38results about How to "Increase flight altitude" patented technology

The invention provides an overweight compensating guidance method and trajectory reshaping guidance method conducting correction based on a pseudo-spectral trajectory optimization result, and belongsto the field of the space technology, the weapon technology and guidance control. The overweight compensating guidance method and trajectory reshaping guidance method specifically comprises the stepsthat firstly, a fight model is established, and guided missile pneumatic parameters and atmosphere model parameters are determined; secondly, a guided missile motion equation is established, and an optimal control problem is established; thirdly, the pseudo-spectral method is used for solving the optimal control problem; fourthly, polynomial fitting and other manners are used for fitting the pseudo-spectral optimal result; and fifthly, according to the pseudo-spectral optimal result, the typical trajectory reshaping guidance rule and the typical gravity compensation guidance rule are corrected. The overweight compensating guidance method and trajectory reshaping guidance method has the advantages that the final velocity of a guided missile is increased, and the attacking effect of the guided missile is greatly improved; through fitting of the pseudo-spectral optimal result, the guidance rule is segmented, the guided missile flight speed is increased in a front section, the guidance parameters are adjusted in a rear section, and the guidance rule conforms to the fall angle constraint; and the black hole phenomenon of the typical gravity compensation guidance rule is avoided, and important significance is achieved for actual application.

The invention relates to a multielement seeding combustion explosion type rainfall-increasing and anti-hail rocket. In the rocket, one end of a safety system (2) is connected with a flame bullet seeding catalyst system (1), the other end is connected with the front end of a solid motor (3); the back end of the motor (3) sticks to an empennage; four catalyst seeding holes are evenly distributed in the middle part of a nozzle (5), a plurality of flame bullets (12) are sleeved together to be arranged in a shell (15), safety fuses (16) are arranged in the centre bores of the flame bullets (12), a propelling medicine (13) is filled to one end of each flame bullet (12); a cladding medicine block(9) is filled in the threaded connection section capsule of the shell (15), an ignition medicine package (8) is arranged in the counter bore of the cladding medicine block(9), and the ignition wire of the ignition medicine package passes through the centre bore of the nozzle (5). The invention adopts the flame bullet burning mode that catalyst is burnt and seeded continuously and a plurality of flame bullets are thrown along the parent trajectory, for seeding the catalyst, thus requiring that the flame bullets are thrown reliably and the burning is stable. The flame bullets of the invention adopt casting moulding for structure design, the technology is easy and stable, and the flame bullets are easy for the batch production.

The invention discloses an aircraft structure capable of repeatedly entering and exiting from water. The aircraft structure comprises a fuselage and a head component, wherein the fuselage is providedwith telescopic wings and a rotatable empennage, and a fuel system is installed in the fuselage; the head component is arranged at a head of the fuselage; the head component includes an air storage tank, a cavitator connected with the air storage tank and a pusher connected with the cavitator; the cavitator includes an annular fixed part with a front-end vent hole and a control moving part movingalong the front-end vent hole; the pusher drives and enables the moving part to move so as to close or open the front end vent hole; the head component further includes a vent ring hole connected withthe air storage tank; and the pusher drives the annular fixing part to move so as to close or open the vent ring hole. The aircraft structure can fly in the air, does not generate a too high resistance to underwater diving, and can repeatedly enter and exit from water.

Belonging to the technical field of aircraft design, the invention discloses a deformable lift and buoyancy integrated aircraft aerodynamic configuration. The aerodynamic configuration has a single-fuselage, tandem wing and horizontal tail-free layout, double vertical tails tilt outward certain angle, wings are located at the upper part of the fuselage, front wings and back wings have the same design. The fuselage can produce radial deformation, the fuselage is divided into a front section, a middle section and a back section, and the three sections of the fuselage deform respectively. Because of the introduction of dynamic lift, the aircraft has higher flight height than an airship, greater flight speed, and stronger wind resistant performance and maneuverability; and due to the introduction of static lift, the aircraft has loading capacity far higher than that of conventional high-altitude unmanned aerial vehicles, and has higher structural height and strength. In the process of vertical rising and fall, the fuselage can produce corresponding deformation to change the fuselage volume so as to guarantee the fuselage lift and the aircraft weight balance. With no need for ballonet and ancillary equipment in conventional airships and lift and buoyancy integrated aircrafts, the deformable lift and buoyancy integrated aircraft aerodynamic configuration provided by the invention can reduce the aircraft weight and decrease the ground parking volume of the aircraft.

