CN203612212U - Safe landing device during helicopter land-air and sea-air fault shutdown - Google Patents

Abstract

The invention discloses a safe landing device during helicopter land-air and sea-air fault shutdown. The safe landing device consists of a top wing (1) mounted above a rotor wing of a helicopter, a bottom wing (22) mounted in an undercarriage and the like; a parachute is mounted in the top wing, during normal flight, the top wing is rotated along with the rotor wing; during fault shutdown, the parachute is ejected out of the top wing and is opened within one second under the effect of a cold explosive bomb, and thus the helicopter can slowly land on the ground; a water surface float boat is mounted in the bottom wing, after the helicopter has fault shutdown above the sea surface, the cold explosive bomb is started, the water surface float boat is immediately ejected out of the bottom wing, an inflatable cushion is used for supporting the lower surface of the helicopter, and thus the helicopter can safely land in the sea.

Description

Safe falling device when helicopter land empty air-sea malfunction shutdown

Technical field

Safe falling device when helicopter land empty air-sea malfunction shutdown, belongs to air material class.

Background technology

The world today, numerous research institutions and aircraft manufacturing producer all rack one's brains, rack one's brains, move heaven and earth at the aircraft of safe falling when how producing in-flight failure always, and constantly dropping into huge manpower and financial resources is making great efforts, but, airplane crash is also also being showed at continuation, tragedy, each airplane crash, not only allow victim family members overwhelmed with sorrow, not only bring massive losses to country, and bring ill effect to the reputation of aircraft industry.Reason is because aircraft is in high airflight, inclement weather impact, lightning thunderbolt, flying bird collision, mechanical breakdown and oil circuit be overheated cause a variety of causes such as on fire cause aircraft stop can not normal flight factor be too complicated too much really, so aeroplane accident is still difficult to avoid

2004,670,000 dollars of American Space General Administration's appropriation and the cooperative study of trajectory system of defense company of the U.S., design a new generation can be used in the forced landing umbrella system of blimp, this parachute system device is after blimp back seat, by people's manual manipulation, utilize rocket projectile to penetrate, can within 1 second, open fast.In the time that aircraft is out of control, captain can release a parachute, and the powerful rope of parachute hitches wing, fuselage and tail, can make aircraft safety landing ground.But this parachute can only be used for, speed is low, the flivver of microlight-type, does not help for the jetliner of super ton of weight, 900 kilometers of speed per hours.

As for the flame-out in flight safe falling problem of autogyro, rarely has so far report.This is because have rotor on autogyro, after have empennage, both cannot be as fix parachute to blimp, also be difficult to as fighter plane ejection-seat by direct aviator bullet from aircraft ... so so far, the occupant of the helicopter problem of escaping, only have the former Soviet Union to develop armed helicopter parachute mode, escape similar with launching of fighter plane, when escape, explosive bolt on rotor can first be blown up rotor to come off, then aviator is ejected to passenger cabin, target is that people-oriented and saves aviator, as for aircraft value how much and whether also have other passengers just all no matter.At present, the autogyro of whole world active service only has Muscovite card 50 to have above-mentioned ejection-seat.As for civil helicopter, do not mention the escape problem of flame-out in flight back occupant, be exactly the mode that aviator's parachute-opening is landed, also do not appear in the newspapers.

Summary of the invention

Object of the present invention, be exactly for problem that can not safe falling after the empty air-sea malfunction shutdown in above-mentioned helicopter land, provide one to stop once in-flight failure, the even general all steerable safe falling devices of passenger of aviator, security officers, attendant, both save passenger, also saved aircraft.

The method one that the present invention takes is installed a dish shape box that is similar to flying saucer " UFO "---" the Top wing " above lifting airscrew, in box, equipping parachute, when aircraft normal flight, " flying saucer " is along with rotor rotates together, and in the time of helicopter malfunction shutdown, " flying saucer " inner parachute can, under the effect of cold quick-fried bullet, launch out " flying saucer " and open in the second, thereby makes aircraft slowly land ground; In order to prevent that rotor from revolving strand umbrella rope parachute was lost efficacy in the time that parachute is opened, " flying saucer " inner customized design a set of arrangement of clutch, this arrangement of clutch in the situation that of the normal rotation of rotor in leaving situation, parachute is kept with " flying saucer " synchronous rotary always, and launch out after " flying saucer " when parachute, under the drag force of parachute, this arrangement of clutch is at once in closure state, now, no matter whether rotor rotates, umbrella rope can not be subject to the impact of rotor and twist, thereby guarantees that parachute normally opens use.Because the lower surface of " flying saucer " is a plane or slightly upwards recessed, upper surface is a cambered surface raising up, so adding individual wing with regard to being equivalent on the top of helicopter---the title of " the Top wing " is come therefrom, as long as helicopter normal flight, according to Bernoulli Jacob's fluid mechanics principle, this Top wing will produce certain lift, just in time make up the little defect that even there is no multiple spot lift of lifting airscrew centre lift, therefore not only do not increase the weight of the burden of aircraft, also can increase on the contrary the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft, reduce the quantity discharged of carbon dioxide, clean air, implement environmental protection.

