CN100385194C - Composite material made box body structure for storage and conveying launch box - Google Patents
Composite material made box body structure for storage and conveying launch box Download PDFInfo
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- CN100385194C CN100385194C CNB021550107A CN02155010A CN100385194C CN 100385194 C CN100385194 C CN 100385194C CN B021550107 A CNB021550107 A CN B021550107A CN 02155010 A CN02155010 A CN 02155010A CN 100385194 C CN100385194 C CN 100385194C
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Abstract
The present invention relates to a box body structure made of composite materials for storing and transporting emitting boxes, which adopts a shallow arch single-shell plate structure which is provided with longitudinal reinforcing members and transversal reinforcing ribs, and a corresponding symmetrical layer-spread form. Base plates on four surfaces of the box body structure are formed by smoothly connecting shallow arch shell plates having small arch degrees at four sides and circular cylindrical shell plates at four corners; the transverse reinforcing ribs are arranged along the length direction of the base plates on the four surfaces of the box body with equal intervals; guide track seats, rudder tracks and thickening layers of the base plates being opposite to the guide track seat, which are integrally connected with the box body structure, act as the longitudinal reinforcing members; both ends of the box body adopt flanges made of whole composite materials, which are in a flanging form and are integrally connected with the base plates of the box body. The box body structure of the present invention has very high specific strength and specific rigidity and good air tightness and can bear long-distance transportation vibration, external force impact and internal pressure impact during the thermal emission of missiles so as to ensure the safety, the reliability and the emitting accuracy of the missiles in the box body.
Description
Technical field
The present invention relates to a kind of launch canister composite body structure of guided missile, is the main load-carrying construction of launch canister, is used for support fixation, transportation, airtight stored dry and vertical thermal and launches a guided missile.
Background technology
The high-performance of advanced carrier rocket and guided missile, high reliability and low-cost application and the corresponding structure optimal design that depends on new material to a great extent, it can reduce architecture quality, increase payload and range, the reduction launch cost of carrier rocket and guided missile effectively.General MISSILE LAUNCHING box function only is not possess the function of storage, transport missile simultaneously as launching a guided missile, and such body structure is a cylinder type.The U.S. is in the MX missile of later stage eighties typing, and segment structure all adopted carbon/epoxy composite material manufacturing after sub warhead discharged the cabin cylinder-like shell and reenters submissile head capsule body, and it is light by 40% that the comparable corresponding metal structure of its quality is wanted.United States Patent (USP) " guided missile tube and the manufacture method " (patent No.: 5,115,711) described 4 conjuncted guided missile accumulatings and launched cylindrical shell with composite square structure of aluminium honeycomb interlayer; Japan Patent " the launch canister " (patent No.: 5-149696) described and have fiber strengthened plastic inner lining, honeycomb interlayer and the outer guided missile accumulating emission cylindrical shell that twines the square structure of carbon fiber surface; Shipborne weapon " " extra large lance " guided missile vehicle views " (1998 the 3rd phases; pp15-27) described the columnar structured submarine-based missile vehicle of a kind of laminar composite, the structural wood bed of material of this guided missile vehicle is made up of flat-shaped phenolic aldehyde honeycomb interlayer, coated Kevlar fabric protective layer and the extexine that twines of graphite fibre and epoxy resin on this honeycomb.These design features mainly are the laminar composite structures at the honeycomb interlayer, and such laminate structures only helps improving the integrally bending rigidity of structure, but can not bear guided missile caused higher internal pressure during heat emission in casing.In addition, the shape of cross section of described guided missile accumulating emission cylindrical shell is simple square or circular; Internal structure is simple, no track base and rudder rail chair; Cylindrical shell is not a disposal integral molding, is difficult to guarantee higher assembly precision.Therefore, the guided missile accumulating of above patented invention and document description emission cylindrical shell is not suitable for as quick vertical thermal launches a guided missile, and has supports concurrently, fixes, the launch canister body of airtight stored dry and transport missile function.
Launch a guided missile for can be used to quick vertical thermal, have the launch canister of support, fixing, airtight stored dry and transport missile function concurrently, because body structure has support concurrently, fixes and store the function of guided missile, the cross section of body structure is general to be required to square.But the square box structure does not possess the good ability of pressing in the MISSILE LAUNCHING of bearing, and must the line style to the box plate shell carry out special consideration in design.
