CN1027531C - Structural airfoil having integral expulsive system - Google Patents
Structural airfoil having integral expulsive system Download PDFInfo
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- CN1027531C CN1027531C CN 90108905 CN90108905A CN1027531C CN 1027531 C CN1027531 C CN 1027531C CN 90108905 CN90108905 CN 90108905 CN 90108905 A CN90108905 A CN 90108905A CN 1027531 C CN1027531 C CN 1027531C
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Abstract
A structural member having integral surface de-icing capability and method of manufacture are described. The structural member includes a non-metallic high tensile modulus fiber-reinforced matrix structural backing, thin force and displacement generation means, and a thin high tensile modulus outer skin bonded to said backing and said force and displacement generation means which is postioned between the backing and the skin. The force and displacement generation means may include one or more inflatable tubular members and/or electromagnetic apparatus. The structural member may be substituted for the aluminum alloy leading edge structural skin typically employed on modern aircraft.
Description
The present invention relates to a kind of composite material structural member, it comprise as a global facility from external surface of structural member (for example: the device of ice sheet) separating with a kind of solid, more particularly, the present invention relates to a kind of framing member that is particularly suitable for as wing aerofoil or leading edge, this member is used for aircraft leading edge when surface, it comprise one as a whole parts be applicable to afterburning displacement mechanism for the high-modulus uppermost layer deicing of composite element.
From having the air age beginning of engine installation, aircraft just flies under the state of flight of the surperficial accumulated ice of its part (for example wing and strut) tedious.If unconstrained, this accumulated ice just to the profile of aircraft weightening finish and change aircraft wing and control surface, consequently causes the state that can not fly.People are by effort, have proposed three kinds of universal methods (being commonly referred to deicing technology) of removing accumulated ice and have been used for preventing and/or remove accumulated ice under the state of flight.
First kind of deicing method is called hot deicing method, is exactly to the leading edge heating, thereby makes the adhesive ability between accumulated ice and airplane parts loose.Here " leading edge " said means those edges that easily freeze on the flight part and flow through the gas shock of aircraft, and this this edge also has the point or the line of diffusion.By heating, in case adhesive ability is lax, the air-flow that accumulated ice will be flow through aircraft usually blows away from airplane parts.The method that adds heat front has two kinds usually.A kind of is so-called electro-thermal deicing method, places an electric heating element at the frontal region of airplane parts, and laying method or be placed in the high resiliency cover that encases leading edge is perhaps put into the covering of airplane parts.These heater elements generally provide electric energy by one or more electrical generators that driven by aero-engine, and opening or closing of it will guarantee that enough heats come loose accumulated ice.Flivver can not provide the electric energy of q.s to adopt the electro-thermal deicing method.
Another kind of method of heating are to make the high-temperature gas from one or more levels compressor of turbine engine flow through the leading edge of airplane parts (as: wing and strut), so that the effect that forms a kind of deicing or prevent to freeze.This method only is used to the aircraft with turbine engine, can supply usefulness because one or more levels air compressor of this turbine engine can be discharged high temperature compressed air.This method of heating can reduce fuel oil consumption and turbine output rate.
Second kind of general-duty deicing method is chemical method.Under condition of limited, a kind of pharmaceutical chemicals is applied on all or part of part of aircraft, with the adhesive ability between reduction and aircraft and accumulated ice, or the solidfying point of the water of reduction productive set on aircraft surfaces.
The third general-duty deicing method is mechanical deicing's method.In main Business Machine deicer, pneumatic deicer assembly is arranged, the tubular member that a plurality of expandable available compressed fluids (being generally pressurized air) are full of covers on the frontal region or wing or strut part of aircraft.During inflation, tubular member tends to make the leading edge shape of wing or strut to expand, and makes long-pending ice in the above cracked, spills in the air-flow by airplane parts.In general, the shape of these tubular members is roughly parallel to the leading edge of aircraft.These common low-pressure pneumatic ice removals by have like rubber or be roughly elastomeric cmpd and constitute.The material that constitutes inflatable tube in this ice removal member is general inflatable or enlarge 40% or more in an inflation cycle, thereby causes the bigger variation of ice removal and leading edge shape, and makes the ice that amasss on leading edge cracked.A large amount of air of these common pneumatic de-icing devices needs charges into it is expanded, and the inflationtime of pipe, and average out to is about 2～6 seconds on the general custom.Because the distortion meeting of the Airfoil shape that the pipe inflation causes significantly changes the airflow model by wing, therefore the lifting characteristic to wing has adverse effect.The rubber or the general Young's modulus (modulus of elasticity) of rubber like material that constitute these common pneumatic de-icing devices are about 690KPa.The modulus of elasticity of ice has multiple report, and for about 275,000KPa is to about 3,450, between the 000KPa.It has been generally acknowledged that the modulus of elasticity that has of ice can make accumulated ice control to and make the surface profile variations minimum of supporting this accumulated ice.The modular ratio of the rubber compound that common ice removal the is used modulus of elasticity relevant with accumulated ice is much lower.Common pneumatic de-icing utensil has big swell increment, has the effect that accumulated ice is cracked or rupture that makes, and therefore the air-flow that accumulated ice is impacted is cleared away.