And when aircraft is across the sea when empty parking, no matter how good parachute first aid be also of no avail.Now, helicopter must can ensure safety by the another set of device of startup.This covering device is arranged among the alighting gear of aircraft below, owing to being in the bottom of fuselage, and is the sea lifesaving appliance with airfoil lift function, therefore be named as " end wing ".Groundwork, structure and the profile of this end wing is substantially identical with aforementioned " flying saucer " Top wing, difference is that what in this end wing, to fill is water surface floating ship rather than parachute, that its shape is also not necessarily justified, oval, but in the majority with oblong, its width is less than alighting gear, its length and fuselage are suitable, concave surface is downward, convex surface upwards, equaling so has again increased a wing to aircraft, can greatly increase the lift of aircraft, at least also can balance out the added burden that aircraft has increased to driving engine because having increased the devices such as the wing of a set of end; Be in again the bottom of fuselage due to this end wing, the loss of lift causing to aircraft so can effectively hide the pressure (be commonly called as down and wash wind-force) of the downward wind of aircraft rotary wing, than in addition installing two width additional to helicopter, to be exposed to the lift effect of the wing under rotor downwash wind pressure far better.When aircraft is across the sea after empty malfunction shutdown, start the cold quick-fried bullet in the end wing, water surface floating ship can eject at once the end wing and inflate pad below aircraft, simultaneously, the air accumulator that is arranged on fuselage below outside alighting gear can be in seconds to floating ship inflation, thereby lands a plane safely in the sea.Again because this water surface floating ship design is unique, function is equivalent to drag for the strainer of dumpling, even if thereby aircraft stops in the very low in-flight failure of plane off sea, as long as there is the time of launching floating ship in one or two second, even if aircraft is pricked in water inlet together with the first sample of floating ship image-stone afterwards, the floating ship of sufficient gas also can be held out the water surface by aircraft within ten seconds.

accompanying drawing explanation:fig. 1 is structural representation of the present invention, [1] for roof limb is " flying saucer ", [2] be at the bottom of the Top wing, at the bottom of being called for short the wing, [3] be Top wing lid, be called for short wing lid, [4] be parachute, [5] be umbrella rope, [6] be umbrella rope adapter plate, [7] be spring, [8] be cold quick-fried bullet, claim to launch again bullet, [9] for parachute launches telecontrol antenna, [10] be thrust baring, [11] be the powerful gusset of spider shape, [12] be powerful gusset bolt of rear end plate, [13] be Top wing pipe link, be called for short pipe link, [14] be rotor, [15] be slurry hub, [16] be rotor dynamical axis, [17] for parachute launches manual control line, be called for short umbrella control line, [18] be parachute ejection controller, be called for short controller, [19] be fuselage, [20] be air accumulator, [21] be alighting gear, [22] be the end wing, [23] be at the bottom of the end wing, [24] be end wing lid, [25] be water surface floating ship, be called for short floating ship, [26] for floating ship launches bullet, also claim the floating cold quick-fried bullet of ship, [27] for floating ship launches bullet wireless antenna, [28] be the powerful muscle of the end wing, [29] be end wing pitman, [30] be gas ducting, [31] for floating ship launches manual control line, [32] be floating ship ejection controller.

specific embodiments:specific embodiment of the invention scheme is divided into two steps, and the first step is, in the top of rotor [14], the Top wing [1] is installed; Second step is that the end wing [22] is installed in the middle of alighting gear [21]---is included between alighting gear [21] and fuselage [19] bottom air accumulator [20] is installed.

