CN107984774A

CN107984774A - A kind of composite material empennage technology of preparing

Info

Publication number: CN107984774A
Application number: CN201711352119.5A
Authority: CN
Inventors: 陈永务; 严治平; 陶文斌; 孟宪斌
Original assignee: JIANGXU CHANGJIANG CHEMICAL CO Ltd
Current assignee: JIANGXU CHANGJIANG CHEMICAL CO Ltd
Priority date: 2017-12-15
Filing date: 2017-12-15
Publication date: 2018-05-04

Abstract

A kind of composite material empennage technology of preparing, including step:Structure design, including leading edge radome fairing and wing main body two parts；Material selection, using resin base fibrous composite；Moulding process, after first leading edge radome fairing is prepared using vacuum aided die press technology for forming, then the compression molding together with wing body；Combination, the leading edge radome fairing that will be prepared, is inserted on the good empennage body of laying according to structural requirement, is put into mould；Compacting；Post-processing.Have the characteristics that tail size precision is high, meeting design requirement, tail structure, complete, deflection is no more than 5%.

Description

A kind of composite material empennage technology of preparing

Technical field

The present invention relates to a kind of composite material empennage technology of preparing, particularly a kind of empennage being provided on rocket is (below Abbreviation empennage) technology of preparing, be rocket system aerodynamic configuration d type part, be installed on the afterbody of Sounding Rocket System, it is main to use In stablizing sounding rocket flight attitude.

Background technology

High-speed aircraft such as intercontinental missile, artificial satellite, spaceship etc., from outer space, atmospheric reentry is, its speed Degree is already close to relatively low damage stone speed.During ground is gone back to, situation of being heated is very serious.When satellite goes back to ground with 8km/s speed, stay Point temperature can be up to 8000~10000K, and intermediate range missile atmospheric reentry, its head temperature is in 5800K.In order to make bullet Head and reentry vehicle are not burned out, it is ensured that when warhead passes through aerial flight, bullet contour structures is kept complete, kept There is normal operating condition in bullet and aircraft cabin（Temperature, pressure etc.）, it is anti-that heat must be carried out to bullet and reentry vehicle Shield.

Since temperature is higher, many materials cannot withstand, as the intensity of steel construction can be reduced when temperature is higher than 973K, aluminium Magnesium alloy can only work in below 673K, and explosive requires temperature to be no more than 353~373K, nuclear payload charging and built-in precision Instrument then requires temperature to be no more than 323~333K, therefore, it is necessary to take some special measures to solve the problems, such as head heat release, i.e., It is so-called to overcome due to thermal boundary caused by Aerodynamic Heating.

Although aircraft is heated seriously, during reentering, heated time is shorter, is heated to intermediate range or the intercontinental bullet that reenters Time is about（20~40）S, to artificial satellite and airship, its heated time also exists（200~500）s.

For above-mentioned severe rugged environment, the thermal protection method of use usually has heat sink method, radial pattern solar heat protection method and ablation Method.Using heat sink method specific heat need to be used big, the good metal of thermal conductivity, such as copper, beryllium and its alloy.But generally this kind of material mistake Go with guided missile warhead, because easy melting deformation, performance are not very good under high temperature.Radial pattern solar heat protection method is with height radiation and low suction Receipts are characterized, in the case of high hot-fluid, using being restricted.So ablation is current most widely used solar heat protection method.

Physics, chemical change of the actual ablation process with large amount of complex, but roughly, following mechanism is followed, with Exemplified by high silicone/phenolic resin material, the substantially 1. thermal capacitance heat absorption of material of its ablative thermal protection mechanism in itself;2. the heat of matrix resin point Solution and carbonization heat absorption;3. the fusing heat absorption of high silica fiber;" 4. thermal resistance " effect;5. the chemical reaction heat absorption on carbon-coating surface.Institute It should be set about with evaluating ablator from the following aspects:

(1) specific heat is big, and substantial amounts of heat can be so absorbed in heat of ablation journey.

(2) thermal conductivity factor is small, and the part that can so make into high temperature is only limitted to surface, and heat is difficult to be transmitted in internal structure Go.

(3) density is small, in aerospace field, should reduce the gross weight of manufacture material to greatest extent.

(4) Recession rate is small, i.e. material speed of eating away in hot environment is small.

