CN203612213U - Safe landing device for high-altitude helicopter fault shutdown - Google Patents

Abstract

The invention discloses a safe landing device for high-altitude helicopter fault shutdown. The safe landing device consists of a top wing (1) mounted on a rotor wing and the like, wherein a parachute is arranged 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 a helicopter can slowly land on the ground; in addition, after the safe landing device for high-altitude helicopter fault shutdown is mounted on the helicopter, the safe landing is ensured during the high-altitude helicopter fault shutdown, the lift force of the helicopter is increased, the burden of the rotor wing is reduced, the energy consumption of the helicopter is reduced, the emission load of carbon dioxide is reduced, and the safe landing device for high-altitude helicopter fault shutdown is really an excellent object beneficial to the nation and the people.

Description

Safe falling device when helicopter high-altitude malfunction shutdown

Technical field

Safe falling device when helicopter high-altitude 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 safe falling problem of the flame-out in flight 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.

accompanying drawing:accompanying drawing is structural representation of the present invention, [1] for roof limb be " flying saucer ", at the bottom of [2] are the wing, [3] be wing lid, [4] are parachute, and [5] are umbrella rope, [6] be umbrella rope adapter plate, [7] are spring, and [8] are cold quick-fried bullet, claim again to launch bullet, [9], for parachute launches telecontrol antenna, [10] are thrust baring, [11] be the powerful gusset of spider shape, [12] are powerful gusset bolt of rear end plate, and [13] are pipe link, [14] be rotor

[15] be slurry hub, [16] are rotor dynamical axis, and [17] are manual control line for parachute launches, and is called for short umbrella control

Line, [18] are parachute ejection controller, are called for short controller, [19] are fuselage.

specific embodiments:specific embodiment of the invention scheme is that the device of a set of Top wing by name [1] is installed in the top center position of rotor [14].

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 connecting screw rod [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: the cambered surface of [2] at the bottom of the cambered surface of wing lid [3] is greater than the wing, little cancave cambered surface under, large convex globoidal is 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 be passed through 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 that lower surface is plane or recessed disk of thin wall acetabulum slightly upwards, 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 riveting

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 centre, rotor [14] top 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.

In sum, after the safe falling device of helicopter in the time installing high-altitude of the present invention malfunction shutdown, once high-altitude malfunction shutdown, the even general passenger of crew can quick-friedly turn over wing lid ejaculation parachute and moment opens by making to launch by the button on movement controller [18], makes aircraft slowly land ground.In addition, helicopter is installed after safe falling device of the present invention, safe falling not only can guarantee aircraft high-altitude malfunction shutdown time, but also can increase the lift of aircraft, and reduce the burden of rotor, reduce the energy consumption of aircraft, reduce the quantity discharged of carbon dioxide, clean air, reduces environmental protection cost, is good job feelings of benefiting the nation and the people really.

Claims (2)

1. helicopter high-altitude fault stoptime safe falling device, by roof limb [1], at the bottom of the wing [2], wing lid [3], parachute [4], umbrella rope [5], umbrella rope adapter plate [6], spring [7], cold quick-fried bullet [8], parachute launches telecontrol antenna [9], thrust baring [10], the powerful gusset of spider shape [11], powerful gusset bolt of rear end plate [12], pitman [13], rotor [14], slurry hub [15], rotor dynamical axis [16], parachute launches manual control line [17], parachute ejection controller [18], the compositions such as fuselage [19], 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, umbrella rope adapter plate [6] is installed successively at [2] at the bottom of the wing and spider shape brute force gusset [11], thrust baring [10] and spring [7], 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, the top of parachute [4] is covered with wing lid [3], at the bottom of the wing, [2] and wing lid [3] by bonding or flanging pressing or closing-up or bolts and nuts are fastening etc. that mode is linked together, is characterized in that: roof limb [1] is arranged on rotor [14] top center position by pitman [13].

2. the safe falling device when malfunction shutdown of helicopter claimed in claim 1 high-altitude, it is characterized in that: described roof limb [1] be a large cambered surface upper little cambered surface lower be the dish shape box of 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.

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