The Top wing [1] is to have the disk dish box-like body that is stamped the end, and the middle device of box parachute [4] etc., the space of box by the wing at the bottom of [2] link together and self-assembling formation from the different cambered surface of wing lid [3], the Top wing [1] is arranged on rotor [14] top center position by pipe link [13] and slurry hub [15], because the lower surface of the Top wing [1] is that [2] are there is no the plane of radian or slightly recessed cambered surface upwards at the bottom of the wing, upper surface is that wing lid [3] is the cambered surface radius that the cambered surface radius of [2] is greater than wing lid [3] at the bottom of the cambered surface and the wing raising up, that is to say little cancave cambered surface at lower large convex globoidal upper, therefore according in Bernoulli Jacob's fluid mechanics about " the large pressure of flow velocity is little, the little pressure of flow velocity is large " principle, in the time that air flows to the edge of another side from the edge on any one side of the Top wing [1], bottom cambered surface is little, flow velocity is slow, pressure is large, and cap cambered surface is large, flow velocity is fast, pressure is little, therefore air-flow can produce a lift upwards to [2] at the bottom of the wing and lift power, this power of lifting can by formula be lift=airfoil lift coefficient × 1/2 × density of air × speed square × wing area tries to achieve.

According to calculating, this Top wing [1] is under the state of aircraft normal flight, and the lift bringing to aircraft is much higher than the gravity of the Top wing [1] and inner matter thereof.In other words, add and load onto after this Top wing [1] to helicopter, not only can not increase the weight of the burden of aircraft, also can increase on the contrary the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft.A central part again because this Top wing [1] is to meet hydromechanical smooth dish fluid, and in rotor, therefore the resistance of the wind of the hand of rotation causing to rotor while following rotor wing rotation is very little, almost negligible.

At the bottom of the wing, [2] are the straight or recessed disk of thin wall acetabulum slightly upwards in lower surface, the centre at its top be cambered surface the downward punching press in the highest convex protrusion position diameter be not more than the hole nest of 200mm so that objects such as device bearing, spring and umbrella rope plate and play powerful effect.

Wing lid [3] is the disk of thin wall acetabulum that a upper surface raises up, and cambered surface direction when it connects with [2] at the bottom of the wing is identical, and its connection mode can be bonding, can be also flanging pressing, can also be that closing-up or bolts and nuts are fastening.

Powerful gusset [11] is a synthesis that is similar to spider shape, " belly " of " spider " is the hole nest that a diameter being stamped to form is not more than 200mm, " claw " is the powerful gusset that it outwards bends and stretches, its radian is identical with [2] at the bottom of the wing, to be connected with at the bottom of the wing, [2] are seamless, its quantity or be 3, 4, or be 5, 6, or it is 8, maximum 10, it connects except the fastening form of bolt and nut with [2] at the bottom of the wing, also can adopt bonding or riveting, the form of weldering and sticky, riveting, the form that bolt and nut uses simultaneously, in the nest chamber, hole that is connected formed with [2] at the bottom of the wing at it, spring [7] is housed successively, thrust baring [10] and umbrella rope adapter plate [6], the in the situation that of aircraft normal flight, thrust baring [10] and umbrella rope adapter plate [6] nest under the thrust of spring [7] is synchronized with the movement with the Top wing [1] the nest bottom, hole at [2] center at the bottom of the wing, once cold quick-fried bullet [8] plays and quick-friedly throws wing lid [3] and after making parachute [4] launch out the Top wing [1] and opening, umbrella rope adapter plate [6] can make on thrust baring [10] to move to and draw close and keep the attitude of relative rolling with the center bottom plane of the powerful gusset of spider shape [11] at the drag force lower compression spring [7] of umbrella rope [5], like this, no matter whether rotor [14] and the Top wing [1] rotate, can not apply to umbrella rope [5] power of rotation, thereby can not make parachute because revolving of umbrella rope twisted and closed inefficacy.

Installation and the inner structure of the Top wing [1] are: roof limb [1] is arranged on rotor [14] top center position by pitman [13] and slurry hub [15]; At the bottom of its wing, the top of [2] is installed with the powerful gusset of spider shape [11] by powerful gusset bolt of rear end plate [12]; In the hole nest combining at the powerful gusset of [2] at the bottom of the wing and spider shape [11], umbrella rope adapter plate [6], thrust baring [10] and spring [7] are installed successively; The top of the powerful gusset of spider shape [11] stacked parachute [4]; Inner the wrapping up in of parachute [4] put cold quick-fried bullet [8], one end of cold quick-fried bullet [8] is connected with the parachute ejection controller [18] in cabin by umbrella control line [17], the other end launches telecontrol antenna [9] with the parachute that stretches out the Top wing [1] or be arranged in cabin the inside and is connected---parachute be set launch the object of telecontrol antenna [9], once be the button inconvenience that crew's operation is fixed on the vicinal controller of cabin [18], also can use the remote controller cold quick-fried bullet of ignition [8] of carrying that parachute is launched and open; The top of parachute [4] is covered with wing lid [3], and at the bottom of the wing, [2] and wing lid [3] are by bonding or flanging pressing or closing-up or bolts and nuts are fastening etc. that mode is linked together.