The composite material formed based on matrix, reinforcing fiber and interface phase is special due to its excellent mechanical property, function Property, material designability and easy the advantages that being manufactured, be widely used in each industrial field, especially various matrixes Advanced composite material possessed by high specific strength, high specific stiffness, high temperature resistant, erosion resistant, conduction, heat conduction, thermal coefficient of expansion it is small, Fatigue resistance is good, damping capacity is good, resistance to ablation, resistance to erosion, anti-width are penetrated, inhale ripple, transducing and other physical functions, can be fine Ground meets the requirement of ablation resistant material.It can be said that application of the composite material in ablation resistant material will have great future.

Ablator is mainly used in the form of fibre reinforced plastics and coating, wherein the polymer used has epoxy, phenol Aldehyde, organosilicon and polyurethane.The performance of ablation resistant material is affected by many factors, for example the composition of base-material, structure and processing work Skill influences, and the selection of wherein matrix is even more important.Matrix is used as filler and various additives in ablator manufacturing process Adhesive, but vital influence is played on the performance of ablator.The heat resistance of wherein resistance to ablative composite material is from root Said in sheet be exactly matrix heat resistance.It must select that heat resistance is high, carbon forming rate is high or the basis material of resistance to ablation.

Polyurethane can be used for the extremely low ablation foamed plastics of manufacture density.What organosilicon was used for ablator is with bullet The polymethyl siloxane and polymethylphenylsiloxane of property.Larger thermoplasticity is presented in the resin at high temperature, it is thus possible to disappears Except hot pressing, but abrasion resistance is not as good as phenolic aldehyde and epoxy resin because it formed after being pyrolyzed be not carbon-coating but silica.Ring The mechanical property of materials is good made of oxygen tree fat, but carbon forming rate of the resin itself is relatively low, and only 15.6%.Into carbon after phenolic resin pyrolysis Rate is high, and general reachable 50% or so, using appropriate technique carbon forming rate can be made to be higher than 60%.The carbon formed after resin thermal degradation is A kind of material of polyacene structure, it can be strongly adhered to filler together, to resist washing away for hot-fluid.Therefore high carbon forming rate Phenolic resin is used to manufacture ablator, has preferable flushing resistance.Table 1 has made pair the ablation property for commonly using high polymer Than the ablation property of phenol-formaldehyde resin modified is preferable in common high polymer.AR is ablation velocity in table.

Table 1 often uses the ablation property of high polymer

Polymer name	A·R/mm·s^-1	I₂₀₀/s	API/mm·s^-2
				Polymethyl methacrylate	0.46	11.6	7.93
Polytetrafluoroethylene (PTFE)	0.52	11.8	8.8
				Polyurethane resin	0.72	8.0	18.0
Phenolic resin	0.11	39.6	0.56
				Epoxy resin	0.36	11.0	6.5
Organic siliconresin	0.37	14.5	5.2
				Steel 1010 (tester)	0.36	6.0	12
Graphite（AJT）(tester)	0.01	2.2	0.91

Note:(I) experimental condition:3037 DEG C of oxy-acetylene neutral flame temperature, hot-fluid 62.4 × 10⁵/( m²S), sample Thickness 12.7m；

(Ⅱ) I₂₀₀It is that the sample back side reaches the time required at 200 DEG C under above-mentioned flame；

(III) API (Ablative Performanee Index) for ablation performance index API=(mm/s²) 。

The Koo JosePhH in the U.S., which are closed, have studied 29 kinds of ablators, these materials are divided into 3 classes：With various fiber reinforcements Phenolic resin, elastomer and ceramics.He comes from the indexs such as maximum ablation depth, mass loss, the heat of ablation and ablation velocity Make comparisons, show that phenolic resin has the conclusion of optimal comprehensive ablation property.

Phenolic resin is just applied from the 1960s as high temperature resistant and ablation resistant material, as thermosetting property tree One of principal item of fat, it has the advantages of cheap, craftsmanship is good, is still used as the master of resin base ablator so far Matrix resin is wanted, is even more the component of resistance to ablation being widely used in aerospace material at present.It is but rapid with space technology Development, heat resistance and ablation resistance to ablation resistant material resin matrix propose the requirement of higher；On the other hand, traditional phenol Urea formaldehyde is since with medium thermo-oxidative stability, inherent brittleness, the generation of low molecular weight volatile thing is had by condensation curing The shortcomings of.It is difficult to the requirement for meeting higher, therefore the modification of phenolic resin and the phenolic resin of synthesizing new structure are just into resistance to The hot spot of ablator research.