Another kind of mechanical deicing device comprises the electromechanical hammering device, as US Patent № .3,549, people such as 964(Levin) described the sort of.Because wing cover has sensivity for stress fatigue taking place when the whole long-time hammering, so unlikely from commercial big great development or use this technology.
US Patent № .4,690, people such as 353(Haslim) another kind of electromechanical deicer is disclosed.The flexible tape conductor (each is all folded up) of one or more stacks itself is embedded in a kind of elastomeric material.If this conductor is supplied with big pulse current, the adverse current electric current in relative section of the adjacent two layers of conductor just causes interactional magnetic field so, thereby produces a kind of electric pulse power between the stack conductor segment, make their almost moment ground separate.This dilating effect can be removed the lip-deep any solid of elastomeric material.
US Patent № .4,875, people such as 644(Adam) described another kind of electromechanical deicer, this specification sheets is in conjunction with reference to its content.When feeding big magnetic current pulse in the conductor, two or more board-like arrays (each all contains one group of arrange at regular intervals, parallel ribbon conductance element) are just by excitation respectively fast and effectively.
US Patent № .4,706, people such as 911(Briscoe) and US Patent № .4,747, people such as 575(Putt) disclose a kind of device of leading edge deicing that is, in this device, fed the high-pressure pulsating fluid and make at area supported and have appendix rapid expanding between the tabular covering of suitable high-modulus.Pulsating fluid is admitted to appendix and makes the high-modulus skin morph, stops suddenly then.Therefore, the momentum that gives accumulated ice causes moving of ice, and this helps the separation of icing and removes.In some most preferred embodiment, inflatable tubular members is preferably in less than 0.1 second in 0.5 millisecond and just finishes inflation.US Patent № .4,706,911 Fig. 4 and supplemental instruction have described a kind of aie escape valve that is applicable to eductor/guide rod manipulation of this pneumatic pulsation ice removal.US Patent № .4,747,575 Fig. 7 and supplemental instruction have described a kind of electric shock valve that is used for pneumatic pulsation ice removal, and it is delivered to a series of rapid fluid pressure pulsations in the expandable tubular of the deicer that is contained in leading edge.Be devoted to improve this air pulsing ice removal system and cause constantly making great efforts to improve the valve of carrying desirable fluid pulse.
Though disclosed apparatus and method have all been confirmed as the deicing that is applicable to aircraft in the above-mentioned patent, but still exist the target of an industrial effort, promptly reduce weight as far as possible and increase service life and reliability.In order to reach this target, the designer of present generation aircraft and originating firm adopt more and more by high modulus fibre and include, but is not limited to the light weight composite material that carbon, graphite, aromatic poly amide and glass fibre strengthen organic resin or carbon back.The leading edge surface for example leading edge surface and the empennage part of aircraft wing and strut all is equipped with picture US Patent № .4, and 706,911 and № .4, the device of the independent manufacturing that 747,575 disclosed devices are such.This device with the adhesive securement of bonding this auxiliary deicer on existing wing structure.Owing to there is this auxiliary device, changed the shape of leading edge, this is a kind of undesired consequences.In other words, in when design or before this device had been installed, the leading edge of a wing of some prior art embodiment must be made amendment, and assigns to install deicer so that suitable recess to be provided.Owing to have recess, so the method for this installation deicer just can guarantee that the finished product assembly has smooth stream condition.But, in the present invention, be complete and do not add deicer in addition on lower floor's area supported and the wing structure.Its deicer does not increase or has increased on a small quantity the structural strength of lower floor's area supported of fixing it.Previously known many auxiliary deicers all have one deck by the elastomeric material accumulated ice uppermost layer made of rubber (poly-chloroprene rubber) or urethanes for example.These materials awing to from the corrosion susceptibility of rainwater, rain and snow, hail and snow more than the common aluminum alloy leading edge surface height that adopts in modern large aircraft and some the general flight.This aircraft comprises that the expectation of service life that is generally about 0.025～about 0.190 inch thick aluminum alloy outer cover is 20 years or higher.The number of times of repairing or change this deicer is reduced to the target that Min. is airplane industry.The anti-weathering ability of always wishing this deicer ideally equals to adopt the resistance to corrosion of the used aluminum alloy outer cover of large-scale turbine commercial aircraft of bleeding device deicing at least.
Rain is not unique alluvium that leading edge ran into.In the service life of aircraft, the impact of thing of also may run into for example bird, hail, the chance when staggering the fragment that flies up and aircraft routine maintenance being run into etc.
An aspect of of the present present invention provides a kind of framing member with integral surface de-icing capability, and this framing member comprises:
(a) composite material substrate that strengthens basal body structure by high tensile modulus non-metallic fibers;
(b) Bao afterburning displacement mechanism;
(c) one deck bonds to the thin uppermost layer of high tensile modulus on above-mentioned substrate and the above-mentioned afterburning displacement mechanism,
Above-mentioned afterburning displacement mechanism is between above-mentioned substrate and above-mentioned uppermost layer.
Another aspect of the present invention provides a kind of a kind of method with framing member of integral surface de-icing capability of making, and this method comprises:
(a) provide a former;
(b) outer metallic surface and an outer adhesive linkage are put into mould;
(c) the thin afterburning displacement mechanism of moulding and it is adhered on the above-mentioned outer adhesive linkage;
(d) an interior adhesive linkage is adhered on the afterburning displacement mechanism;
(e) strengthen the polymer matrix composite layer with multi-layer fiber and constitute a composite material substrate, and this substrate is adhered on the above-mentioned interior adhesive linkage;
(f) assembly set of above-mentioned uppermost layer, afterburning displacement mechanism and substrate is solidified and bond together, form above-mentioned single-piece framing member.