Launch canister is bearing under remote transportation vibration, external impacts, level and the load effects such as vertical lifting, require body structure indeformable, air tight, do not lose efficacy, guaranteed guided missile safe and reliable and precision of launching in casing, thereby requiring the composite body structure to have symmetry, harmony and very high overall glacing flatness preferably, this need determine in the design of composite body structure.
The composite body structure has the function of airtight stored dry guided missile, and the two ends of casing must be furnished with flange connector and be carried out being tightly connected of end.Flange connector on the general composite structure all is a metal flange.Metal flange can or carry out suit with composite structure and mix reinforcement by connection with the moulding of composite structure co-curing.But the thermal coefficient of expansion of the thermal coefficient of expansion of metal flange and composite does not match, no matter how metal flange is connected with composite structure under the environment of variations in temperature, the crack all will appear in the junction of metal flange and composite structure, very difficult guard box body structure has good air-tightness.This is to need the difficult point that solves in the composite body structure design.
Summary of the invention
The objective of the invention is at the deficiencies in the prior art, a kind of launch canister composite body structure of newer versions of these missiles is provided, make it to have light as far as possible weight, and the interior pressure can bear remote transportation vibration, external impacts and guided missile heat emission the time is impacted, guarantee the safe and reliable and launch accuracy under accumulating, lifting and the carrier-borne state of guided missile in casing, satisfy the functional requirement that launch canister should have.
For realizing such purpose, the functional requirement that the present invention should have according to the launch canister body structure, utilize the designability of composite, body structure geometry and layering type are optimized design.It is that to be that cylindrical coverboard is smooth link for the shallow arched roof plate of little camber and four jiaos that the four sides substrate of body structure adopts four limits.Casing adopts the shallow arch monoshell plank frame that has vertical stiffener and laterally strengthen rib, both on the casing substrate, adopted and laterally strengthened rib and equidistantly distribute along the length direction of casing, utilize the vertical stiffener of the thickening layer of the track base, rudder rail and the track base opposing substrate that are connected as a single entity with body structure as casing, make the distribution of material (comprising bending resistance the moment of inertia, layering type) of the entire profile of composite casing all satisfy the layer design of symmetry shop, to keep harmonious preferably and higher overall glacing flatness.Adopt the flange design of the full composite material flange form that is connected as a single entity with composite casing board structure, the casing substrate with casing end thickening layer continuously at the end flange, and, form the end flange flange of the full composite material flange form that is connected as a single entity with composite box plate shell structure in flange intersection chamfered transition.
The present invention determines being restricted to of system coordination size and shape according to the concrete function of launch canister:
(1) cross section of casing is square
(2) the cabinets cavity minimum dimension is b
1* b
1
(3) casing contour dimension is b to the maximum
2* b
2
(4) track base is wide and high given
(5) shape of upper end cover and size are definite.
According to Plate Theory, be cylindrical shell to pressing the structure optimum structure form of cutting the lotus effect in being subjected to, worst is the square plate casing.Thus, the present invention has carried out optimal design to the casing linearity.Under aforementioned casing cross section was square qualifications, casing of the present invention four sides substrate was designed to be made up of the shallow arched roof plate and the cylindrical coverboard of smooth connection.According to the restriction of cooperative dimensioning, get sagitta on four limits of casing and be
Shallow arched roof plate, getting radius four jiaos of casings is R=R
OThe cylinder coverboard; Utilize a specific transcendental curve equation to make the shallow arched roof plate of little camber and four jiaos of smooth knot casing four sides substrates that connect into of cylindrical coverboard.
Composite casing of the present invention adopts the shallow arch monoshell plank frame that has vertical stiffener and laterally strengthen rib, and adopts the layer design of corresponding shop.
Casing four sides substrate be the composite casing basic building block, be to be the shallow arched roof plate of f and to get radius by four jiaos of casings be R=R by casing four limit sagitta
OSmooth the connecting to form of cylindrical coverboard, to satisfy horizontal local strength, consider enough vertical rigidity requirements simultaneously.
Adopt the shallow arch monoshell of skeleton plate box structure in length and breadth, both configuration laterally strengthened rib and equidistantly distributed along the length direction of casing on the casing substrate, utilized the vertical stiffener of the thickening layer of the track base, rudder rail and the track base opposing substrate that are connected as a single entity with body structure as casing.
Tank ends portion adopts the full composite material flange form flange that is connected as a single entity with the casing substrate, the casing end and first substrate that laterally strengthens in the frame spacing are substrate end thickening layer, and substrate end thickening layer forms full composite material flange form flange at casing end flange.The intersection of flange flange and substrate end thickening layer has the chamfered transition layer.For technology is easier, second grade of rib distance is the casing substrate later on; And in the width of distance end l, 2 horizontal enhancing ribs, the chamfered transition layer is arranged.