Foreign study situation

The U.S., Russian and other developed countries have larger input in the field always, but due to the sensitiveness in the field, it is crucial Material technology maintains secrecy relatively sternly always, the particularly later research work of the mid-80, the valuable data ten that state's interior energy obtains Divide limited.

Resin base ablation thermal protection composite material experienced with high silicone/phenolic resin and Avcoat5026-39 for representative One stage development, the second stage using first generation carbon/phenolic aldehyde as representative develop, and using advanced carbon/phenolic aldehyde as the 3rd of representative After stage development, low ablation velocity and the control of ablation pattern are tentatively realized, meets high-performance reentry vehicle, planet Detector and high-performance solid engine thermal protection requirements.Later stage, main research emphasis included:Burnt in further investigation

Erosion degrade on the basis of further control ablation degrade, the ablation to different materials varying environment degrade achieve it is deeper The understanding entered, lays a good foundation for thermal protection system selection and material improvement innovation.

Low density carbon/phenolic composite is successfully developed with reducing space probe thermal protection struc ture mass ratio in development PICA (Phenolic Impregnated Carbon Ablator) materials are simultaneously applied to stardust (Stardust) recoverable capsule Heat shield, in about 12MW/m²Under heat-flux conditions, solar heat protection mass ratio is only 22%, is developing Phenecarb Low-density heat-resistant composite material in (Phenolic Carbon) and BPA (Boeing Phenolic Ablator) etc., is being improved While the anti-thermal efficiency, the strength of materials and thermal protection struc ture reliability are improved.

The Apollo Personnel investigation Program number for starting for 1966 to develop " mooncraft also uses low density ablator, and phenol aldehyde glass honeycomb The advantages of filling epoxy novolac adds quartz fibre, fully shows ablator in lattice.

Phenol cyanate resin (PT resins) is reported in the U.S. in 1989 earliest.Its basic framework is phenolic resin, but is wherein drawn People's triazine ring.It has the resistance of the processing performance of epoxy resin, the high-temperature behavior of bismaleimide and phenolic resin at the same time Fire performance.Phenolic resin starts to decompose about more than 200 DEG C, and PT resins will just start to decompose to 440~450 DEG C. In nitrogen, the carbon forming rate about 60% of phenolic resin, and PT resins are 68~70%, this is exactly desired by ablation resistant material 's.Particularly PT resins non-volatility accessory substance, thus in the curing process excellent as the composite property of basis material using it More.

Development of Novel high performance carbon/phenolic composite is with applied to advanced weapon system, as using high intensity Polyacrylonitrile-based carbon fibre and the new high resistance to Ablative resin development of carbon residue with PAA (Polyarylacetylene) for representative New Type of Carbon/carbon/phenolic heat insulating composite material, improves the mechanical property and Burning corrosion resistance energy of material, while further realizes that material is burnt Lose the control of pattern.

PAA is a kind of more advanced matrix of resistance to Ablative resin synthesized first by GE companies of the U.S..It is a kind of height Crosslinked aromatic polymer, only carbon containing and hydrogen.When its major advantage is that this kind of polymer is heated to high temperature in inert environments The volatile matter of only its quality 10% disengages, and carbon forming rate is up to 90%, and hygroscopicity is 0.1~0.2%, is only the 1/50 of phenolic aldehyde, and And its curing reaction is polyaddition reaction, no low-molecular material disengages;It is mainly characterized by glass transition temperature height, pyrolysis temperature Height, pyrolysis peak temperature is 800 DEG C, and thermal decomposition product is mainly hydrogen, is that instead of a kind of high performance resin of phenolic aldehyde.Made of it Carbon fibre composite compactness is good, and ablating rate and mass loss are significantly better than that carbon/phenolic materials.

