CN101214429A - Aircraft casing and shaping technique thereof - Google Patents
Aircraft casing and shaping technique thereof Download PDFInfo
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- CN101214429A CN101214429A CNA2007100330336A CN200710033033A CN101214429A CN 101214429 A CN101214429 A CN 101214429A CN A2007100330336 A CNA2007100330336 A CN A2007100330336A CN 200710033033 A CN200710033033 A CN 200710033033A CN 101214429 A CN101214429 A CN 101214429A
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Abstract
The invention discloses an aircraft shell and a process of shaping the aircraft shell, which includes a model aircraft (model airplane, model rocket and model UFO). The aircraft shell is shaped by thermoplastics of a light sheet; the framework of the shell is provided with network ribs and a weight loss window; the cross sections of the ribs are in arch shape. The arch shape width W of the ribs is 1 to 10mm, and the height H is 0.5 to 15mm. The invention first designs a mould based on the shape and the size of the aircraft; the surface of the mould is provided with convex ribs which surround a pit; the light sheet made of PVC, HDPE, PP/BOPP, BOPS, ABS, PET, PC or EVOH is arranged in the mould, and then thermoplastically shaped to process a shell with convex ribs and a pit on the surface; and then the pit of the shell is hollowed, with the convex ribs left, to form a framework with the ribs and the weight loss window. The invention adopts mechanical production, with high productivity, low cost, light weight and high strength. The cross sections of the ribs are in arch shape, which provides firmer structure.
Description
Technical field
The present invention relates to a kind of model aircraft (model of an airplane, model rocket and model flying saucer), aircraft casing and moulding process thereof that particularly a kind of shell adopts light extruded moulding single or multiple lift plastic sheet (plate) to make.
Background technology
The structure of existing model airplane generally makes framework with timber, the outside is with coverings such as heat shrinkage film, complex structure not only, the cost height, the model impact resistance is poor, and needs staff machine-shaping, for batch process brings certain obstacle, need simultaneously to consume a large amount of timber, ecology is caused have a strong impact on.
A kind of shell of fuselage, wing, tailplane, vertical tail that comprises is disclosed among the Chinese patent literature CN2134884 by Unitarily blowing formed model airplane aircraft.Though this structure has replaced making by hand by the making of mechanization, replaces timber with plastics, it is many to consume plastics, and structural strength is low.
A kind of model of an airplane wing, empennage that has reinforcement and for example disclosed in the China Patent No. 03220172.9.This technical scheme is: be incorporated with the long bamboo chip of thin type in the cross section of wing or empennage, make bamboo chip form an integral body with wing firmly, therefore can improve the intensity of wing greatly.It is said that this structure is strengthened the intensity of wing and empennage, and is not fragile, and do not need the former of existing wing, empennage is transformed, can effectively solve the strength problem of wing empennage.But owing to strengthen the intensity of structure by increasing material, thus increase more or less the weight of model, influence its flight quality, also improved cost of manufacture.
Summary of the invention
Purpose of the present invention aim to provide a kind of in light weight, intensity is high, the loss of weight cost is low, be fit to aircraft casing and moulding process thereof that mechanization in enormous quantities is produced, to overcome weak point of the prior art.
A kind of aircraft casing by this purpose design, include model aircraft (model of an airplane, model rocket and model flying saucer), its architectural feature be the housing of aircraft by lightweight sheet material thermoplastic shaping, the skeleton of housing is provided with network-like iliacus and loss of weight window, the iliacus cross section is arch.
The fuselage of described housing, host wing, aileron, tailplane and vertical tail respectively by about or up and down the butt joint of two skeletons form, outer surface covers the heat shrinkage film covering.
