional in-orbit maintenance robot system
InactiveCN109454633ACompact structureImprove reliabilityProgramme-controlled manipulatorGripping headsDegrees of freedomEngineering
The invention belongs to the field of robots, and discloses a multifunctional in-orbit maintenance robot system. The system comprises a free flight robot platform, a mechanical arm and a plurality ofend effector systems, wherein a plurality of holes are formed in the free flight robot platform; the mechanical arm comprises two capture arms and an elbow joint, each capture arm comprises a rotary degree-of-freedom joint, a first connection joint, a deflection degree-of-freedom joint, a second connection joint, a pitching degree-of-freedom joint and arm rods, and the rotary degree-of-freedom joint, the first connection joint, the deflection degree-of-freedom joint, the second connection joint, the pitching degree-of-freedom joint and the elbow joint are all of a two-section type rotating rodstructure; and each section of rod piece of the elbow joint is connected with the other end of one arm rod. According to the system, travalling positioning of the mechanical arm can be realized, theworking orientation of the mechanical arm can be expanded, and the mechanical arm can be mounted on a spacecraft, an astronautic aircraft, a space station, a satellite and other space aircrafts as a standard device for in-orbit maintenance.
Owner:HUAZHONG UNIV OF SCI & TECH
Variable pneumatic layout structure for projectile body
ActiveCN104089546AMeet static stability requirementsReduce the impactProjectilesFree flightControl system
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY +1
Unmanned aerial vehicle trajectory generation method based on flight corridor and Bezier curve
InactiveCN112068588AGuaranteed accuracyCollision will notPosition/course control in three dimensionsFree flightControl theory
The invention discloses an unmanned aerial vehicle trajectory generation method based on a flight corridor and a Bezier curve, and belongs to the field of robot motion planning. According to the trajectory generation method, a robot can meet the motion constraint of continuous acceleration on the premise that obstacle avoidance is guaranteed, and the average speed is high. The method comprises thefollowing specific steps: obtaining surrounding map point cloud information through a depth camera sensor / laser radar sensor or global known information; constructing a rasterized obstacle map; planning a collision-free and optimal path by using an A* algorithm; generating a collision-free flight corridor capable of moving by a robot based on the A* planned path; and finally, generating a Beziercurve in the flight corridor for the robot to move. A series of nodes on a safety path are converted into a series of convex geometries (corridor blocks) in a mode of generating a safety corridor, sothat the information amount is greatly increased, and the modeling accuracy is ensured.
Owner:ZHEJIANG UNIV
Autonomous media capturing
ActiveUS20200014848A1Simple processGood photoInput/output for user-computer interactionTelevision system detailsSocial circleFree flight
Owner:GOVE ROBERT JOHN
Method for pre-estimating flight path of wind tunnel free flight test model
ActiveCN105258906ASimple methodEfficient methodAerodynamic testingComplex mathematical operationsRunge–Kutta methodRunge–Kutta methods
The invention provides a method for pre-estimating flight path of a wind tunnel free flight test model, and the method comprises the steps: 1, obtaining an attack angle - mechanics coefficient table of a flight model; 2, setting the initial attack angle value theta0 of a free flight test, a transmission position, and an initial transmission speed, obtaining the mechanics coefficient at the initial attack angle value theta0 through linear interpolation, and enabling the initial attack angle value theta0 and the corresponding mechanics coefficient to serve as an initial transmission parameter D0; 3, calculating and obtaining pre-estimated flight path data through a Runge-Kutta method after flight at the transmission position; 4, repeatedly carrying out the steps 2 and 3 when the pre-estimated flight path data does not meet the testing requirements, obtaining a new pre-estimated flight path, and carrying out step 4 till the new pre-estimated flight path meets the testing requirements. The method pre-estimates the flight path of free flight of a model in a wind tunnel, enables the flight path to stay for longer tie in an observation region, and obtains more effective information during testing.
