53results about How to "Short landing distance" patented technology

The invention discloses a parachuting autogyro. The parachuting autogyro comprises a fuselage, a rotor wing device, a screw propeller device and a parachute device, wherein the fuselage comprises a cabin and a tail vane; a control system is arranged at the front end of the cabin; an engine is arranged at the rear end of the cabin; an undercarriage is further arranged under the fuselage; the rotor wing device is arranged at the top of the fuselage and comprises a rotor wing head and rotor wing sheets which are symmetrically arranged at the periphery of the rotor wing head; the rotor wing device is arranged at the tail part of the cabin and is connected with the engine through a gear box; and the parachute device is arranged above the rotor wing head and comprises a complete machine parachute, a storage cabin for storing the complete machine parachute and a catapult for opening the parachute. The parachuting autogyro has the following effects (1) the safety is high; (2) a taking-off and landing distance is short; (3) the stability is high and the wind resistance is strong; and (4) the cost performance is relatively high.

A modularized mobile airplane water taking-off and landing platform based on photovoltaic power station comprises multiple movable water modules which are end to end to be assembled to form an airplane taking-off and landing runway; the movable water modules comprise hulls, control units, module docking units, battery arrays, energy storage battery devices and propelling devices, wherein the control units, the module docking units, the battery arrays, the energy storage battery devices and the propelling devices are mounted on the hulls; decks of the hulls are of rectangular structures; the module docking units are positioned at the front and back ends of the hulls; the two adjacent hulls are assembled and connected through the module docking units; and the battery arrays are arranged on the decks. According to the modularized mobile airplane water taking-off and landing platform based on the photovoltaic power station, through adoption of a modularized combined mode, the length of thetaking-off and landing runway can be effectively increased, and the building period and difficulty of the platform are reduced; during the taking-off and landing of an airplane, the platform can be controlled to obtain a certain initial speed so that the taking-off and landing distance of the air[plane is reduced by means of relative motion; and by laying the solar battery array on each deck, electric energy is provided for the operation of the movable water modules so that the endurance of the platform is effectively enhanced.

The invention provides a zero backward thrust composite wing aircraft with ducted fan composite ailerons. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons comprises an aircraft body and composite lift wings which are fixedly mounted on the two sides of the aircraft body, wherein the aircraft body is arranged as a deck platform; self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; ducted fan propellers are arranged at the front ends of ducted fan thrust self-energizedcomposite ailerons; the self-sealing ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electricity, liquid and gas ports and the wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wings through thewing hinges. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons has the characteristics that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; and the ailerons adopt compositelift forces to guarantee appropriate power.

The invention provides a foldable composite wing aircraft with twin-propeller thrust composite ailerons. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons comprises an aircraft body and composite lift wings, wherein the composite lift wings are mounted on the two sides of the aircraft body in a foldable manner; the aircraft body is arranged as a deck platform;self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; propellers are arranged at the front ends of propeller thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arrangedon one side or two sides of the propeller thrust self-energized composite ailerons; and the propeller thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high,the structural intensity of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; the ailerons adopt composite lifts so that the adaption range of the power is guaranteed.

The invention discloses a rear single-paddle type compound wing airplane with twin-duct thrust compound auxiliary wings and additional wings. The rear single-paddle type compound wing airplane comprises an airplane body, compound lift force wings fixedly mounted on two sides of the airplane body and ducted fan propellers, wherein self-enclosed ducted fans are arranged in the compound lift force wings; wing hinges are designed on the outer sides of the compound lift force wings; the ducted fan propellers are arranged at the front ends of propeller thrust self-powered compound auxiliary wings; self-enclosed ducted fans are arranged in the propeller thrust self-powered compound auxiliary wings; electricity liquid gas connection ports and the wing hinges are arranged on both sides of the propeller thrust self-powered compound auxiliary wings which are movably connected with the compound lift force wings through the wing hinges on one sides. The rear single-paddle type compound wing airplane has the characteristics of short take-off and landing distance, high flying speed, high wing structure strength, capability of energy storage in the wings, low flying energy consumption, long hang time, high safety and the like; the auxiliary wings adopt compound lift force to guarantee an application range of power.