When helicopter is across the sea when empty parking, being arranged on the inner floating ship of the end wing [22] among the alighting gear of helicopter below launches bullet [26] and can water surface floating ship [25] be launched out to the end wing within 1 second and open fast pad below aircraft, meanwhile, being arranged on the air accumulator [20] of fuselage below outside alighting gear can be by gas ducting [30]

In seconds give water surface floating ship [25] inflation, thereby land a plane safely in the sea.

The end wing [22] is arranged among the alighting gear of aircraft below, and its essential structure, shape and principle are identical with aforementioned " flying saucer " cardinal principle, and difference is that what in this end wing, to fill is water surface floating ship rather than parachute; The end wing [22] is also that a upper cambered surface is greater than the box-like body that lower camber side is the cambered surface of [23] at the bottom of the cambered surface of end wing lid [24] is greater than the end wing, its shape can be both circle can be also oval, both can be leg-of-mutton can be also square, rectangular, can also be trapezoidal or rhombus, generally in the majority with circle, ellipse and oblong; At the bottom of the end wing, the bottom surface of [23] can be a plane, also can be a upwards slightly recessed cambered surface, its width is less than alighting gear, its length and fuselage are suitable, cancave cambered surface is downward, and convex globoidal upwards, so equals and increased a no small wing to aircraft, can greatly increase the lift of aircraft, at least balance out the extra burden that aircraft has increased to driving engine because having increased the wing of a set of end and air accumulator; Be in again the bottom of fuselage due to this " end wing ", the loss of lift causing to aircraft so can effectively hide the pressure (be commonly called as down and wash wind-force) of the downward wind of aircraft rotary wing, installing two width additional than the fuselage both sides of giving in addition helicopter, to be exposed to the lift effect of the wing under rotor downwash wind pressure far better.

At the bottom of the end wing, the top of [23] is installed with the powerful muscle of the end wing [28], the top of the powerful muscle of the end wing [28] stacked water surface floating ship [25], water surface floating ship [25] is inner to be wrapped up in and is putting floating ship and launch bullet [26], one end that floating ship launches bullet [26] is launched manual control line [31] by floating ship and is connected with the floating ship ejection controller [32] in cabin, the other end launches wireless antenna [27] with floating ship and is connected, the top of water surface floating ship [25] is covered with Di Yigai [24], at the bottom of the end wing, [23] and end wing lid [24] are by bonding or flanging pressing or closing-up or bolts and nuts are fastening etc. that mode is linked together.

Air accumulator [20] be one made by corrosion-resistant steel or carbon fibre material be full of compressed-air actuated tank-like body, be arranged on the both sides of fuselage below outside alighting gear and be connected with water surface floating ship [25] by gas ducting [30]; In order to reduce as far as possible the weight of air accumulator [20], increase its safety, therefore the pressure of selecting can not be too large, the weight of the enough water surface floating ships of air [25] the picking-up aircraft that the inside fills is just.

Water surface floating ship [25] is one and can pierces in water together with the aircraft falling, the lifefloat that can from water, the aircraft falling be emerged again, and its function and shape are equivalent to strainer, are formed by connecting by numerous balloons that differ in size; Make all balloon gas leakage after gas because some balloons are damaged in order to prevent that balloon is full of, thus a tire tube valve that is similar to bicycle valve core function is set in each balloon, can only air inlet, can not give vent to anger; Huge kinetic energy is exactly that firm iron and steel life boat all may pierce, and is the aerated materials of rubber and so on still more in the time that aircraft falls in the air from height! So, best way, allow exactly the aircraft that falls together with inflatable open or not yet completely the floating ship of inflatable open as space recoverable module, first splash down in water, and then emerge and wait for rescue about 10 seconds.