Owner:CHINA ACAD OF AEROSPACE AERODYNAMICS
Free flight supporting device in full wingspan flying wing body freedom flutter wind tunnel test
InactiveCN110686854AObvious pitching/heaving motion phenomenonAvoid influenceAerodynamic testingFree flightClassical mechanics
The invention provides a free flight supporting device in a full wingspan flying wing body freedom flutter wind tunnel test. The device comprises a cross beam, a pulley block and a steel shaft. A flying wing model is connected with the pulley block through the cross beam, the cross beam is connected with the pulley block through a bearing, the relative rotation of the pulley block and a beam is not affected, the pitching degrees of freedom of a flying wing is released in the experiment process, the pulley block is driven to move up and down through the cross beam, the sinking and floating degrees of freedom of the model is released, and meanwhile, a displacement limiter is further arranged and used for limiting the up-and-down movement of the model and preventing the model from being dispersed or damaged due to violent oscillation. The flying wing and the pulley block are connected by the cross beam, so that the frictional resistance is reduced, a supporting spring is not required to be designed independently, the sinking and floating degrees of freedom and the pitching degrees of freedom can be released simultaneously, the device has the advantage of easiness in implementation, and the influence of the bearing rigidity introduced by the supporting spring on an experimental result is avoided; and a designed supporting device can simulate the real flying state of the flying wingto the maximum extent and can reduce experimental errors caused by frictional resistance.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Rotorcraft-assisted systems and methods for launching and retrieving a fixed-wing aircraft into and from free flight
The present disclosure describes various systems and methods configured to: launch a fixed-wing aircraft from a moving object into free, wing-borne flight using a multicopter; retrieve the multicopter after fixed-wing aircraft launch using a retrieval winch; retrieve the fixed-wing aircraft from free, wing-borne flight back onto the moving object using the multicopter; and retrieve the multicopter after fixed-wing aircraft retrieval using the retrieval winch.
Owner:HOOD TECH CORP
Modal test method for carrier rocket
ActiveCN110907208AImprove accuracyReduce distractionsStructural/machines measurementFree flightElement model
The invention provides a modal test method for a carrier rocket, and the method comprises the steps: obtaining a first-order vibration mode of the carrier rocket in a free flight state at a zero-second moment according to a finite element model, and taking an intersection point of the first-order vibration mode of the carrier rocket and the central line of the carrier rocket as a node position; hosting the carrier rocket with the circumferential outer side, corresponding to the node position, of the carrier rocket as a hoisting point, and arranging an elastic lengthening structure between a rocket body of the carrier rocket and the hoisting wrapping belt so as to eliminate the influence of the bending rigidity of the hoisting beam on the bending rigidity of the rocket body; and obtaining modal parameters of the carrier rocket in a hoisting state. According to the modal test method provided by the invention, the influence of the rigidity of the hanging beam on rocket modal parameters can be reduced, and the reliability of a rocket modal test result is improved.
Owner:BEIJING LANDSPACETECH CO LTD
Low-speed wind tunnel horizontal free flight model attitude measurement method
The invention is applicable to the technical field of wind tunnel tests, and provides a low-speed wind tunnel horizontal free flight model attitude measurement method. The method comprises the following steps: S10, placing an aircraft model in a wind tunnel test section, and arranging a plurality of cameras at the tops of two sides of the aircraft model and outside the wind tunnel test section; S20, calibrating the plurality of cameras at the same time; S30, establishing a world coordinate system and a body axis coordinate system; S40, setting a plurality of mark points on the aircraft model, and obtaining position information of the plurality of mark points in the world coordinate system; and S50, calculating an attitude angle and an airflow angle of the aircraft model according to the position information of the plurality of mark points in the body axis coordinate system. The attitude measurement method provided by the invention can be suitable for research of horizontal free flight of different models of aircrafts in the wind tunnel, has good versatility, is simple to use and operate, can be popularized to other low-speed wind tunnels, and has good engineering application prospects.
Owner:LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
Inertia drop point control closed-loop guidance method under solid carrier rocket exhaustion shutdown mode
ActiveCN112287525AHigh precisionImprove robustnessGeometric CADDesign optimisation/simulationFree flightClassical mechanics
The invention relates to an inertia drop point control closed-loop guidance method in a solid carrier rocket depletion shutdown mode, and the method comprises the steps of deducing an analytical solution of an instantaneous orbit drop point related derivative in a free flight process according to the differential derivative relation of an instantaneous orbit drop point, and building a mapping relation between a current point and the orbit drop point; determining the current acceleration instruction vector according to the current remaining flight time of the solid carrier rocket, and it is guaranteed that the instantaneous orbit drop point moves to the target point when an engine of the solid carrier rocket is exhausted and shut down, the carrier rocket continues to slide to the target drop point along the Kepler orbit, and meanwhile the invention has very high guidance precision.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Method and apparatus for automated launch, retrieval, and servicing of a hovering aircraft
ActiveUS20140054415A1Light and portableArresting gearRemote controlled aircraftFree flightFly control
Owner:AEROVEL CORP
Embedded wind tunnel free flight test model pose acquisition method
ActiveCN112577706ARemove pulsation interferenceRemove high frequency vibration interferenceAerodynamic testingFree flightFlight test
The invention discloses an embedded wind tunnel free flight test model pose acquisition method, and relates to the technical field of flight tests. The embedded wind tunnel free flight test model poseacquisition method comprises the steps of: carrying out the interception of inertial sensor data according to a preset rule to obtain test effective data which comprises triaxial accelerometer data and triaxial gyroscope output data; performing low-pass filtering on the triaxial accelerometer data to obtain first data, and removing high-frequency vibration interference; performing band elimination filtering on the first data and the output data of the three-axis gyroscope to obtain second data, and removing pulsation interference of a pneumatic airflow; and carrying out recursive pose calculation on the basis of the second data to obtain six-degree-of-freedom pose information of the aircraft model within effective time in the test process. The embedded wind tunnel free flight test model pose acquisition method can improve the test precision for the application scene of the wind tunnel free flight test.