By most preferred embodiment of the present invention and description taken in conjunction with the accompanying drawings, will be clearer to the features and advantages of the present invention.
Fig. 1 is for constituting its leading edge portion with device of the present invention and being in the part sectional view of the wing of strained condition;
Fig. 2 is similar to the local amplification profile that device shown in Figure 1 is in the non-stress state and has one deck ice;
Partial enlarged drawing when Fig. 3 is in its strained condition for the device of Fig. 2;
Fig. 4,5 and 6 is respectively a kind of lateral plan, biopsy cavity marker devices front elevation and backplan of rainwater etch specimen holder;
Fig. 7 is the block diagram that is used to test the another kind of sample of anti-rainwater erosion.
The invention provides a kind of have can be the device of the framing member formula with integral surface separating capacity of leading edge of a wing deicing.The present invention also provides the method for making this device and the method that adopts this device deicing.Deicing is exactly after leading edge forms ice it to be removed." leading edge " is meant that component surface meets and wash open the position of the air-flow of collision on component surface, and for example wing, stabiliser, strut, gondola and other shells front portion and aircraft separately at first is subjected to bossing by the gas shock of aircraft when flight.Referring to accompanying drawing, Fig. 1 illustrates a kind of according to the leading edge structure 10 with integral de-icer ability of the present invention, and the device 10 shown in the figure is in the strained condition of (in order the to say something) distortion that has exaggeration.In fact, the deflection of the aerofoil profile of smooth and continuous is much smaller.Device 10 is used for replacing being used as traditionally the aluminum alloy outer cover (not shown) of the heaviness on leading edge of a wing surface.The variation range that the thickness of this aluminum alloy outer cover is general is 0.025 inch to 0.190 inch, and big thickness is that the aircraft that loads on 100 passengers or the more high-capacity trade route adopts.Device 10 usefulness common method is fixed on the remainder 200 of wing structure, for example, flushes make-up machinery fastener 50 or gluing connection method is fixed with shown in Figure 1.This structure (for example because impact failure) is when needed changed device 10 in the outfield.
Fig. 2 illustrates a kind of deicer 20 according to most preferred embodiment of the present invention, and this device 20 has a superficial layer or uppermost layer 22, and the modulus of elasticity of the material of this uppermost layer is at least 40,000KPa.Be right after uppermost layer 22 below be the crust bonding layer 24 of one layer of polymeric material.Be right after crust bonding layer 24 below be a kind of mechanism 26 that produces release power and displacement.Be right after this mechanism 26 below be a kind of interior bonding layer 28 of polymeric material.It below interior bonding layer 28 a kind of fibre-reinforced composite material substrate 30.There is shown and on the outside face 23 of uppermost layer 22, adhering to one deck ice 18.
US Patent № .4,706,911 disclosed a kind of expandable tubular that makes in the member with integral surface separating capacity of the present invention that is applicable to produces control system and the high pressure valve that fluid pulsation expands, and the present invention is with reference to this structure.US Patent № .4,873,647(R.M.Hohenshil and J.C.Putt) set forth the most preferred embodiment of air pulsing transfer valve, the present invention is also in conjunction with reference to its content.
Fiber reinforced polymer matrix composite substrate 30 strengthens thermoset polymer matrix composite by the multilayer byssaceous material and constitutes.This filamentary material and to make its technology that is combined into the laminar composite structure be on record.Series of factors is depended in the selection of concrete material and concrete structure, comprises characteristic, bending stiffness, torsional stiffness, leading edge resistance to impact, general thickness restriction and the overall weight restriction of the wing of this device of forming leading edge portion.The most preferred embodiment of apparatus of the present invention comprises a kind of by graphite or carbon fiber reinforced epoxy resin-base composite material substrate 30.Other high modulus and strength fiber as: aromatic poly amide and glass fibre etc. can use separately or be used in combination with the other types fiber.
Fig. 3 illustrates and is in the deicer 20 that strained condition and ice pellets 19 have been dished out, and its structure is identical with structure shown in Figure 2.Device shown in Figure 2 is in and stops body state or non-stress state, and has ice sheet 18.During work, high pressure gas (being generally air) fill in the expandable tubular 27 with the pulsation form, when gas pulses when the pipe, the introducing of above-mentioned fluid with regard to make uppermost layer 22 produce a kind of fast and the distortion of moment.The work of apparatus of the present invention 20 is generally speaking as US Patent № .4, and 706,911 and № .4,747,575 is described such, if tell additional expandable tubular (this specification sheets is not shown) from main bulged tube, just as US Patent № .4,826,108 is described the same.These gas pulses produce constant in expandable tubular 27 pressure changes, thus the distortion that makes the ice sheet on the surface 23 that covers deicing organ pipe 27 produce a series of constants, and this gets rid of with regard to causing ice sheet 18 to be broken into ice pellets 19.The typical supply gas pressure of air being introduced the quick-action valve of inflatable 27 is at least about 1000Psig(6894KPa), be preferably 1500Psig(10340KPa), and can surpass 2000Psig(13788KPa).