Studies in China situation

The researchs such as intercalation life show that the carbon forming rate of boron bakelite resin is 70% at 900 DEG C, and more than phenolic resin, (50% is left It is right), the initial decomposition temperature of resin is 424 DEG C, and peak temperature is up to 625 DEG C, and hot property is very excellent.In ablation process, The pyrolysis gas that boron phenolic material produces is less, and the internal pressure of ablation reduces, and is conducive to improve resistance to ablation vertical resolution.Xiao Cuirong points The rocket tube converging portion of glass fiber reinforcement is not pressed into ammonia phenolic aldehyde and boron phenolic, carries out ablation test, Under 3144K, 1.4 MPa, ablation 9.3s, the linear ablative rate of glass fibre/ammonia phenolic aldehyde is 0.253 mm/s, and boron phenolic is 0.084mm/s, is only the former 1/3, and carburization zone is uniformly complete, and quality is hard, and ablation property is substantially better than ammonia phenolic aldehyde.

Hua Youqing etc. is in N₂Atmosphere, to cured molybdenum phenolic aldehyde, 131H at 700 DEG C₄Phenolic aldehyde, ammonia phenolic aldehyde, barium phenolic aldehyde carry out heat Weight analysis, weight-loss ratio are respectively 21.69%, 37.53%, 27.37% and 31.87%, wherein the resistance to thermal degradation performance of Mo-phenolic resin Most preferably, carbon forming rate highest.With the increase of molybdenum content, heat decomposition temperature rises, and thermal weight loss rate declines, and the heat resistance of resin substantially increases Add.This main chain mainly due to aluminium element into people's phenolic resin, o-Mo-0 key connection phenyl ring, the big raising of bond energy husband.Molybdenum phenolic aldehyde/ The linear ablative rate of carbon cloth and ammonia phenolic aldehyde/carbon cloth is respectively 0.348mm/s, and 0.491 mm/s, and ablation resistance improves 20~ 30%, and remain carburization zone that is thick and complete, fine and close, porous and being firmly combined with base material.

Spread out etc. to cured phenylphenol modified phenolic, barium phenolic aldehyde, ammonia phenolic aldehyde and common thermosetting phenolic resin In N₂At 700 DEG C of atmosphere, thermogravimetric analysis is carried out, carbon forming rate is:70.8%、64.0%、60.0%、56.8%.Heat decomposition temperature is then It is followed successively by:449.0℃、405.0℃、355.7℃、420.1℃.The carbon forming rate of phenylphenol phenol-formaldehyde resin modified is up to 70.8%, Carbon forming rate and heat decomposition temperature are excellent far more than ammonia phenolic aldehyde and barium phenolic aldehyde, hot property.Good congruent research shows recklessly, phenylphenol Stretching, compression, bending and the shear strength value and barium phenolic materials of modified phenolic resin composite material are not much different.But oxy-acetylene Linear ablative rate and mass ablative rate are significantly lower than barium phenolic materials, and average linear ablative rate is down to 9 pm/s from 23 μm/s, average Mass ablative rate is down to 23mg/s from 26 mg/s.Barium phenolic materials after ablation, turn white by surface, and carbon cloth aliquation, arch upward, ablation Section has gap, and ablation face is big;And phenylphenol modified phenolic material ablation face blacks, a large amount of phenolic aldehyde carbon, tapered burning are remained Pit, edge carbon cloth also aliquation, section tight, fire-resistance flame ability is preferable after illustrating carbonization.

The Comparision that domestic Sichuan University cares for preferably et al. is representative, they have synthesized the benzoxazine of various structures Resin.Sui the increase of oxazine ring number, the curing crosslink density of resin

Increase, is conducive to the raising of resin carbon forming rate.Resin (PBOZ) carbon forming rate of , Duo oxazine rings is up to 68.0% at 700 DEG C. Polycyclic benzene benzoxazine composite material.Ablation test shows that material surface is essentially smooth, local roughness, and average ablating rate is 0.184mm/s, ablation property are preferable.

Yan Lian lifes et al. are modified PAA using boron phenolic, in the case where not reducing charring rate, hence it is evident that improve The adhesive property of PAA and carbon cloth, make the shear strength of charcoal/PAA composite materials bring up to 11 VIII a, but solidification process by 5.5 VIII a The small molecule discharged is unfavorable to processing and forming；Wang Ming etc. pass through in PAA add Y-1 modifiers, hence it is evident that improve with The interface performance of carbon fiber, the interface shear strength of composite material improve 40%~50%, interlaminar shear strength improve by Nearly 1 times, ablation property is substantially suitable with unmodified resin.