The invention provides a large or ultra-large compact hard or semi-hard high-speed large-voyage airship. The airship comprises an air bag. A nacelle is arranged on the inner side of the bottom of theair bag. A flight control and propelling device is arranged at the rear end of the airship. A power system for driving the airship to advance and driving all devices to work is arranged in the nacelle. The power system is an oxy-hydrogen fuel battery pack. Multiple liquid containing cavities are formed in the nacelle. Water outlets of the power system communicate with the liquid containing cavities. The liquid containing cavities are provided with controllable drainage devices. The air bag is filled with helium gas or mixed gas of helium gas and hydrogen gas. Multiple elastic connecting piecesare arranged in the air bag. Part of a bag body of the air bag is drawn together through the elastic connecting pieces to form a buffer air bag part. Through collection and drainage of water generated by the oxy-hydrogen fuel battery pack, gravity center adjustment and control over the flight height and take-off and landing of the airship are achieved, an auxiliary air bag arranged in an existingairship air bag is saved, and the size and flight resistance of the whole airship can be greatly reduced.

The invention relates to an intelligent unmanned aerial vehicle for take-out delivery based on the Internet of Things. The intelligent unmanned aerial vehicle comprises a main body and a storage mechanism; the storage mechanism comprises a storage box, the two mounting assemblies and the two obstacle detection assemblies; each obstacle detection assembly comprises a driving unit, a sliding rod, arack, a driven wheel, a radar and a plurality of driven teeth; two direction adjusting assemblies are arranged in the storage box; each direction adjusting assembly comprises a second motor, a bufferblock, a second driving shaft, a sliding block, a supporting rod and a hinge block. The intelligent unmanned aerial vehicle for take-out delivery based on the Internet of Things has the advantages that: a cover plate is driven to rotate through the direction adjusting assemblies, so that a closed environment is formed in the transportation process of the storage box and food is prevented from being bitten by birds and flies, and health and safety of food are guaranteed; obstacle information in front is detected through the obstacle detection assemblies and the unmanned aerial vehicle can fly over obstacles for take-out delivery, so that smooth flight of the unmanned aerial vehicle and smooth takeout delivery are guaranteed, and the practicability of the equipment is improved.

The invention discloses an ornithopter, particularly relates to an operation method of the ornithopter, aims to provide an ornithopter with little power loss, large flight distance and high speed, and provides an operation method of the ornithopter which is simple to operate, high in flight efficiency and little in power loss. The ornithopter comprises a body (1), buoyancy wings (2), power wings (3), a flapping wing driving device, an empennage and a control system, wherein a plurality of wing holes (5) are formed in the buoyancy wings (2) and the power wings (3), and opening and closing devices are arranged on the buoyancy wings (2) and the power wings (3). According to the operation method, the wing holes (5) in the power wings (3) are closed, and the wing holes (5) in the buoyancy wings (2) are opened simultaneously; the wing holes (5) in the power wings (3) are opened, and the wing holes (5) in the buoyancy wings (2) are closed simultaneously, and periodic cycling is performed. The ornithopter and the operation method of the ornithopter are applied to the technical field of aircrafts.

The invention discloses an aircraft detection method. A detection device is arranged in the aircraft, and the detection device detects the distance or the vertical height between the aircraft and a detected area. A planar array photoelectric sensor is arranged in the detection device, the detection device acquires the distance or the vertical height between a below detected area in front of the aircraft and the aircraft based on the planar array photoelectric sensor in a flight state of the aircraft, and the distance between a detected area right below the aircraft and the aircraft can be acquired. The invention also discloses an aircraft height control method. A flight device acquires the vertical height A between a detected area right below the aircraft and the aircraft through the aircraft detection method, the vertical height H1, H2, H3...Hn between the below detected area in front of the aircraft and the aircraft is acquired, and according to the vertical height A and the verticalheight H1, H2, H3...Hn, the flight control system in the aircraft controls the flight height of the aircraft.

According to a simulation method for infrared characteristics of an actual aircraft, a designed infrared source can adjust the luminous intensity and the radiation intensity according to the infraredcharacteristics of the actual aircraft so as to be closer to the actual aircraft, and it can be guaranteed that the striking effect is real and effective. The infrared source is applied to the targetdrone, and the target drone simulating the infrared characteristics is designed and comprises a drone body unit, a navigation control unit, a power unit and an infrared source unit. The infrared source unit is provided with a device capable of releasing an infrared source, so that the infrared source is combusted and hit outside a cabin of the drone aircraft, and the drone aircraft can be repeatedly used. The target drone is further provided with a recycling device, the combustion condition of the infrared source combustion agent can be detected in real time, and therefore the infrared sourceobtained after combustion and the infrared source with abnormal combustion are recycled, pollution is reduced, waste is avoided, and cost is saved.