The shop layer design of casing substrate considered enough vertical rigidity requirements simultaneously to satisfy horizontal local strength, and it always spreads the number of plies is the n layer.
The shop layer design of the substrate thickening layer of track base opposite coverboard takes into account shearing resistance and shock resistance to satisfy longitudinal rigidity, and it always spreads the number of plies is n1.
According to characteristic and technological requirement that horizontal enhancing rib only bears transverse curvature and self axial tension, frame spacing is L
1(mm), the m root is set, is circumferentially closed, all get [90 °] n along total length.
The shop layer design of track base must have enough shearing resistances and local crush resistance strength performance based on longitudinal rigidity.Its total shop number of plies is n2;
Wear-resisting and crushing strength is considered on the top layer of rudder rail, and the intermediate layer is based on longitudinal rigidity.
The present invention has carried out optimal design to the linearity of body structure four sides substrate under the qualifications of aforementioned given casing cross section physical dimension.Body structure four sides substrate is designed to connect to form, provided corresponding shop layer and design by shallow arched roof plate and cylinder coverboard are smooth, makes the four sides substrate of body structure have enough horizontal local stiffness and intensity under the instantaneous impact air pressure effect of MISSILE LAUNCHING and satisfy vertical rigidity requirement bearing.
Body structure of the present invention adopts the shallow arch monoshell plank frame that has vertical stiffener and laterally strengthen rib, parts for the difference in functionality of body structure carry out different shop layer designs, thereby make the distribution of material of the entire profile of composite casing (comprise the bending resistance the moment of inertia, layering type) all has symmetry, harmonious preferably and very high overall glacing flatness, guaranteed that launch canister is bearing remote transportation vibration, external impacts, load effect lower box structures such as level and vertical lifting are indeformable, to guarantee the precision of the safe and reliable and emission of guided missile in casing.
The flange of the design employing of tank ends of the present invention portion flange and the whole full composite material flange of casing coverboard form, substituted employed metal flange on the general composite structure, solved air-tightness problem, guaranteed that the launch canister body structure has the function of airtight stored dry guided missile in the environment lower box structure of variations in temperature.
The launch canister composite body structure of the present invention's design can carry out integral body shop layer or Wrapping formed by certain technology mode at an easy rate, have very high specific strength and specific stiffness, air-tightness is good, can repeatedly launch repeated use, the overall good straightness degree of body structure can guarantee the launch accuracy of guided missile, adapt to remote transportation, anti-vibration, shock resistance and fatigue behaviour are good, the production efficiency height, cost is low, its quality is than the light weight 50% of the stainless steel metal body structure with said function, greatly improve the carrier-borne resilience energy power of army, the vertical thermal emission function has guaranteed the quick operation respond to sky.
Description of drawings
Fig. 1 is the line illustration of composite body structure of the present invention.
Among Fig. 1, the four sides substrate of body structure is formed in 1 expression, the horizontal enhancing rib of 2 expression composite casings, the flange of the full composite material flange form that 3 expressions and casing substrate are in aggregates, the chamfered transition layer of 4 expression full composite material flange form flange flange intersections, L
0The length of expression casing.
Fig. 2 be among Fig. 1 A-A, B-B to view.
Fig. 2 has provided the inner chamber line style and the full composite material flange line style schematic diagram of composite tank ends cross section.Among the figure, the shallow arched roof plate on 5 expression casings, four limits, the cylindrical coverboard that 6 expression casings are four jiaos, shallow arched roof plate 5 and the cylindrical coverboard 6 smooth casing four sides substrates 1 that connect to form, 7 are support fixation and the track base of launching a guided missile, the 8 rudder rails for constraint guided missile missile wing, 9 is the substrate thickening layer of track base opposite coverboard, the flange of the full composite material flange form that 3 expressions and casing substrate are in aggregates.
Fig. 3 is the shop layer schematic diagram of composite body structure end flange, end upsetting layer, chamfered transition layer and casing substrate.
Among Fig. 3, the thickening layer of 10 expression flange flanges, 11 is casing substrate end thickening layer, 12 is the transition zone of casing substrate end thickening layer 11 to substrate 1.
Fig. 4 is the limited element calculation model of composite body partial structure of the present invention.
Fig. 5 is the integrally-built limited element calculation model of composite casing of the present invention.