Applicant is surprised to find that, know already with people, specially be fixed to original covering of aircraft or the structure on other external surface of objects of wanting deicing is compared with bonding or mechanical means, the integral de-icer device comprises that the application of composite material substrate in metal sheath pneumatic de-icing device improved performance significantly.So far, deicer all is to manufacture a kind of liner or protecting sleeve that is applicable on the prototype structure covering that is fixed to wing separately, and this structure is referred to as deicing pad or deicing cover.In contrast, in the present invention, deicer is used for replacing by the prototype structure covering and separately makes and the combination of the auxiliary deicer that fixedly gets on.Applicant finds that the present invention has good anti-rainwater etch ability, can satisfy the requirement of airplane industry to this respect.On the contrary, the anti-rainwater etch ability side of one type of prior art syringe is much lower, and it can the representative type failure occur owing to the fracture that is accumulated in the outer ice sheet on the metal skin in the rainwater etch test.Feature performance benefit of the present invention is listed as the explanation of each example as follows.
Example 1
The structure of sample 1 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (natural rubber glueds joint the agent layer)
(natural rubber)
The expandable tubular type assistor of ###()
// // // // (laminated type lining cement)
＊＊＊＊＊＊＊）
* * * * * *) (aluminium substrate)
＊＊＊＊＊＊＊）
Rainwater etch results-1 hours 30 minutes.
The structure of sample 1 is represented comprehensive existing low-pressure pneumatic ice removal technology and the resulting result of high-pressure pneumatic pulse technology.The viewed best rainproof water logging erosion performance of this structure is 1 hour 30 minutes, arrives 1 hour 30 minutes, and crackle appears in titanium alloy surface.
Example 2
The structure of sample 2 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (nitrile phenol primer)
The expandable tubular type assistor of ###()
(nitrile phenol glued membrane)
========(air curing joint cement)
＊＊＊＊＊＊＊）
* * * * * *) (aluminium substrate)
＊＊＊＊＊＊＊）
Rainwater etch crystallization-2 hour.
With used natural rubber based joint cement in nitrile phenol primer and the nitrile phenol glued membrane replacement example 1 afterburning displacement mechanism is adhered on the titanium alloy uppermost layer.As Fig. 1, anti-icer is adhered at titanium alloy-based the end with the laminated type joint cement.Viewed best rainproof water logging erosion performance is 2 hours.At 1 hour half, see a crackle first.Run up to 2 hours at the trial, cracks can spread, part failure.
Example 3
The structure of sample 3 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (nitrile phenol primer)
The expandable tubular type assistor of ###()
========(air curing joint cement)
＊＊＊＊＊＊＊）
* * * * * *) (aluminium substrate)
＊＊＊＊＊＊＊）
Rainwater etch crystallization-2 hours 45 minutes.
Replace sample 2 used laminated type joint cements to come the bonding aluminium substrate except glued joint agent with room curing, the structure of sample 3 is identical with sample 2.When carrying out the rainwater etch test, at 2 hours 30 minutes, the sample edge began to occur crackle.At 3 hours halfs, observe tangible internal fissure and interior etch.Test proceeds to timesharing in 2 hours 45, and part is determined and can not re-uses.
Example 4
The structure of sample 4 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (air curing primer)
)))))))) (air curing adhesive agent)
(nitrile phenol glued membrane)
The expandable tubular type assistor of ###()
========(air curing adhesive agent)
＊＊＊＊＊＊＊）
* * * * * *) (aluminium substrate)
＊＊＊＊＊＊＊）
Rainwater etch crystallization-30 minute.
Glueing joint agent with room curing adheres on its adjacent layer titanium surface layer and aluminium substrate respectively.Rainwater etch test only 30 minutes is just observed its top layer and was lost efficacy (fatigue cracking occurs and peel off).
Example 5
The structure of sample 5 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (urethanes joint cement)
The expandable tubular type assistor of ###()
＊＊＊＊＊＊＊）
* * * * * *) (aluminium substrate)
＊＊＊＊＊＊＊）
Rainwater etch results-1 hours 30 minutes.
The lower-left side of observing sample 5 before test has a crackle.Along with the lengthening of rainwater etch test time, original crackle is extended to the fracture in the titanium epidermis, occurs peeling off around the breach thereupon.Test after 1 hour 30 minutes, part is determined and can not re-uses.In the time of about 2 hours 30 minutes, judge that sample is entirely ineffective.
Example 6
The structure of sample 6 is as follows:
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (nitrile phenol primer)
The expandable tubular type assistor of ###()
＊＊＊＊＊＊＊）
* * * * * *) (composite material substrate)
＊＊＊＊＊＊＊）
Rainwater etch results-7 hour did not lose efficacy.
Each sample in example 1～6 according to the requirement of maker, can use commercially availabie joint cement material.The titanium alloy surface layer is that 0.005 inch thick Ti-15V-3Al-3Cr-3Sn(is by AMS4914) alloy, carry out anodic oxydation treatment with chromic acid to wanting bonding surface.Aluminium substrate or bottom are made by the 6061T6 alloy, and profile is shown in Fig. 4～6.The total length of aluminium substrate is 3 inches, and leading-edge radius is 0.50 inch, and wall thickness is 0.25 inch, and bottom-to-top-height is 1.25 inches.According to the requirement of maker, nitrile phenol glued membrane (AF32 of 3M company, 10 μ are thick) can use with its nitrile phenol primer that replenishes.Before using nitrile phenol glued membrane, be not coated with primer in the composite material substrate.