Owner:CHINA ACAD OF AEROSPACE AERODYNAMICS
Degree of freedom release device of wind tunnel free flight experiment
ActiveCN107449581ASimple structureEasy to installSustainable transportationAerodynamic testingFree flightClassical mechanics
The invention discloses a degree of freedom release device of a wind tunnel free flight experiment. The degree of freedom release device comprises a supporting rod and a degree of freedom release joint; the supporting rod is fixedly installed at the center of a wind tunnel test experiment platform; the degree of freedom release joint is installed at the center of gravity of the belly of an aircraft model; and the degree of freedom release joint and the aircraft model are fixed together through screws, and then are connected with a supporting base by bearings. With the degree of freedom release device of the wind tunnel free flight experiment of the invention adopted, single-degree of freedom release of rolling, pitching and yawing of the aircraft model in the wind tunnel free flight experiment and two-degree of freedom release of pitch rolling, yaw rolling and pitch yawing of the aircraft model in the wind tunnel free flight experiment can be realized, and the three-degree of freedom release of the aircraft model can be realized, and the release angle of the pitching and rolling ranges from +35 degrees to -35 degrees, and the yawing of the aircraft model can achieve release ranging from +180 degrees to -180 degrees. The degree of freedom release device of thee invention has the advantages of simple structure, capable of realizing of the release of a plurality of kinds of degrees of freedom, small interference and simple installation and adjustment method.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Method for eliminating rigid displacement in airplane deformation under free flight trim load
The invention discloses a method for eliminating rigid displacement in airplane deformation under a free flight trim load. Basic feature comprises: applying any reasonable statically determinate constraint to the structural finite element model with the balancing load effect; calculating to obtain structural displacement data by using engineering commercial software; reconstructing a displacementfield on a selected area by means of a consistent tight support radial basis interpolation function, constructing a deformation gradient matrix, performing extreme decomposition operation on the deformation gradient matrix to obtain a product of a symmetric matrix and an orthogonal matrix, the symmetric matrix describing the extension of the structure, and the orthogonal matrix reflecting the rotation of the structure; and according to the rigid rotation matrix obtained by the extreme decomposition, constructing the overall rigid displacement of the structure, and then eliminating the overallrigid displacement of the structure from the total displacement, so that the real elastic displacement of the free structure is obtained. According to the method, the basic characteristics of the total rigid matrix of the structure are not changed, the operand is small, the calculation is simple, and the overall rigid displacement of the structure caused by statically indeterminate constraint setting in the static deformation calculation process can be efficiently eliminated.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Safe mail delivery by unmanned autonomous vehicles
Operation of Unmanned Autonomous Vehicles (UAVs) around human population requires the utmost level of safety. Trackpath pre-computed navigation paths and Free flight corridor protection systems reduce the possibility of injuring humans during flight, but at the point of delivery the drone must, by necessity, come down to level of and near humans. This invention teaches the system and method of a personal household mail system that minimizes human exposure to the delivery UAV, provides a method of verifying that the addressee is correct, and optionally secures the mail until it is picked up by the designated recipient.