That the arch cross section of described iliacus is is inverted U-shaped, inverted V-shaped, trapezoidal, channel steel shape, m shape or waveform, and the arch width W is 1～10mm, and height H is 0.5～15mm; Wherein, host wing is connected with fuselage by intubate, its inner corresponding intubate is provided with Ω shape locating slot, support chip is extended under the iliacus one or both sides in the surface, support chip end and skeleton bottom surface maintain an equal level, highly be 5～50mm, dock to form symmetrical airfoil or asymmetric airfoil up and down naturally by last lower skeleton.Since on the host wing between the lower skeleton span little, process together with support chip man-hour so add at thermoplastic shaping, can make the host wing structure more stable, quality is lighter, and reduces installation steps.Aileron, tailplane and vertical tail structure are also consistent.
Be provided with bracing frame in the described aircraft fuselage, power set are arranged on fuselage or plug-in host wing both sides; Afterbody is provided with groove, and bottom portion of groove is provided with flat hole, and vertical tail end rounding, and being arranged in the groove is hinged by pin-joint piece and fiber major axis and afterbody.Described pin-joint piece one end both sides are provided with projection and snap onto end face both sides, flat hole, and the other end is provided with hinge hole, pass flat hole and insert in the vertical tail, and the fiber major axis passes hinge hole, and is positioned in the vertical tail.This connects according to true aircaft configuration, has reduced the room that is connected that exists between vertical tail and the afterbody, avoids occurring eddy current, makes its flight more stable.Since about fuselage between two skeletons span bigger, adopt the plastic support of thermoplastic shaping to support, insufficient rigidity is so need additionally acquire bracing frame.
A kind of aircraft casing moulding process, earlier go out mould according to aircraft shape size design, die surface is provided with convex tendon, and the position that convex tendon centers on is a pit, the lightweight sheet material is arranged in the mould processes the housing that the surface has convex tendon and pit by thermoplastic shaping; With the pit portion hollow out of housing, be left the convex tendon part then, have the skeleton of iliacus and loss of weight window with formation.
The height of described mould is in 5～300mm scope the time, its pit may extend to the mould bottom surface, and the outer bottom of pit also docks when making the butt joint of two skeletons, again with the pit of two skeletons hollow out simultaneously, the sidewall sections of remaining pit is to form the support chip of support frame.
That the convex tendon cross section of described mould is is inverted U-shaped, inverted V-shaped, trapezoidal, channel steel shape, m shape or waveform.
Edge by arch connection strap and skeleton between described skeleton and the skeleton adopts the mode of hot melt butt joint, bonding, ultrasonic bonding or high-frequency welding to be connected.That the cross section of arch connection strap is is inverted U-shaped, inverted V-shaped, trapezoidal or channel steel shape, pitch of arch H
1Be 2～15mm, arch span degree W
1Be 2～15mm.
Described lightweight sheet material is PVC (polyvinyl chloride), HDPE (high density polyethylene (HDPE)), PP/BOPP (polypropylene), BOPS (polystyrene and expanded polystyrene (EPS) sheet), ABS (acrylonitrile, butadiene and cinnamic terpolymer), PET (polyester), APET sheet (M-phthalic acid and diethylene glycol (DEG) are to the polyester modification), CPET sheet (crystallinity PET), GPET/PETG sheet (with cyclohexanedimethanol to the polyester modification), PET co-extrusion slice, PC (Merlon), lucite sheet (poly-methyl-prop is known sour methyl esters) or EVOH (comprise the MULTILAYER COMPOSITE extrudate piece, its main stor(e)y is a polyolefin, nylon, barrier layer is EVOH and polyesteramine 6, adhesive layer is a polyolefin resin) plastic sheet, its thickness is 0.1～2mm.
Skeleton of the present invention passes through thermoplastic shaping, by mechanization production, and the production efficiency height, cost is low, light weight, the intensity height, weight is 60%～90% of timber system shell, and reduces consumption of wood, more environmental protection.The iliacus cross section is arch, and structure is more firm.
Description of drawings
Fig. 1 is one embodiment of the invention structural representation.
Fig. 2 is afterbody and vertical tail catenation principle structural representation.
Fig. 3 is a host wing skeleton structure schematic diagram.
Fig. 4 is an A-A sectional structure schematic diagram among Fig. 3.