The invention provides a rear single-duct fan type combined wing manned aircraft which is composed of a rear single-duct fan type combined wing aircraft and a manned cabin. The rear single-duct fan type combined wing aircraft comprises an aircraft body, combined lift force wings fixedly installed on the two sides of the aircraft body and a ducted fan propeller. The aircraft body is arranged to bea deck platform. Self-closed ducted fans are arranged in the combined lift force wings, and wing hinges are designed on the outer sides of the combined lift force wings. The manned cabin is installedbelow the aircraft body. The rear single-duct fan type combined wing manned aircraft has the beneficial effects of being short in take-off and landing distance, high in flight speed, high in wing structural strength, capable of storing energy through the wings, low in flight energy consumption, long in hang time, high in safety and the like.

The invention relates to a rear single ducted fan type composite wing aircraft with double ducted fan composite ailerons. The rear single ducted fan type composite wing aircraft with the double ductedfan composite ailerons comprises a rear single ducted fan type composite wing aircraft and ducted fan thrust self-energized composite ailerons which are assembled on the two sides of the rear singleducted fan type composite wing aircraft, wherein the rear single ducted fan type composite wing aircraft comprises an aircraft body, composite lift wings and a propeller, wherein the composite lift wings are fixedly mounted on the two sides of the aircraft body; the aircraft body is a deck platform; self-sealed ducted fans are placed in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; self-sealed ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electric, liquid and gas interfaces and wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wingsthrough the wing hinges. The rear single ducted fan type composite wing aircraft with the double ducted fan composite ailerons has the advantages of short takeoff and landing distance, high flying speed, high wing structural strength, energy storage ability of the wing, low flying energy consumption, long hang time and so on; and the large-area composite lift wings can have effects of gliders inan emergency case, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are guaranteed.

The invention discloses a composite wing air freighter with twin-screw composite auxiliary wings with solar additional wings. Rear thrust force-free composite wing aircraft comprises an aircraft body,composite lifting wings which are fixedly arranged at the two sides of the machine body, and additional wings, wherein the machine body is a deck platform; self-sealing ducted fans are arranged in the composite lift force wings; wing hinges are designed at the outer sides of the composite lift force wings; batteries/fuels are arranged in the additional wings; solar cell panels are arranged on thesurfaces of the additional wings; and a freight bin is mounted below the aircraft body. The composite wing air freighter has the characteristics of being short in takeoff and landing distance, high in flying speed, high in wing structural strength, capable of storing energy by the wing, low in flying energy consumption, long in hang time, high in safety, and the like; and the auxiliary wings adopt composite lift force, so that the applicable range of the power is guaranteed.

The invention discloses a composite lift force aircraft with a development platform. The composite lift force aircraft consist of a rear single-propeller type composite wing aircraft, thrust-free self-powered composite auxiliary wings assembled at the two sides of the rear single-propeller type composite wing aircraft and an manned bin, wherein the rear single-propeller type composite wing aircraft comprises a machine body, composite lift force wings which are mounted at the two sides of the machine body in a foldable mode, and a propeller; the machine body is a deck platform; self-sealing ducted fans are arranged in the composite lift force wings; wing hinges are designed at the outer sides of the composite lift force wings; self-sealing ducted fans are arranged in the thrust-free self-powered composite auxiliary wings; an electric-liquid gas interface and a wing hinge are arranged at one side or the two sides of each propeller thrust self-powered composite auxiliary wing, and are movably connected with the composite lift force wings through the wing hinges; and the manned bin 112 is mounted below the machine body. The composite lift force aircraft has the characteristics of beingshort in takeoff and landing distance, high in flying speed, high in wing structural strength, capable of storing energy by wings, low in flying energy consumption, long in hang time, high in safetyand the like.

The invention relates to a rear single screw foldable composite wing manned craft with an additional wing. The rear single screw foldable composite wing manned craft comprises a craft body, the composite lift force wings mounted at the two sides of the craft body in a foldable manner and a propeller, wherein the craft body is arranged as a deck platform, the self-sealing ducted fans are arranged in the composite lift force wings, and the wing hinges are designed at the outer sides of the composite lift force wings; a manned cabin is arranged below the craft body, a magnetic type automatic interlocking interface male connector and a magnetic type automatic interlocking interface female connector are respectively arranged in front of and behind the composite lift force wings, and the magnetic type automatic interlocking interface male connector and the magnetic type automatic interlocking interface female connector have the same size. A wing hinge and an electric-hydraulic-gas interfaceare arranged on one side, facing the craft body, of the additional wing, and the additional wings are installed at the outer sides of the composite lift force wings in a foldable manner through the wing hinges. The craft has the characteristics of short take-off and landing distances, high flight speed, high structural strength of the wings, energy storage wings, low flight energy consumption, long hang time, high safety and the like.