The preparation of sample 6 comprises two key steps.The first step, the titanium alloy surface layer is adhered on the skin of nitrile phenol glued membrane, and in the hot air autoclave, keep carrying out in 1 hour partly solidified down in 350 temperature and about 3 atmospheric pressure about down, make and force the afterburning district and the internal layer of nitrile phenol glued membrane to bond together.Second step, soak the way of internal layer that material adheres to nitrile phenol glued membrane and the graphite epoxy is given soak the composite material substrate and adhere on the formed structure of step 1 by successively the graphite epoxy being given, more formed assembly set is put into the hot air autoclave and kept 1 hour down in 350, about 3 barometric pressures.Gained sample 6 carried out the rainwater etch test after 7 hours, only observed slight erosion in the sample both sides of the edge, and any damage or erosion are not seen in other place.
The rainwater etch sample of example 6 is identical with the overall dimensions and the leading-edge radius of the sample of example 1～5.The nominal thickness of fiber reinforced composite substrate is 0.100 inch.Along the trailing edge of each sample, one group of counter bore is arranged.Sample is fixed on the conv on the rotating blade that is contained in rainwater etch test device by one group of sunk serew.The method that conv is fixed on the blade is identical with sample 1～5.
The rainwater etch test method (method I) of sample 1～6 is as follows.With mechanical means sample is fixed on the spiral arm of experimental set-up.It is 500mph that the adjustment said apparatus makes the speed of sample, and being equivalent to the spiral arm rotating speed is 1400rpm.The speed of current is adjusted to 0.8 gallon per minute, to form a kind of per hour 1 inch and raindrop diameter is about 1.5mm～the rainy speed of 2.0mm.Each sample of sample 1～6 all uses same device and above-mentioned condition to test.
In order to confirm that sample 6 has good anti-rainwater etch ability, has prepared the additional sample with following array structure.
Sample 7
--------(0.005 inch thick titanium alloy surface layer)
++ ++ ++ ++ (nitrile phenol primer)
The expandable tubular type assistor of ###()
＊＊＊＊＊＊＊）
* * * * * *) (graphite-epoxy composites substrate)
＊＊＊＊＊＊＊）
Rainwater etch results-4 hour 30 minutes flawlesses.
Sample 8
--------(0.005 inch thick nitriding titanium alloy surface layer)
++ ++ ++ ++ (nitrile phenol primer)
The expandable tubular type assistor of ###()
＊＊＊＊＊＊＊）
* * * * * *) (graphite-epoxy composites substrate)
＊＊＊＊＊＊＊）
Rainwater etch results-4 hour 30 minutes flawlesses.
Shape sample 7 and 8 as shown in Figure 7 carries out rainwater etch test (method II) in the mainframe originating firm.The size of sample is as follows: total length is at least 4 inches, the radius of leading edge 71 is 0.50 inch, its radian is 170 degree, the upper and lower plane area 72,73 of leading edge extends back 1.40 inches with the angle with respect to 78 one-tenth 20 ° of sample chordwise from the leading edge arc, and the upper and lower plane area 74,75 of back extends back about 1.4 inches with the direction that is parallel to sample chordwise 78 from separately frontal plane district 72,73.The radius that connects each connecting portion 76,77 of forward and backward plane area is 0.06～0.25 inch.Test condition comprises: spot speed is 600mph in the sample, and the water spray velocity is per hour 3～4 inches, and drop diameter is 1.5～2.0mm.The minimum performance standards of aircraft factory comprises requirement under these conditions through the rainwater etch test after 4.5 hours, and the feel of surface finish is that 240 sand is low smooth than granularity.The performance of sample 7 and 8 in this test surpasses common aluminum alloy aircraft skin.
Except from the use viewpoint is indicated in addition, all pressure are gauge pressure.
Framing member with integral surface separating capacity of the present invention can be with following method manufacturing: make a kind of shape and the corresponding standard model of aerofoil profile that will fit into leading edge device.Preferably a kind of leading edge device that can make begins to pile up from the high-modulus top layer of its outside, arrives the former of its bottom that is connected with wing part gradually inwards.The method that whole device is connected on the wing generally adopts machanical fastener, for example concave surface or sunk serew or rivet.
Be similar to the embodiment shown in Fig. 1,2 and 3 and have the manufacture method of device of Fig. 7 CONSTRUCTED SPECIFICATION as follows: the one side that titanium-alloy thin-plate will be sprayed fine mist nitrile phenol primer (according to the 3M company product of originating firm guide, code is EC3901) is carried out anodic oxydation treatment.According to joint cement originating firm guide the titanium alloy top layer that is coated with primer is toasted then, this example is about 180 °F, 30 minutes.