Owner:BIRKET IP HLDG INC
Aircraft control-surface-free flight control method based on synthetic dual-jet flow field control
The invention relates to an aircraft control-surface-free flight control method based on synthetic dual-jet flow field control. According to the method, an autonomous and controllable synthetic dual-jet exciter is applied to the field of aircraft flight control, the synthetic dual-jet exciter is arranged at a preset position according to different aircraft layouts, flight states and control requirements, a piezoelectric vibrator repeatedly compresses an expansion cavity under the control of a power supply controller, and the synthetic dual-jet exciter and the piezoelectric vibrator are combined. Periodically-blown and sucked synthetic dual-jet is formed at an outlet, the synthetic dual-jet is utilized to change a streaming flow field of the aircraft and reconstruct surface pressure distribution, and a preset control strategy is adopted to achieve the purpose of controlling the attitude of the aircraft. According to the method, when the aircraft is subjected to flight control, any mechanical structure does not need to be operated, so that the invisibility and the aerodynamic configuration of the aircraft are prevented from being damaged, the mechanical wear is reduced, and the method has extremely high application value; the method is suitable for replacing the conventional control surface of the aircraft, and can also be matched with the conventional control surface at the same time or in a time-sharing manner.
Owner:NAT UNIV OF DEFENSE TECH
Unmanned aerial vehicle cluster autonomous formation control method imitating migrant bird migration behavior
The invention discloses an unmanned aerial vehicle cluster autonomous formation control method imitating a migrant bird migration behavior. The method comprises the implementation steps of 1, initializing an unmanned aerial vehicle cluster; 2, determining a lead aircraft; 3, determining a leader relationship among the unmanned aerial vehicles; 4, enabling the lead aircraft to judge whether obstacles exist in the front flight environment or not; 5, performing a barrier-free flight mode in the environment; 6, performing an obstacle flight mode in the environment; 7, updating a control instruction of the unmanned aerial vehicle pilot; and 8, performing formation reconstruction. The method aims at achieving autonomous formation flight of multiple unmanned aerial vehicles and simulating cluster behaviors shown by the migrant birds during long-distance migration, is used for designing an unmanned aerial vehicle cluster formation control strategy, improves the robustness of an unmanned aerial vehicle cluster and the adaptability to the environment, and effectively improves the autonomous ability level of the unmanned aerial vehicles.
Owner:BEIHANG UNIV
Free flight analog simulation platform
The invention relates to a free flight analog simulation platform. The free flight analog simulation platform comprises an analog setting system, a data information system, a permission setting system, and an actual scene analog system. The implementation method of the platform includes the steps that first, a flight rule is designed, wherein in the actual scene analog module, an airplane flight process model is built on the basis of the core through that the distance is equal to the number generated when the speed is multiplied by the time; a conflict avoidance rule is designed, wherein in the actual scene analog module, the courses of airplanes are obtained through an equation of motion of the airplanes, the course included angle is calculated, and which encounter condition happens to the airplanes is judged so that corresponding avoidance measures can be taken. The free flight analog simulation platform is mainly used for the teams researching free flight to collect data and provides relevant data for free flight analog, analog logs are output, the analog data can be visually displayed for users, the users can conveniently calculate collision risk in free flight so that factors for influencing safety of free flight can be researched, and technical support is provided for achieving free flight.
Owner:CIVIL AVIATION UNIV OF CHINA
Method of measuring micro thrust eccentricity of solid rocket engine without constraint condition
PendingCN111350616AReduce mistakesRocket engine plantsSustainable transportationFree flightGyroscope
The invention relates to a method of measuring micro thrust eccentricity of a solid rocket engine without constraint condition. The method comprises the following steps of configuring a certain load to the engine, wherein the flight of the engine is limited at a certain height and speed range; measuring and recording data through a gyroscope sensor in a free flying state; and calculating the processed data to obtain micro thrust eccentricity of the engine. Test data of an aircraft and thrust of the engine are established in a rectangular coordinate system of the aircraft. In the coordinate system, the thrust eccentricity is calculated finally by solving components of the thrust of the engine in three coordinate axis directions.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Electromagnet suspension throwing device for free flight test of hypersonic wind tunnel model
The invention discloses an electromagnet hanging and throwing device for a free flight test of a hypersonic wind tunnel model. The device comprises a mounting support plate, a mounting base and an adsorption electromagnet which are sequentially connected from top to bottom, wherein the upper end of the mounting support plate is fixed on an upper attack angle mechanism of a hypersonic wind tunnel test section attack angle mechanism, and the lower end of the adsorption electromagnet adsorbs a model. The device also comprises a driver which is fixed on the mounting support plate, the model fixingdevice is fixed on the mounting base, and the driver controls the model fixing device to clamp or release the model. During test preparation, a power supply for adsorbing the electromagnet is turnedoff, and the model fixing device clamps and fixes the model; before testing, a power supply of the adsorption electromagnet is turned on, the model fixing device is withdrawn, and the adsorption electromagnet adsorbs and fixes the model; in the test process, the electromagnet is adsorbed to power off and release the model. The device is compact in structure, reasonable in layout, good in stabilityand high in reliability, and can meet the requirement of quickly putting the model in the free flight test process of the hypersonic wind tunnel model.