In sum, after the safe falling device of helicopter in the time installing the empty air-sea malfunction shutdown in land of the present invention, safe falling not only can guarantee that airplane fault stops time, but also can increase the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft, reduce the quantity discharged of carbon dioxide, clean air, reduces environmental protection cost, the many birds of one stone are good job feelings of benefiting the nation and the people really.

Claims (4)

1. safe falling device when the empty air-sea malfunction shutdown in helicopter land, by roof limb [1], at the bottom of the Top wing [2], Top wing lid [3], parachute [4], umbrella rope [5], umbrella rope adapter plate [6], spring [7], cold quick-fried bullet [8], parachute launches remote control burst at the seams [9], thrust baring [10], the powerful gusset of spider shape [11], powerful gusset bolt of rear end plate [12], Top wing pipe link [13], rotor [14], slurry hub [15], rotor dynamical axis [16], parachute launches manual control line [17], parachute ejection controller [18], fuselage [19], air accumulator [20], alighting gear [21], the end wing [22], at the bottom of the end wing [23], end wing lid [24], water surface floating ship [25], floating ship launches bullet [26], floating ship launches antenna [27], the powerful muscle of the end wing [28], end wing pitman [29], gas ducting [30], floating ship launches manual control line [31], the compositions such as floating ship ejection controller [32], roof limb [1] is arranged on rotor [14] top center position by Top wing pipe link [13] and slurry hub [15], at the bottom of its wing, the top of [2] is installed with the powerful gusset of spider shape [11] by powerful gusset bolt of rear end plate [12], in the hole nest combining at the powerful gusset of [2] at the bottom of the wing and spider shape [11], umbrella rope adapter plate [6], thrust baring [10] and spring [7] are installed successively, the top of the powerful gusset of spider shape [11] stacked parachute [4], inner the wrapping up in of parachute [4] put cold quick-fried bullet [8], and one end of cold quick-fried bullet [8] is connected with the parachute ejection controller [18] in cabin by umbrella control line [17], and the other end launches telecontrol antenna [9] with the parachute that stretches out the Top wing [1] or be arranged in cabin the inside and is connected, the top of parachute [4] is covered with wing lid [3], and at the bottom of the wing, [2] and wing lid [3] are by bonding or flanging pressing or closing-up or bolts and nuts are fastening etc. that mode is linked together, the end wing [22] is arranged among the alighting gear of helicopter below, at the bottom of its end wing, the top of [23] is installed with the powerful muscle of the end wing [28], the top of the powerful muscle of the end wing [28] stacked water surface floating ship [25], water surface floating ship [25] is inner to be wrapped up in and is putting floating ship and launch bullet [26], one end that floating ship launches bullet [26] is launched manual control line [31] by floating ship and is connected with the floating ship ejection controller [32] in cabin, the other end launches antenna [27] with floating ship and is connected, the top of water surface floating ship [25] is covered with Di Yigai [24], at the bottom of the end wing, [23] and end wing lid [24] are by bonding or flanging pressing or closing-up or bolts and nuts are fastening etc. that mode is linked together, air accumulator [20] is arranged on outside alighting gear fuselage below and is connected with water surface floating ship [25] by gas ducting [30], it is characterized in that: roof limb [1] is arranged on rotor [14] top center position by Top wing pipe link [13], the end wing [22] is arranged among the alighting gear of helicopter below.

2. safe falling device when the empty air-sea malfunction shutdown in helicopter claimed in claim 1 land, it is characterized in that: described roof limb [1] is that a upper cambered surface is greater than the dish shape box that lower camber side is the cambered surface of [2] at the bottom of the cambered surface of wing lid [3] is greater than the wing, at the bottom of the wing, the bottom surface of [2] can be a plane, can be also a upwards recessed cambered surface.

3. safe falling device when the empty air-sea malfunction shutdown in helicopter claimed in claim 1 land, it is characterized in that: the described end wing [22] is that a upper cambered surface is greater than the box-like body that lower camber side is the cambered surface of [23] at the bottom of the cambered surface of end wing lid [24] is greater than the end wing, its shape can be both circle can be also oval, both can be leg-of-mutton can be also square, rectangular, it can also be trapezoidal or rhombus, at the bottom of its end wing, the bottom surface of [23] can be a plane, can be also a upwards recessed cambered surface.

4. safe falling device when the empty air-sea malfunction shutdown in helicopter claimed in claim 1 land, is characterized in that: described water surface floating ship [25] is strainer shape, is formed by connecting by the balloon differing in size.

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