Although China achieves tremendous improvement and breakthrough in terms of resistance to ablative composite material basic research field in recent years, Material as actual use, in addition it is also necessary to consider the processing technology and its total cost of material.To further commenting for ablator Valency is to carry out simulated experiment and flight experiment, investigates using effect in the actual environment, China has in resistance to ablative composite material In terms of actual use in body product, uncorrelated report.

The content of the invention

Its purpose of the invention, which is that, provides a kind of composite material empennage technology of preparing, high, full with tail size precision The characteristics of sufficient design requirement, tail structure are complete, deflection is no more than 5%.

The technical solution realized above-mentioned purpose and taken,

A kind of composite material empennage technology of preparing, including step:

1) structure design, including leading edge radome fairing and wing main body two parts；

2）Material selection, using resin base fibrous composite

a）Resin matrix, using phenol-formaldehyde resin modified, it is desirable to which 900 DEG C of carbon yield/% are 72, and decomposition starting temperature/% is 486；

b）Reinforcing material, using S glass fiber compound materials, it is desirable to density

g/cm³For 2.49, tensile strength GPa is 4.66, and Young's modulus GPa is 85, and fusing point DEG C is 1250；

3）Moulding process, first by leading edge radome fairing using vacuum aided die press technology for forming prepare after, then with one molding of wing body It is molded；

a）Leading edge radome fairing moulding process, including it is leading edge radome fairing film, leading edge radome fairing fabric dividing, leading edge radome fairing laying, preceding Edge radome fairing is suppressed and leading edge radome fairing post-processing；

The leading edge radome fairing film impregnates phenol-formaldehyde resin modified for S glass fabrics, and the control of glue content is solvable 40~45% Property resin content control more than 97%；

Leading edge radome fairing fabric dividing, leading edge radome fairing adhesive plaster sized mold are cut, and quantity is 3；

Leading edge radome fairing laying, the adhesive plaster that will be cut out, is covered on mould with spray gun heating；

Leading edge radome fairing is suppressed, pressing process parameter：100 DEG C, 1~3MPa of pressure, time 5min of temperature；150 DEG C of temperature, pressure 3~5MPa, time 10min；180 DEG C, 5~10MPa of pressure, time 60min of temperature；200 DEG C, 10~15MPa of pressure of temperature, when Between 120min；

Leading edge radome fairing post-processing, the product that will be suppressed, is placed on polishing machine, is processed by shot blasting, remove flash removed and overlap；

b）Empennage body moulding process, including empennage body film, empennage body fabric dividing, empennage body laying, empennage body pressure System and empennage body post-processing；

Empennage body film impregnates phenol-formaldehyde resin modified for S glass fabrics, and the control of glue content is 40~45%, soluble resin Content is controlled more than 97%；

Empennage body fabric dividing, empennage body adhesive plaster size are cut by structural requirement, and quantity is 58；

Empennage body laying, it, is covered on mould by the adhesive plaster that will be cut out in order with spray gun heating；

3 ）Combination, the leading edge radome fairing that will be prepared, is inserted on the good empennage body of laying according to structural requirement, is put into mould In；

4）Compacting, pressing process parameter：100 DEG C, 1~3MPa of pressure, time 5min of temperature；150 DEG C of temperature, pressure 3~ 5MPa, time 10min；180 DEG C, 5~10MPa of pressure, time 60min of temperature；200 DEG C, 10~15MPa of pressure of temperature, time 120min；

5）Post-processing,

（1）The product that will be suppressed, places in punching tooling, according to structural requirement, is processed；

（2）The product that will be suppressed, is placed on polishing machine, is processed by shot blasting, removes flash removed and overlap.

Beneficial effect

The present invention has the following advantages compared with prior art.

Have the characteristics that tail size precision is high, meeting design requirement, tail structure, complete, deflection is no more than 5%.

（1）Tail size precision, meets design requirement；

（2）Quality≤0.8kg；

（3）The suffered shearing in root is 2002.3N, and empennage root institute bending moment is 218Nm, it is desirable in flight course, empennage Structural integrity, deflection are no more than 5%（11.325mm）（Consider safety coefficient f=2）；

（4）2 are shown in Table in the temperature at leading edge 0mm, 35mm, 150mm inside missile wing with surface, it is desirable to meet intensity requirement.

2 empennage Aerodynamic Heating temperature of table

Brief description of the drawings

The invention will be further described below in conjunction with the accompanying drawings.