The invention provides a BRDF data acquisition system and method based on unmanned aerial vehicle-mounted hyperspectral imaging, and relates to a data acquisition method which comprises an auxiliary positioning device, a data acquisition unit and a measurement and control unit. The auxiliary positioning device comprises a disc, a measuring rope and ground identification cloth, the data acquisitionunit comprises an unmanned aerial vehicle, a holder and a hyperspectral imager, and the measurement and control unit comprises a graph judgment module, an angle control module, an observation position control module and a data processing module. The collection method comprises the following steps: selecting an observed surface feature/scene, and arranging ground identification cloth; determininga coordinate position W of an observed surface feature/scene center point; calculating an observation angle; determining the hovering position of the unmanned aerial vehicle and collecting data; and forming a BRDF data set based on unmanned aerial vehicle hyperspectral imaging. According to the system, accurate control over the placing position of the ground identification cloth is achieved through the ground angle measuring device, the measuring and calculating workload during each operation is reduced, and the flight control efficiency of the unmanned aerial vehicle is improved.

The invention relates to an unpowered manned craft, discloses a kite in which a kite pilot can ride, short for a controlled kite, and simultaneously discloses a flying method of the controlled kite. The controlled kite consists of an upper lifting surface and a lower lifting surface, wherein the lower lifting surface adopts a manner of an arc-shaped curved surface with a depressed middle part and two upwarping ends, and is distributed bisymmetrically, the wingtip parts of two ends of the upper lifting surface and the lower lifting surface are closely overlapped or connected with each other, a lifeboat, an inflatable seat, a gravity center regulating device, an inflation protection column and a driven beam driving device are arranged below the middle part of the lower lifting surface, the lower end of an upper hoisting line is connected with a traction line system through a lifting hook, the traction system has the following three modes: an iron anchor traction line device, an umbrella anchor traction line device, and an unmanned ship traction line device, and can be randomly switched to be in a traction state or a gliding state. The invention aims at creating a new sports item, and the manned kite can freely glide and distantly fly. The controlled kite has the advantages that the ground control on the kite is changed to air control, so that the ancient kite sports are more colorful.

The invention discloses a model rocket suite for spaceflight science popularization education, and belongs to the technical field of science popularization education of sounding rockets. The model rocket suite comprises a rocket shell, an empennage and a parachute bag, wherein the rocket shell is formed by coaxially connecting a rocket nose cone, a rocket parachute cabin section rocket body, a connecting piece and a rocket power section rocket body in sequence; a window is formed in the peripheral face of a rocket parachute cabin section rocket body, and a rocket parachute cabin section cover plate is installed at the window in a sealed mode through a shearing bolt, an aluminum alloy bolt and a parachute cabin section sealing piece; the parachute bag is arranged in a rocket body of a rocket cabin section; a flight control panel is installed in a rocket body of a rocket power section through a control panel fixing piece; and a rocket engine is installed in the tail end of the rocket power section rocket body through an engine force bearing piece and an engine positioning plate. The rocket is in modular design and is divided into the recovery section rocket body comprising the parachute cabin section and the rocket body comprising the engine power section, the two parts can be independently manufactured and used in cooperation, and the rocket is good in universality and high in repeated utilization rate.

The invention relates to two aerospace turbofan engines. The first one is to feed rich oxygen in an intake way. The second one is to feed rich oxygen singly or synchronously in the intake way and an afterburner. Aiming at limited working height of an aviation turbofan engine, an intake way rich oxygen injecting module is arranged, a main structure of a traditional aviation turbofan engine is continuously used, and two sound cavity and separation regenerative cooling afterburners are adopted, so that the aviation turbofan engine can be changed to two aerospace turbofan engines capable of working at any height. The aerospace turbofan engine is an aerospace integral engine mainly adopting the traditional aviation turbofan engine, is excellent in technical succession, and facilitates development and application. The aerospace turbofan engine can propel an aircraft to fly at a 30-50 km height and a 3-5 M speed, or even more highly and more quickly, and is suitable for multiple aerospace integral aircrafts repeatedly used by multiple times.