The specific embodiment
Below in conjunction with drawings and Examples technical scheme of the present invention is further described.
Composite body structure of the present invention as shown in Figure 1, surround casing by casing four sides substrate 1, length direction along casing four sides substrate 1 equidistantly disposes horizontal enhancing rib 2, the two ends of casing four sides substrate 1 be the full composite material flange flange 3 in aggregates with casing substrate end thickening layer 11, and full composite material flange flange 3 is to an enhancing transition zone 4 is arranged between the casing substrate end thickening layer 11.
Casing substrate 1 of the present invention is that to get radius for four jiaos be R=R for the shallow arched roof plate 5 of f and casing by four limit sagitta of casing
OCylindrical coverboard 6 smooth connecting to form, as shown in Figure 2, one side of four sides substrate 1 has the track base 7 that is connected as a single entity with body structure, has support fixation and the function of launching a guided missile, track base 7 opposing substrates are furnished with substrate thickening layer 9, and the distribution of material (comprising bending resistance the moment of inertia, layering type) that plays the entire profile that makes the composite casing all has symmetry, harmonious and very high overall glacing flatness specific function preferably.There is the rudder rail 8 that is connected as a single entity with body structure track base 7 adjacent both sides, have constraint guided missile missile wing function.Substrate end thickening layer 11 fuses with flange flange 3.
For increasing the intensity of the variant connecting portion of casing, the present invention is provided with between substrate end thickening layer 11 and flange flange 3 and strengthens transition zone 4, as shown in Figure 3, flange flange 3 links to each other with the end upsetting layer 11 of casing substrate 1, flange thickening layer 10 strengthens transition zone 4 with the substrate end and links to each other, and between substrate 1 and the substrate end thickening layer 11 transition zone 12 is arranged.
According to the restriction and the technological feasibility of instructions for use, cooperative dimensioning, body structure of the present invention adopts track base 7 and opposing substrate thickening layer 9 thereof as vertically stiffener, employing laterally strengthen the shallow arch monoshell plank frame of rib 2 as the partial lateral strength-reinforcing member.
The shop layer design of box component:
Casing substrate 1 is considered enough vertical rigidity requirements simultaneously to satisfy horizontal local strength.Total shop number of plies n=38, the shop layer compares n
90: n
0: n
45=10: 5: 4.
Track base opposite coverboard substrate thickening layer 9 is taken into account shearing resistance and shock resistance and is always spread number of plies n=24 based on longitudinal rigidity, and the shop layer compares n
0: n
45=4: 2
According to characteristic and technological requirement that horizontal enhancing rib 2 only bears transverse curvature and self axial tension, frame spacing is got L
1(mm), along total length m=L is set
0/ L
1(root) is circumferentially closed, all gets [90 °] n.Track base 7 must have enough shearing resistances and local crush resistance strength performance based on longitudinal rigidity.Total shop number of plies n=56; The number of plies compares n
0: n
45: n
90=4: 2: 1
Wear-resisting and crushing strength is considered on the top layer of rudder rail 8, and is middle based on longitudinal rigidity.
In an embodiment of the present invention, the four sides substrate of composite casing linearity is by cylindrical coverboard and shallow arched roof plate is smooth connects to form, and getting radius four jiaos of casings is R
OThe cylindrical coverboard of=72mm; Get the shallow arched roof plate that sagitta is f=5mm on four limits of casing.
The tangent circular arch radius R of four limits and foursquare arc is determined by following formula:
The central angle at two circular arc point of contacts is determined by following equation
This casing is got R
O=72, f=5, B=b
1-2f
Can determine by formula (1) and (2): R=R
1(mm),
The concrete layering type of composite casing substrate skeleton:
(1) casing substrate 1 layering type: [45/45/90
2/ 0/90
2/ 0/90/-45/45/90/0/90
2/ 0/90/0/90]
s
(2) track base opposing substrate thickening layer 9 layering types: [45/0
2/ 45/0
2]
2, s
(3) laterally strengthen rib 2 layering types: [90 °]
136
(4) track base 7 layering types: [45/0/-45/0
2/ 90/0]
4, s
(5) rudder rail 8 layering types [(45/0/45/0/90
2)
3/ 0
n].
Full composite material flange formula flange:
(1) the end upsetting layer 11 of casing substrate 1 is formed flange formula flange 3 at the end flange, and the layering type of the thickening layer 10 of its flange 3 is: [45/45/0
2/ 90/0
2/ 90/-45/45/0
2/ 90/0
2/ 90/0
2]
s
(2) 3 to first horizontal enhancing ribs of flange formula flange place is 8/20 inclined-plane layer 4 transition with tapering; At second grade of rib apart from transitting to casing substrate 1 gently with inclined-plane layer 12.