Fig. 1 is the tail structure schematic diagram of the present invention；

Fig. 2 is the empennage moulding process flow process schematic diagram of the present invention；

Fig. 3 is the leading edge radome fairing moulding process step schematic diagram in the present invention；

Fig. 4 is the leading edge radome fairing adhesive plaster sized mold schematic diagram in the present invention；

Fig. 5 is the leading edge radome fairing pressing process curve map in the present invention；

Fig. 6 is one schematic diagram of empennage adhesive plaster template in the present invention；

Fig. 7 is two schematic diagram of empennage adhesive plaster template in the present invention；

Fig. 8 is three schematic diagram of empennage adhesive plaster template in the present invention；

Fig. 9 is four schematic diagram of empennage adhesive plaster template in the present invention；

Figure 10 is five schematic diagram of empennage adhesive plaster template in the present invention；

Figure 11 is six schematic diagram of empennage adhesive plaster template in the present invention；

Figure 12 is seven schematic diagram of empennage adhesive plaster template in the present invention；

Figure 13 is eight schematic diagram of empennage adhesive plaster template in the present invention；

Figure 14 is nine schematic diagram of empennage adhesive plaster template in the present invention；

Figure 15 is ten schematic diagram of empennage adhesive plaster template in the present invention；

Figure 16 is 11 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 17 is 12 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 18 is 13 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 19 is 14 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 20 is 15 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 21 is 16 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 22 is 17 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 23 is 18 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 24 is 19 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 25 is 20 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 26 is 21 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 27 is 22 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 28 is 23 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 29 is 24 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 30 is 25 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 31 is 26 schematic diagram of empennage adhesive plaster template in the present invention；

Figure 32 is the pressing process curve map of the present invention.

Embodiment

A kind of composite material empennage technology of preparing, including step:

2）Material selection, using resin base fibrous composite

5）Post-processing,

Embodiment

1.1 structure design

The structure design of empennage, as shown in Figure 1.

1.2 material selection

It is well known that resin base fibrous composite is made of reinforcing fiber and resin matrix, compared with metal material, have High specific strength and specific stiffness, designability are strong, fatigue durability is good, wave transparent, good corrosion resistance and the advantages that resistance to ablation, extensively Applied to field of aerospace, become the fourth-largest structural material after titanium, aluminium, steel.In this patent, preferentially using resin Base fibrous composite, which substitutes aluminum alloy materials, has greater advantage.

In the two big materials for forming composite material, resin, which mainly rises to undertake, transmits the functions such as load, burn-out proof, fiber master Play heat-insulated, structural re-enforcement.Must be taken into full account in composite Materials Design using thermal conductivity factor is small, specific heat is big, density is small, The material that ablation velocity is small, intensity is higher.

1.2.1 resin matrix

Resin matrix is various in style at present, and the resin matrix for being commonly used for ablation resistant material mainly has polyurethane type resin, asphalt mixtures modified by epoxy resin Lipid, organic siliconresin class etc., material typical case is shown in Table 3.Wherein polyurethane, polytetrafluoroethylene (PTFE), organosilicon intensity are relatively low, should not make Standby high performance structures material.The mechanical property of materials made of epoxy resin is good, but carbon forming rate of the resin itself is relatively low, is only 15.6%。

Phenolic resin high mechanical strength, carbon forming rate may be up to 60% or more after pyrolysis, and flushing resistance is good, have preferable Comprehensive performance, be widely used to the preparation of resistance to ablative composite material.

The ablation resistance of 3 common resins matrix of table

Polymer name	A·R/ mm·s^-1	I₂₀₀/s	API/mm·s^-2
				Polymethyl methacrylate	0.46	11.6	7.93
Polytetrafluoroethylene (PTFE)	0.52	11.8	8.8
				Polyurethane resin	0.72	8.0	18.0
Phenolic resin	0.11	39.6	0.56
				Epoxy resin	0.36	11.0	6.5
Organic siliconresin	0.37	14.5	5.2

Note:

(I) experimental condition:3037 DEG C of oxy-acetylene neutral flame temperature, hot-fluid 62.4 × 10⁵/( m²S), thickness of sample 12.7mm；

(II) AR is ablation velocity；

(Ⅲ)I₂₀₀It is that the sample back side reaches the time required at 200 DEG C under above-mentioned flame；

(IV) API (Ablative Performanee Index) for ablation performance index API=(mm/s²) 。

Traditional phenolic resin Residual carbon is low, and resistance to mechanical is washed away and ablation energy force difference.To improve this performance, grind at present A variety of resistance to Ablative resins of high Residual carbon are made, such as ammonia phenolic aldehyde, barium phenolic aldehyde, molybdenum phenolic aldehyde, boron phenolic, benzoxazine, phenol triazine tree Fat (PT) and poly- square base hexin (PAA), heat resistance temperature are shown in Table 4.

