39results about How to "Reduce the acceleration of gravity" patented technology

The invention discloses a movable supporting framework plate supporting structure for a roadway. According to the movable supporting framework plate supporting structure, one ends of upper baffles arehinged to top rotating shafts, the other ends of the upper baffles are fixedly connected to or hinged to side rotating shafts, the upper ends of side baffles are fixedly connected to or hinged to theside rotating shafts, the top rotating shafts are arranged in the extending direction of the roadway, the upper baffles hinged to the two sides of the top rotating shafts are inverted-U-shaped or inverted-V-shaped, the two sides of an elastic sheet are fixedly connected to the lower surfaces of the upper baffles on the two sides separately, limiting elastic sheets are C-shaped and are arranged onthe lower surfaces of the upper baffles and the inner side surfaces of the side baffles, one sides of the limiting elastic sheets are fixedly connected to the upper baffles or the side baffles, the two ends of the side rotating shafts are hinged to the compression ends of elastic compression rods on the two sides separately, the fixed ends of the elastic compression rods are hinged to supportingcolumns, the two ends of torsion supporting mechanisms are connected to the fixed ends of the elastic compression rods and the supporting columns, the other ends of the supporting columns are arrangedon a roadway base plate, and one ends of supporting column supporting mechanisms are fixedly connected to or hinged to the supporting columns and enable the supporting columns to be supported on theroadway base plate or to be fixedly connected to the roadway walls. According to the movable supporting framework plate supporting structure, roof fall and rib spalling of the mine roadway or a temporary traffic tunnel can be effectively protected.

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 discloses a construction method for vertically laying super-high-rise building cable. The construction method includes the steps: (1) mounting a cable reducer on a building structure close to a cable bridge every preset distance along the lowering direction of the cable; (2) conveying the coiled cable to the highest layer of a building by equipment and mounting the coiled cable on acable pay-off rack with an emergency brake; (3) lowering a cable head in a pulling manner, and laying the cable sequentially bypassing all the cable reducers from top to bottom; (4) detaching the cable reducers from the building structure from top to bottom, moving the cable reducers into the cable bridge and temporarily fixing the cable reducers; (5) detaching two fixed pulleys of each cable reducer, moving the cable into the cable bridge, fixing the cable and finishing laying the cable. By the method, the super-high-rise building cable can be safely and rapidly vertically laid and constructed in a quality and quantity guaranteed manner.

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 movable suspended protection rib plate supporting structure for a roadway. The movable suspended protection rib plate supporting structure comprises upper baffles, side baffles, an anchor rod, a top rotating shaft, side rotating shafts, an elastic slice and limiting elastic slices. One ends of the upper baffles are hinged to the top rotating shaft and the other ends of the upper baffles are hinged to the side rotating shafts, and the upper ends of the side baffles are hinged to the side rotating shafts. The upper end of the anchor rod is anchored at the top of the roadway, and the lower end of the anchor rod is hinged to or fixedly connected with the top rotating shaft, the top rotating shaft is arranged along extending direction of the roadway, and the upper baffles hinged to the two sides of the top rotating shaft form a reversed-U shape or a reversed-V shape. The two sides of the elastic slice are separately and fixedly connected with the lower surfaces ofthe upper baffles hinged to the two sides of the top rotating shaft, the limiting elastic slices are of C-shaped structures and are arranged on the lower surfaces of the upper baffles connected with the side rotating shafts and the inner side faces of the side baffles, and one sides of the limiting elastic slices are fixedly connected with the lower surfaces of the upper baffles or the inner surfaces of the side baffles. The movable suspended protection rib plate supporting structure can effectively overcome the defects of a traditional roadway supporting structure, and can effectively protectroof falling and rib spalling of a mine roadway and a temporary traffic tunnel.

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 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.

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.

The invention relates to a rear single-propeller type composite wing manned craft which comprises a rear single-propeller type composite wing craft and a manned bin, wherein the rear single-propellertype composite wing craft comprises a craft body, the composite lift force wings fixedly installed at the two sides of the craft body 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; the wing tails are further arranged at the tail ends of the composite lift force wings, the propeller is a screw propeller, and the manned bin is arranged below the craft body. 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.