Owner:中国空气动力研究与发展中心超高速空气动力研究所
Wind tunnel free flight test model pose measurement system and measurement method
PendingCN112014062ARich and effective aerodynamic dataAccurate analysisAerodynamic testingFree flightAngular velocity
The invention discloses a wind tunnel free flight test model pose measurement system. The system comprises an on-site pose capture subsystem, a remote pose resolving subsystem and a model recovery subsystem. The on-site pose capture subsystem is used for measuring the angular velocity and the acceleration of a wind tunnel free flight test model by utilizing an inertial sensor; the remote pose resolving subsystem is used for resolving the angular velocity and acceleration data of the wind tunnel free flight test model measured by the on-site pose capturing subsystem in real time or off line toobtain the pose information of the wind tunnel free flight test model; and the model recovery subsystem is used for recovering the wind tunnel free flight test model and the on-site pose capture subsystem when the test is finished. The invention further discloses a measurement method of the measurement system. According to the invention, the problems that a traditional high-speed photographing method for the wind tunnel free flight test is small in pose information acquisition freedom degree and short in effective data length are solved, and the system is low in cost and can be repeatedly used.
Owner:CHINA ACAD OF AEROSPACE AERODYNAMICS
Trajectory tracking control method for space five-degree-of-freedom free flight mechanical arm
ActiveCN110641738AHigh precisionHigh speedCosmonautic vehiclesSpacecraft guiding apparatusFree flightGeneralized forces
The invention discloses a trajectory tracking control method for a space five-degree-of-freedom free flight mechanical arm. The trajectory tracking control method can solve the accurate problem that aspace object is captured and manipulated by the five-degree-of-freedom space free-flight mechanical arm installed on a spacecraft. The trajectory tracking control method mainly comprises the following four points that 1), a D-H method is applied to establish a forward kinematic model of the mechanical arm; 2) a Lagrange equation is applied to establish a dynamical model of the mechanical arm; 3),a Jacobi transpose matrix and a PD controller are combined to introduce a generalized force vector; and 4), Simulink software is used for constructing a simulation model according to a dynamical differential equation. According to the method, the kinematic and dynamical models of the mechanical arm are constructed at the same time, and the method of the Jacobi transpose matrix in combination withthe PD controller is applied, so that the problem that a kinematic control method applied widely at present cannot well track and control the space high-speed high-precision mechanical arm is effectively solved.
Owner:DALIAN UNIV OF TECH
Fixed-wing flying device configured to fly in multiple directions
A fixed-wing flying apparatus, aircraft, airplane or device is provided which is capable of stably gliding in more than one direction such as backwards, frontward or sideways. The device comprises a plurality of wings arranged around the center of area and defining a space therebetween. Each wing includes an outwardly protruding wall along an outer edge of the wing, which disrupts airflow over the wing flying in front so it is less effective than the wing flying behind, facilitating temporary or long term sustainable speed-seeking glide stability in more than one forward direction without any trim or center of gravity adjustment. The plurality of wings can include two wings, three wings forming a triangle, or four wings forming a square or rectangle. The aircraft can be unpowered, powered, free-flight or controlled. A one-front airplane can also be constructed with very relaxed yaw stability.
Owner:ZONGKER JAMES DEAN
Deceleration separation device
The invention discloses a deceleration separation device which comprises a deceleration parachute cabin, a combination actuator, a deceleration parachute pack, a battery box and a sub-machine controlpanel. The deceleration parachute bay comprises a parachute bay body and a parachute bay cover; a first port of the parachute bay body is clamped with the parachute bay cover; a second port of the parachute bay body is connected with a sub-aircraft protection cylinder of the unmanned aerial vehicle through a first connecting part; the assembling actuator is fixedly arranged in the parachute bay body; one end of the combined actuator is a parachute throwing device and is connected with the parachute cabin cover; the other end of the combined actuator is an explosive bolt and is connected with atransition joint of the unmanned aerial vehicle; the deceleration parachute pack is arranged in the deceleration parachute cabin and connected with the parachute cabin cover and the assembling actuator through second connecting parts. The battery box is arranged in the parachute bay body and is respectively connected with the parachute throwing device and the explosive bolt; and the sub-machine control panel is arranged in the parachute bay body and is in communication connection with the parachute throwing device and the explosive bolt respectively. The device can be separated from the aircraft, the weight during free flight is reduced, and the cruising ability of the aircraft is improved.
Owner:BEIJING ZHZ TECH
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