Have and use the expandable tubular member of required size to make by the fabric that scribbles poly-mer.In example 7 described most preferred embodiments, use about 0.007 inch thick nylon fabrics, the square weave pattern of weave pattern and solid matter, one side scribble the AF32 nitrile phenol resin of 3M company, about 0.015 inch of the gross thickness of coating.The coated fabric tapered cut is become length with the width identical cloth required with each pipe, when cutting out, make the length direction of warp thread and cloth keep about 45 ° oblique angle.Its width was about 1～about 2.5 inches when general pipe flattened.When needs make pipe lay along the minor radius district for example to stride across a leading edge, just use the less pipe of width.With one deck teflin tape or width and want cooresponding other suitable non-adhesive material of width of the pipe of moulding to be put on each bar pipe fabric strip.The forming method of each pipe be with this coated fabric bar along its length direction nest, and make it wrap in the outside of non-adhesive material layer and form an overlay region along longitudinally.The most handy a kind of have width and the length polytetrafluoroethylene extra play (calling the base bar in the following text) that thickness is bigger with fabric strip is identical be put into the above-mentioned fabrics bar above.This base bar helps to make the coated fabric bar to make pipe, and preferably allows a side of belt strap coating towards the inside of pipe.In next step Fabrication procedure, above-mentioned polytetrafluoroethylene film can prevent that adjacent nitrile phenol coated fabric is solidified togather.Above-mentioned polytetrafluoroethylene belt or other suitable release film or handled thing can be retained in the finished product structure.When using off-tape and not planning to remove it later on, it should be adhered to a side of pipe.Each pipe is put into former respectively by its finished product framing member state separately and solidify at autoclave.After the Pipe forming operation, polytetrafluoroethylene base bar is taken out.
After each pipe solidifies, it is processed an aperture, and be stained with a joint for each pipe with other glued membrane and fabric intensifier.In some most preferred embodiment, an inlet union and an outlet connector are installed respectively in the close opposite end of pipe.The internal channel of inlet union is positioned at and the hithermost end of pulsation transfer valve, and in it and the place that expandable pipe component is connected, has formed the elongated slot of a band circular end surface.Outlet connector has circular internal channel.After installing joint, cling with glued membrane with for example folding method sealing and other at the two ends of pipe.The subassembly of gained pipe and joint is again with making the identical whole coating one deck of coated fabric of pipe, put into former then, position in mould should be the position that its finished product structure is occupied, and reinstalls in the vacuum bag and these parts further are solidified togather.The bending of using former can guarantee that subassembly is finished as mould cooperates.Solidify the back and from mould, take out subassembly.
In former, to add last layer mold release and/or release fabric or impel the subassembly after the heatcure from former, to take out easily with other method.
The titanium alloy surface layer is fitted on the profile of former.The outer bonding layer of the AF32 nitrile phenol glued membrane of 3M is added on the titanium alloy surface that coats primer and toasted, the heating of reusable heat air gun, with hand it is compressed simultaneously.Before both put into former, preferably earlier the outer bonding layer of glued membrane is added to and is placed on a plane for example on the titanium alloy surface layer on the bench board, be adjacent to than being easier to like this.After sticking glued membrane, one deck reinforced fabric is attached to the inside face of uppermost layer.Glued membrane also may be by fiber reinforcement.
The above-mentioned subassembly of being made up of pipe, joint and fabric covering layer that is cured is put on the outer bonding layer in the mould.Arrive this, the assembly set of uppermost layer, outer tack coat and subassembly was solidified 1 hour and be bonded together.
After with said method uppermost layer and subassembly being bondd, each layer that will form the composite material substrate again is added on the part that will make, and this moment, whole assembly still was retained in the former.The best method that forms substrate is that some epoxy prepreg reinforced fabric (for example the R6376/CGG108 of Ciba Geigy company, a kind of graphite fiber epoxy gives and soaks material) layer are sticked layer by layer continuously, till finishing required substrate.Finish substrate give soak the material lamination after, again assembly is put into autoclave and is cured.For sample 7 structures used nitrile phenol and epoxy system, best cure condition is 350,3 barometric pressures (dry air), 1 hour.The condition all similar that each above-mentioned curing schedule is used.At last, from autoclave, take out part and mould, from mould, take out part again.
Immerse oneself in to install with machanical fastener for convenience, the titanium alloy skin is pressed and boring in the place that will be connected with wing.In type, behind the curing schedule, part is got out through hole finishing all in these indentations place.
After this, as shown in Figure 1 fabricated part is installed to correspondingly on the framing member with rivet or screw.When the structure of this part was connected with the conduit that communicates with the fluid pulsation generation device, the import of each pipe just can be incorporated into pneumatic pressure pulses in the expandable members.
On the other hand, if the bending spring of mould is enough big, when following flat preformed member is put into mould, pipe can not bend or the situation of fold under, for convenience's sake.Can be on a flat running surface, uncured pipe and joint are added on the assembly set of uppermost layer and outer glued membrane and form a preformed member.If the radius of former is too little, then when being put into mould, flat preformed member will bend or fold.If find pipe or its cylinder-packing fabric this bending or fold taking place, is preferably in preformed member and puts pipe again after putting into former.