A foldable composite-wing manned aircraft with double-propeller-thrust composite auxiliary wings is provided. A rear-thrust-free type composite-wing aircraft includes a fuselage and composite liftingwings mounted, in a foldable manner, at two sides of the fuselage. The fuselage is a deck platform. Self-sealing ducted fans are disposed in the composite lifting wings. Hinges are arranged at outer sides of the composite lifting wings. Front ends of propeller-thrust self-powered composite auxiliary wings are provided with propellers. Self-sealing ducted fans are disposed in the propeller-thrust self-powered composite auxiliary wings. Electro-hydraulic gas connectors and wing hinges are disposed on one or two sides of the propeller-thrust self-powered composite auxiliary wings. The composite auxiliary wings are movably connected to the composite lifting wings through the wing hinges. A manned bin is mounted at the lower part of the fuselage. The aircraft has characteristics of short take-off and landing distances, a high flight speed, high wing structural strength, a characteristic that the wings can store energy, low flight energy consumption, long flying time, high safety, and the like. Composite lifting force is adopted by the auxiliary wings, thus ensuring the adaptive range of power.

The invention relates to a combined-wing cargo aircraft with double propeller thrust combined ailerons. A rear thrust-free combined-wing aircraft comprises a body, combined lift wings fixedly mountedon two sides of the body, and a freight cabin, wherein the body is a deck platform; self-sealing ducted fans are arranged in the combined lift wings; wing hinges are designed outside the combined liftwings; propellers are arranged at the front ends of propeller thrust self-energizing combined ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energizing combined ailerons; an electro-hydraulic gas interface and a wing hinge are arranged on one side or both sides of each propeller thrust self-energizing combined aileron; the propeller thrust self-energizing combined ailerons are movably connected to the combined lift wings through the wing hinges; the freight cabin is mounted below the body. The invention has the characteristics of being short in take-off and landing distances, fast in flying speed, high in wing structural strength, capable of storing energy in the wings, low in flight energy consumption, long in hang time, and high in safety; the ailerons adopt combined lift, to ensure power adaptability.

The invention provides a zero rear thrust composite-wing cargo aircraft with turbofan composite ailerons and additional wings. An aircraft body is arranged as a deck platform; a self-sealing ducted fans are embedded in composite lift wings; wing hinges are designed on the external sides of the composite lift wings; turbofan propellers are arranged under turbofan thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the turbofan thrust self-energized composite ailerons; electricity, liquid and gas interfaces and wing hinges are arranged on one sides or two sides ofthe turbofan thrust self-energized composite ailerons; the turbofan thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges; wing hinges are arranged on one sides, facing towards the aircraft body, of the additional wings; the additional wings are mounted on the external sides of the composie lift wings through the wing hinges in a foldable manner; and a cargo compartment is mounted at the bottom of the aircraft body. The zero rear thrust composite-wing cargo aircraft with the turbofan composite ailerons and the additional wings hasthe advantages that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high, the ailerons adopt composite lift forces to guarantee the power application range and so on.

The invention relates to a rear single-channel fan composite wing aircraft with double-channel fan composite auxiliary wings, which is composed of a rear single-channel fan composite wing aircraft, achannel fan thrust self-powering composite auxiliary wing and a manned cabin installed on both sides of the rear single-channel fan composite wing aircraft. A aft-single-channel fan-type composite-wing aircraft comprise a body, a composite lift wing fixedly arrange on both sides of that body, and a propeller; Wherein, the airframe is arranged as a deck platform; The compound lift wing has built-inself-enclosed duct fan and wing hinge on the outside of the compound lift wing. A self-enclosed ducted fan is arranged in the ducted fan thrust self-powered composite auxiliary wing, and one or bothsides of the ducted fan thrust self-powered composite auxiliary wing are provided with an electro-hydraulic air interface and a wing hinge, which are movably connected with the composite lifting wingthrough the wing hinge, and the manned cabin is installed below the body. The invention not only has the characteristics of short take-off and landing distance, high flying speed, high wing structuralstrength, energy storage capability of the wing, low flying energy consumption, long air stagnation time and the like, but also has the functions of a large-area composite lifting wing, which can play the role of a glider in an emergency situation, greatly improves the safety of an aircraft, and guarantees the safety of personnel and materials.