The heat resistance of 4 modified phenolic of table

Resinous type	900 DEG C of carbon yield/%	Decomposition starting temperature/%
			Barium phenolic aldehyde	58	425
Ammonia phenolic aldehyde	59	420
			Molybdenum phenolic aldehyde	56	424
PT	62	459
			Benzoxazine	65	473
Boron phenolic	70	475
			Make modified phenolic by oneself	72	486
PAA	85	500

As can be seen from Table 4, PAA, self-control modified phenolic, PT and benzoxazine colophony carbon yield and decomposition starting temperature Can preferably, but PAA resin-mades it is standby composite material interlayer shear strength it is relatively low, only 15MPa and expensive, PT and benzo Oxazine resin has substantial amounts of hydrone to separate out, it is necessary to repeatedly deflate, is not suitable for the preparation of this patent empennage in reactive polymeric.

And make the hydroxyl in phenol-formaldehyde resin modified by oneself and substituted by the high triazine ring of heat endurance, the triazine that simultaneous reactions are formed Net structure has excellent heat and oxidation stability again, therefore resistance to elevated temperatures is excellent.Further, since self-control modified phenolic resin Hydroxy radical content reduces in fat, and the association of hydrogen bond weakens between hydroxyl, and in reactive polymeric, anhydrous molecule separates out, and is adapted to this specially Sharp moulding process requirement.

Comprehensive analysis, self-control phenol-formaldehyde resin modified have good dielectric properties, ablation resistance and excellent shaping work Skill, is the material first of this patent design.

1.2.2 reinforcing material

Reinforcing material is one of important component of composite material, and the ablation resistance, mechanical property to empennage have a great influence, main There are glass fibre, high silica fiber, quartz fibre etc., the performance comparison of various reinforcing fiber materials is shown in Table 5.

The performance of 5 various reinforcing fibers of table

As known from Table 5, high silica fiber fusing point is higher, but mechanical property is relatively low.Quartz fibre excellent in mechanical performance, fusing point Height, but it is expensive.Consider, S glass fibre cost performances are the optimal reinforcing fibers for preparing the composite material.

1.2.3 design of material result

Empennage design of material is as a result, be shown in Table 6.

6 design of material result of table

Composition	Material
		Resin matrix	Make phenol-formaldehyde resin modified by oneself
Reinforcing fiber	S glass fibres

1.3 moulding process design

During formed product, composite technology sexual clorminance synchronous with material is made full use of, realizes intensity, 26S Proteasome Structure and Function one Change, ensure quality conformance, effectively reduce process costs, prepared using die press technology for forming.

Empennage prepared by this patent, is mainly made of leading edge radome fairing and wing main body two parts, wherein first by leading edge rectification After cover is prepared using vacuum aided die press technology for forming, then the compression molding together with wing body.Specific moulding process, such as Fig. 2 institutes Show.

1.3.1 leading edge radome fairing moulding process

Leading edge radome fairing moulding process, as shown in Figure 3.

1.3.1.1 leading edge radome fairing film

S glass fabrics impregnate phenol-formaldehyde resin modified, the control of glue content 40~45%, soluble resin content control 97% with On.

1.3.1.2 fabric dividing

Leading edge radome fairing adhesive plaster size is cut by such as Fig. 4 moulds, and quantity is 3.

1.3.1.3 laying

The leading edge radome fairing adhesive plaster that will be cut out, is covered on mould with spray gun heating.

1.3.1.4 compacting

Pressing process, as shown in Figure 5.

1.3.1.5 post-processing

The product that will be suppressed, is placed on polishing machine, is processed by shot blasting, removes flash removed and overlap.

1.3.2 empennage body moulding process

1.3.2.1 empennage film

1.3.2.2 fabric dividing

Empennage adhesive plaster size is cut by such as Fig. 6~Figure 31, and quantity is 58.