After at length having set forth the present invention, having comprised the mechanism that produces air pulsing power and displacement, just can believe: can replace other any thin mechanism that can produce planar forces and displacement and put into being subjected in the sensillary area of glued membrane bedding void formation, for example adopt US Patent № .4,690,350(Haslim etc.) and US Patent № .4, the thin board type electromagnetic force and the displacement generating mechanism that are suitable for of being set forth 875,644(Lowell J.Adams etc.).The electromagnetic force of Adams etc. and displacement generating mechanism comprise a pair of board-like array, and each array is made up of one group of spaced-apart parallel strip conducting element.The conducting direction of these conducting elements is such, promptly any electric current in conducting element all with the conducting element of second board-like array in the direction of opposite current flow.Is interconnected like this between conducting element preferably, that is, makes that the electric current in the adjacent conductive element flows with same direction in the first board-like array, the electric current in second board-like array in the adjacent conductive element then flows with the direction opposite with it.First and second arrays spatially coextend, and pressing close to of laminating type each other, and therefore the conducting element of the first and second board-like arrays is parallel to each other basically.Conducting element is mutual electrical isolation to each other.To the big current impulse of conductive member supply, the first and second board-like arrays are separated by a power supply fast and consumingly, thereby the outer fast speed that takes place of the high-modulus that is coated with ice sheet is moved.
Though above in conjunction with some embodiment, comprise most preferred embodiment and preferably embodiment set forth the present invention, Aircraft Familiarization deicing technical personnel will be very clear, obviously can adopt its other remodeling.These remodeling also comprise the content of claims of this specification sheets and appendix certainly.Also can use different joint cement materials.Expandable pipe also can directly adhere in uppermost layer and the substrate needn't separately use the glued membrane adhesive linkage.The metal package layer also can be handled, and further improves its hardness or reduces its bonding coefficient to ice sheet.The metal package layer also can have the fiber-reinforced resin backing layer to improve for example ability of hail and bird impact of its shock resistance.In single part, also can adopt the afterburning displacement mechanism of comprehensive pneumatic pressure pulses and electric excitation.The composite material substrate does not require that homogeneous thickness or whole profile surface all have uniform structure, and can make different sizes and performance on different positions according to different operatings needs.In particular cases, can suitably strengthen in contiguous composite material substrate with surplus mechanical connection point of wing structure place.Expandable pipe component can be arranged along the described wing spanwise of Fig. 1, perhaps arranges by the chordwise (not shown) or arranges to improve its performance by comprehensive above-mentioned direction.The orientation of pipe is preferably determined according to special application scenario by rule of thumb by the personnel that are skilled in technique.
Claims (30)
1, a kind of framing member with integral surface de-icing capability comprises:
(a) substrate,
(b) Bao afterburning displacement mechanism;
(c) one deck bonds to the thin uppermost layer on above-mentioned substrate and the above-mentioned afterburning displacement mechanism, wherein, above-mentioned afterburning displacement mechanism is between above-mentioned substrate and above-mentioned outside face, it is characterized in that, described substrate is the composite material that high tensile modulus non-metallic fibers strengthens basal body structure, and described outside face has high tensile modulus.
2, according to the framing member of claim 1, it is characterized in that, above-mentioned substrate by several layers fiber reinforcement thermosetting can matrix composite stacked adding form.
According to the framing member of claim 2, it is characterized in that 3, the inside face of above-mentioned outside face is bonded with one deck fiber-reinforced polymer-matrix material.
According to the framing member of claim 2, it is characterized in that 4, above-mentioned afterburning biasing member comprises an expandable pipe component at least, the position of this tubular member can make uppermost layer owing to corresponding mobile is made in its fluid pulsation expansion.
5, according to the framing member of claim 4, it is characterized in that, above-mentioned inflatable tubular members is made through curing by one deck scribbles the material of poly-mer at least one side surface fabric at least, and this inflatable tubular members is adhered between the upper and lower layer of this structure by joint cement.
According to the framing member of claim 5, it is characterized in that 6, it comprises the mechanism that can make above-mentioned expandable tubular expand into required degree in less than 0.1 second time.
According to the framing member of claim 6, it is characterized in that 7, it comprises the mechanism that can make above-mentioned expandable tubular make pulse expansion.
According to the framing member of claim 4, it is characterized in that 8, above-mentioned uppermost layer is metal.
9, framing member according to Claim 8 is characterized in that, is bonded with the fibre-reinforced polymeric material of one deck on the inside face of uppermost layer.
According to the framing member of claim 4, it is characterized in that 10, above-mentioned uppermost layer is a titanium alloys.
According to the framing member of claim 4, it is characterized in that 11, above-mentioned uppermost layer is plastic.
According to the framing member of claim 4, it is characterized in that 12, above-mentioned uppermost layer is a polyether etherketone system.
According to the framing member of claim 4, it is characterized in that 13, above-mentioned substrate is formed by one or more fibre-reinforced epoxy matrix composites stacked the adding in carbon, graphite, aromatic poly amide and the glass fibre by several layers.
According to the framing member of claim 4, it is characterized in that 14, above-mentioned uppermost layer bonds on the expandable member with nitrile phenol or plasticising epoxy jelly membrane.
According to the framing member of claim 2, it is characterized in that 15, above-mentioned afterburning displacement mechanism bonds in the substrate with one deck nitrile phenol or epoxy glue.
According to the framing member of claim 2, it is characterized in that 16, above-mentioned afterburning displacement mechanism is made up of calutron.