The invention discloses an unmanned-aerial-vehicle-mounted laser dazzling device. The device comprises a dazzling device shell, a heat transfer plate, a signal receiver, a light-emitting assembly, a laser control assembly, a divergent lens, a convergence lens and an electric zoom set; when the signal receiver receives a no-target object, the laser dazzling device is used for lighting, 532nmn continuous light spots are generated, according to the received light spot size signal, the electric zoom set is controlled to adjust the distance between the divergent lens and the convergence lens, and the light spots irradiated to the target are magnified; when the signal receiver receives the target object, the laser dazzling device is used for warning and repelling illegal workers, and 532 nm stroboscopic light spots are generated; according to the received light spot size signal, the electric zoom assembly is controlled to adjust the distance between the divergent lens and the convergence lens, and the light spots irradiated to the target shrink. The dazzling device is adopted, the effect of beam concentrating is improved, the weight and the power consumption of a mounting device are reduced, the flying time of a small unmanned aerial vehicle is prolonged, and the flying height of the small unmanned aerial vehicle is increased.

The invention discloses a modularized vertical take-off and landing fixed-wing unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage, two wings and an empennage, wherein a first propeller for providing horizontal traction force is arranged at a front end of the fuselage, a power supply cabin is arranged at the position, close to the first propeller, of the top of the fuselage, and a control cabin is arranged at the position, close to a rear end, of the top of the fuselage; the bottom of the fuselage is detachably connected with a task hanging bin used for carrying different task modules, and the top of the fuselage is in threaded connection with two antenna rods; the two wings are symmetrically arranged and detachably connected to the two sides of the fuselage, and each wing is provided with a second propeller for providing vertical traction force; and the empennage is detachably connected with a rear end of the fuselage. The unmanned aerial vehicle has advantages of a fixed wing unmanned aerial vehicle and a rotor wing unmanned aerial vehicle, the fuselage, the wings and the empennage can be quickly disassembled and assembled and are easy to store and transport, a task pod can be matched with various task loads, the unmanned aerial vehicle can be used for multiple purposes, and in addition, the empennage can be replaced according to task requirements to adapt to different complex geographical environments.

The invention discloses a wingless aircraft. The wing-free aircraft comprises a shell and a driving unit, the shell comprises a shell, an air inlet is formed in the middle of the top surface of the shell, an exhaust port is formed in the periphery, an energy conversion cabin is arranged in the shell, the input end of the energy conversion cabin communicates with the air inlet, the output end communicates with the exhaust port, and an adjusting assembly is arranged in the exhaust port to adjust and control the displacement and exhaust direction; the driving unit is arranged in the energy conversion cabin, air enters from the air inlet and then is accelerated and heated by the driving unit to be output from the exhaust port to generate propulsive force, heat dissipation circulating air is formed with the aircraft as the center, and an air curtain vortex ring is formed by decreasing and diffusing from the center of the top of the aircraft to the periphery below the outer side; meanwhile,a low-pressure area is formed above the aircraft to generate attraction to enable the aircraft to get close to the low-pressure area; when the propelling force and attraction are balanced with the gravity of the aircraft, the aircraft suspends in the air, and the output power of the driving unit is increased to increase the flight height; the flight speed is increased by adjusting the air displacement, and the flight direction is changed by switching air exhaust direction channels.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a propeller driving mechanism for an unmanned aerial vehicle toy. The propeller driving mechanism comprises amain shaft, a driving assembly, a first propeller assembly and a second propeller assembly; the main shaft is connected with an inner shaft in a sleeving manner through a lower propeller; the inner shaft penetrates through the middle of the main shaft; the inner shaft is connected with a reversing rod in a sleeving manner through an upper propeller; the reversing rod penetrates through the middlepart of the inner shaft; the driving assembly is arranged in the middle of the main shaft in a sleeving manner; the first propeller assembly is positioned in the middle of the inner shaft and is positioned above a driving inclined plate; the first propeller assembly is driven by the driving assembly to rotate; the second propeller assembly sleeves the upper part of the inner shaft; and the secondpropeller assembly is driven to rotate reversely through the rotation of the first propeller assembly. The propeller driving mechanism has the advantages that the time of stay in air is long, so thatthe control convenience is brought for a user; the influence of external force is avoided, so that the flight is stable; and an unmanned aerial vehicle is accurate in flight remote control, high in flying height and relatively long in travel distance.