1.3.2.3 laying

It, is covered on mould by the empennage adhesive plaster that will be cut out with spray gun heating by 7 order of table；

Table 7 is paved into order

Sequentially	Template number	Quantity
			1	Template one	3
2	Template two	1
			3	Template three	1
4	Template four	1
			5	Template five	1
6	Template six	1
			7	Template seven	1
8	Template eight	1
			9	Template nine	1
10	Template ten	1
			11	Template 11	1
12	Template 12	1
			13	Template 13	1
14	Template 14	1
			15	Template 15	1
16	Template 16	1
			17	Template 17	1
18	Template 18	1
			19	Template 19	1
20	Template 20	1
			21	Template 21	1
22	Template 22	1
			23	Template 23	1
24	Template 24	1
			25	Template 25	1
26	Template 26	2
			27	Template 26	2
28	Template 25	1
			29	Template 24	1
30	Template 23	1
			31	Template 22	1
32	Template 21	1
			33	Template 20	1
34	Template 19	1
			34	Template 18	1
36	Template 17	1
			37	Template 16	1
38	Template 15	1
			39	Template 14	1
40	Template 13	1
			41	Template 12	1
42	Template 11	1
			43	Template ten	1
44	Template nine	1
			45	Template eight	1
46	Template seven	1
			47	Template six	1
48	Template five	1
			49	Template four	1
50	Template three	1
			51	Template two	1
52	Template one	3

1.3.3 combination

The leading edge radome fairing that will be prepared, requires according to Fig. 1, is inserted on the good wing body of laying, is put into mould.

1.3.4 compacting

Pressing process, is shown in Figure 32.

1.3.5 post-processing

（1）The product that will be suppressed, places in punching tooling, requires, be processed according to Fig. 1；

The effect of 2 this patents

2.1 product size precision

Tail size precision, is shown in Table 8.

8 tail size precision of table

From table 8, it can be seen that：Tail size precision prepared by this patent meets the requirement of 3.1 mesh.

2.2 quality

Empennage prepared by this patent, quality meet the requirement of 3.2 mesh for 0.64~0.66kg.

2.2 flight test test results

Radome fairing prepared by this patent, by the 3 sets of plan model machines prepared in 2015,10 in 2016 sets of first model machines and 2017 5 sets of experimental prototypes, amount to 72, experimental test result shows：

2.2.1 load test

2.2.1.1 static load is tested

Empennage prepared by this patent, applies static load in pressure heart position, considers safety coefficient f=2, be deformed into 10.325mm, and Tail structure is complete, and no destruction, fully meets the requirement of 3.3 mesh.

2.2.1.2 dynamic load is tested

Empennage prepared by this patent, in whole flight course, structural integrity, no destruction, fully meets the requirement of 3.3 mesh.

2.2.2 resistance to ablation test

2.2.2.1 static test

Empennage prepared by this patent, static test.

Test condition is：

a）Air pressure:O₂0.4MPa, C₂H₂0.095MPa；

b）Throughput：O₂1512 L/h, C₂H₂1116 L/h；

c）Heat flow density：4183 kw/m²;

d）Nozzle diameter：2mm；

e）Test temperature：1100℃；

f）Testing time：40s.

Test result, is shown in Table 9.

9 empennage ablation property of table

As can be seen that empennage ablation sample, by 1100 DEG C, after 80s ablations, ablation face top layer is changed into black from hard maroon Color.

From table 9, it can be seen that empennage ablation sample, by 1100 DEG C, after 80s ablations, quality declines, and thickness is slightly Increase and decrease, causing linear ablative rate to have just has negative, mass ablative rate 0.0086g/s.This is because after high temperature ablation, The resin matrix high temperature cabonization loss of ablation face top layer, causes quality to decline, and glass fibre is separated out through high temperature melting, forms height Uneven sealer, causes thickness to increase and decrease.

Empennage prepared by this patent, during whole static test, structural integrity, no destruction, fully meets 3.4 purposes It is required that.

2.2.2.2 dynamic is tested

Empennage prepared by this patent, in whole flight course, structural integrity, no destruction, fully meets the requirement of 3.4 mesh.

Empennage prepared by this patent, by being verified to experimental test result and flight test, shows：Empennage is satisfied by mesh And requirement.

Claims

1. a kind of composite material empennage technology of preparing, it is characterised in that including step:

2）Material selection, using resin base fibrous composite

5）Post-processing,