17, framing member according to claim 16, it is characterized in that, above-mentioned calutron comprises by one group of parallel spaced apart and be the first board-like array formed of first conducting element of electrical isolation and by one group of parallel spaced apart and be the second board-like array that second conducting element of electrical isolation is formed each other each other, electrically connect between above-mentioned conducting element, so that make the direction of current of each conducting element in the first adjacent conducting element identical, and make direction of current in the second adjacent conducting element and the current opposite in direction in first conducting element, therefore between above-mentioned first and second conducting elements, produce a kind of electric repulsion, this power makes above-mentioned first and second conducting elements separately, the above-mentioned first board-like array and the above-mentioned second board-like array spatially be basically coextend and be pressing close to of laminating type each other, therefore, above-mentioned first and second conducting elements are parallel basically.
According to the framing member of claim 16, it is characterized in that 18, above-mentioned substrate is formed by stacking with one or more composite layers that strengthen matrix in carbon, graphite, aromatic poly amide and the glass fibre by several layers.
19, when the framing member of assembling claim 1 and wing structure, will be fixed on the wing structure according to the framing member of claim 1, and constitute the leading edge surface of wing by it.
20, when the framing member of assembling claim 4 and wing structure, form the leading edge surface of this assembly set by framing member according to claim 4.
21, according to framing member and a kind of wing structure of claim 16, it is characterized in that, constitute the leading edge surface of above-mentioned both assembly sets by framing member according to claim 16.
According to the framing member of claim 4, it is characterized in that 22, when under 500mph it being tested 4.5 hours according to examination 1～6 test method, it still has anti-rainwater etch drag.
According to the framing member of claim 4, it is characterized in that 23, when under 600mph it being carried out 4.5 hours test according to the test method of sample 7 and 8, it still has anti-rainwater etch drag.
24, a kind ofly make a kind of method with framing member of integral surface de-icing capability, this method comprises:
(a) provide a cavity block;
(b) a metal package layer and an outer bonding layer are put into mould;
(c) the thin afterburning displacement mechanism of moulding and it is adhered on the above-mentioned outer adhesive linkage;
(d) an interior adhesive linkage is adhered on the afterburning displacement mechanism;
(e) strengthen the polymer matrix composite layer with multi-layer fiber and constitute a composite material substrate, and this substrate is adhered on the above-mentioned interior adhesive linkage;
(f) fabricate block of above-mentioned uppermost layer, afterburning displacement mechanism and substrate is solidified and bond together, form above-mentioned single-piece framing member.
According to the method for claim 24, it is characterized in that 25, this method also is included in afterburning displacement mechanism is adhered to before the above-mentioned uppermost layer, by afterburning displacement mechanism shared position in the finished product framing member afterburning displacement mechanism is solidified earlier.
26, according to the method for claim 24, it is characterized in that, this method also is included in afterburning displacement mechanism is fitted into before the said structure spare, elder generation's moulding contains the afterburning displacement mechanism of at least one inflatable tubular members of being made by the fabric that scribbles poly-mer, and the shape that makes above-mentioned inflatable tubular members be solidified into it to occupy in the finished product member.
27, according to the method for claim 26, it is characterized in that, this method also comprises by what cut sth. askew one and is coated with the method that outside that the polymer fabrics cloth wraps in a non-layer of adhesive material of extending along its length forms an overlay region of extending along its length, makes at least one above-mentioned inflatable tubular members.
According to the method for claim 27, it is characterized in that 28, this method was superimposed together the two-layer non-layer of adhesive material that equates basically earlier before above-mentioned fabrics is made tubular member, wherein one deck removes after tubular member solidifies.
29, according to the method for claim 27, it is characterized in that, this method also comprises joint is installed on each tubular member that has solidified, and clad with the fabric that one deck scribbles poly-mer on the combination of joint and tubular member and form a subassembly, and before this subassembly is put into said structure spare, subassembly is solidified into the bending spare that the position occupied with it is complementary in the finished product framing member.
According to the method for claim 24, it is characterized in that 30, the inboard that this method also is included in the metal package layer adds a fiber-reinforced resin lining.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US43217189A | 1989-11-06 | 1989-11-06 | |
| US07/4321715 | 1989-11-06 | ||
| US432,715 | 1989-11-06 | ||
| US07/432,715 US5098037A (en) | 1989-11-06 | 1989-11-06 | Structural airfoil having integral expulsive system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1051537A CN1051537A (en) | 1991-05-22 |
| CN1027531C true CN1027531C (en) | 1995-02-01 |
Family
ID=27029382
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 90108905 Expired - Fee Related CN1027531C (en) | 1989-11-06 | 1990-11-06 | Structural airfoil having integral expulsive system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1027531C (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9108735B2 (en) * | 2009-05-13 | 2015-08-18 | Tmc Aerospace, Inc. | Electro-expulsive de-icing system for aircraft and other applications |
| EP2650220B1 (en) * | 2012-04-11 | 2015-07-15 | Goodrich Corporation | Deicer zones with shedding-enhanced borders |
| CN105626396A (en) * | 2015-12-29 | 2016-06-01 | 北京金风科创风电设备有限公司 | Blade deicing device, wind generating set and blade deicing method |
| CN111231376B (en) * | 2019-12-03 | 2023-03-24 | 惠阳航空螺旋桨有限责任公司 | Electric heating unit die and method for preparing electric heating unit assembly by using same |
| CN112550665B (en) * | 2021-02-24 | 2021-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Aircraft defroster based on elastic skin |
-
1990
- 1990-11-06 CN CN 90108905 patent/CN1027531C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1051537A (en) | 1991-05-22 |
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