According to composite body structure designing requirement; Get the structural material of T700/ epoxy resin as casing, casing substrate and track base all use prepreg overlay (or winding) technology and one to solidify, the rib winding process, and with the moulding of substrate one co-curing, (sun) mould is that an overall structure makes its molding performance good in the casing, incites somebody to action the outer surface that outer (the moon) mould entirely leans against body structure, and goods are placed in the vacuum still, pressurization, heating cure, one-body molded.
According to the part of composite casing and whole limited element calculation model as shown in Figure 4 and Figure 5, the composite body structure that can draw above design from its numerical simulation has best bearing capacity, and can obtain all functions that launch canister should have, and the weight of composite casing is than in light weight 50% of metal cabinet.
Claims (1)
1. the launch canister composite body structure of a guided missile, it is characterized in that surrounding casing by casing four sides substrate (1), length direction along casing four sides substrate (1) equidistantly disposes horizontal enhancing rib (2), the two ends of casing four sides substrate (1) are the full composite material flange flange (3) in aggregates with casing substrate (1), casing substrate (1) is by the shallow arched roof plate (5) on four limits and four jiaos smooth being formed by connecting of cylindrical coverboard (6), one side of four sides substrate (1) has track base (7), track base (7) opposing substrate is furnished with substrate thickening layer (9), the adjacent both sides of track base (7) are furnished with rudder rail (8), flange flange (3) links to each other with the end upsetting layer (11) of four sides substrate (1), flange thickening layer (10) strengthens transition inclined-plane layer (4) with the substrate end and links to each other, and between substrate (1) and the substrate end thickening layer (11) transition inclined-plane layer (12) is arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021550107A CN100385194C (en) | 2002-12-19 | 2002-12-19 | Composite material made box body structure for storage and conveying launch box |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021550107A CN100385194C (en) | 2002-12-19 | 2002-12-19 | Composite material made box body structure for storage and conveying launch box |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1419101A CN1419101A (en) | 2003-05-21 |
| CN100385194C true CN100385194C (en) | 2008-04-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021550107A Expired - Fee Related CN100385194C (en) | 2002-12-19 | 2002-12-19 | Composite material made box body structure for storage and conveying launch box |
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| CN (1) | CN100385194C (en) |
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| CN1844839B (en) * | 2006-04-30 | 2010-05-12 | 南京航空航天大学 | Integral impacting type composite canister cover |
| CN104075622B (en) * | 2014-06-19 | 2017-01-25 | 北京航天发射技术研究所 | Launch barrel device with inner surface resisting gas flushing |
| CN105151350B (en) * | 2015-09-02 | 2017-09-12 | 北京航天发射技术研究所 | It is a kind of to be used for while the boxing apparatus for the transmitting that leaves the right or normal track |
| CN105501601B (en) * | 2015-12-17 | 2017-09-22 | 深圳市欧亚瑞碳纤维科技有限公司 | A kind of Composite Box and preparation method thereof |
| CN110057244A (en) * | 2019-04-26 | 2019-07-26 | 湖北航天技术研究院总体设计所 | A kind of storing firing box and preparation method thereof |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
| CN111604644B (en) * | 2020-05-09 | 2021-07-06 | 湖北三江航天万峰科技发展有限公司 | Forming method for ensuring high air tightness of aluminum alloy launching box |
| CN112781443B (en) * | 2021-01-04 | 2022-08-19 | 宁波曙翔新材料股份有限公司 | Stealth, ablation and bearing integrated light launching box and preparation method thereof |
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| US5115711A (en) * | 1991-03-25 | 1992-05-26 | Fmc Corporation | Missile canister and method of fabrication |
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-
2002
- 2002-12-19 CN CNB021550107A patent/CN100385194C/en not_active Expired - Fee Related
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|---|---|---|---|---|
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| RU2112648C1 (en) * | 1996-02-29 | 1998-06-10 | Акционерное общество Центральный научно-исследовательский институт специального машиностроения | Method of production of tube of laminated composite material with helical right-angled groove and tube of laminated composite material with helical right-angled groove |
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| JP2001091193A (en) * | 1999-09-17 | 2001-04-06 | Mitsubishi Heavy Ind Ltd | Flying object launching apparatus and canister of flying object |
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| CN1419101A (en) | 2003-05-21 |
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