Fig. 5 analyses and observe and local structure for amplifying schematic diagram for B-B among Fig. 3.
Fig. 6-Figure 11 is the multiple embodiments structural representation in skeleton of the present invention cross section.
Figure 12 is a mould structure schematic diagram of the present invention.
Figure 13 is the structural representation that two skeletons connect by the arch connection strap.
The specific embodiment
Below in conjunction with drawings and Examples the present invention is further described.
Referring to Fig. 1-Fig. 5, this aircraft casing, the airframe 1 that includes aircraft and made by the lightweight sheet material, skeleton are provided with iliacus 1.2 and loss of weight window 1.1, and the iliacus cross section is arch.The arch cross section of iliacus is trapezoidal, sees Fig. 6, and the arch width W is 1～10mm, and height H is 0.5～10mm.Aircraft is provided with bracing frame 6 for to be made of fuselage 4, host wing 5, aileron 5.1, tailplane 3 and vertical tail 2 in the fuselage, power set are arranged on fuselage or plug-in host wing both sides.Host wing 5 is connected with fuselage 4 by intubate, its inner corresponding intubate is provided with Ω shape locating slot 1.4, support chip 1.3 is extended under iliacus 1.2 one or both sides in the surface, support chip end and skeleton bottom surface maintain an equal level, highly be 5～50mm, dock to form symmetrical airfoil or asymmetric airfoil up and down naturally by last lower skeleton.Fuselage 4 afterbodys are provided with groove 4.1, and bottom portion of groove is provided with flat hole 4.2, vertical tail 2 end roundings, and be arranged in the groove, hinged by pin-joint piece 9 and fiber major axis 8 with afterbody.Pin-joint piece 9 one end both sides are provided with projection 9.2 and snap onto 4.2 end face both sides, flat hole, and the other end is provided with hinge hole 9.1, pass flat hole and insert in the vertical tail, and fiber major axis 8 passes hinge hole, and is positioned in the vertical tail.That the arch cross section of iliacus 1.1 is is trapezoidal, inverted U-shaped, channel steel shape, inverted V-shaped, m shape or waveform, sees Fig. 7-Figure 11 successively.Power set are not shown.
Aircraft casing moulding process: go out mould 10 according to aircraft shape size design earlier, die surface is provided with convex tendon 10.2, the position that convex tendon centers on is a pit 10.1, sees Figure 12, the lightweight sheet material is arranged in the mould processes the housing that the surface has convex tendon and pit by thermoplastic shaping; With the pit portion hollow out of housing, be left the convex tendon part then, have the skeleton 1 of iliacus and loss of weight window with formation.Edge by arch connection strap 11 and skeleton between skeleton 1 and the skeleton adopts the mode of hot melt butt joint to be connected, and sees Figure 13, and last, outer surface covers the heat shrinkage film covering.When the height of mould was in 5～300mm scope, its pit may extend to the mould bottom surface, and the outer bottom of pit also docks when making two skeletons butt joints, and with the pit of two skeletons hollow out simultaneously, the sidewall sections of remaining pit is to form the support chip of support frame again.
That convex tendon 10.2 cross sections of above-mentioned mould 10 are is inverted U-shaped, inverted V-shaped, trapezoidal, channel steel shape, m shape or waveform.That the cross section of arch connection strap is is inverted U-shaped, inverted V-shaped, trapezoidal or channel steel shape, pitch of arch H
1Be 2～15mm, arch span degree W
1Be 2～15mm.Above-mentioned lightweight sheet material is PVC (polyvinyl chloride), HDPE (high density polyethylene (HDPE)), PP/BOPP (polypropylene), BOPS (polystyrene and expanded polystyrene (EPS) sheet), ABS (acrylonitrile, butadiene and cinnamic terpolymer), PET (polyester), APET sheet (M-phthalic acid and diethylene glycol (DEG) are to the polyester modification), CPET sheet (crystallinity PET), GPET/PETG sheet (with cyclohexanedimethanol to the polyester modification), PET co-extrusion slice, PC (Merlon), lucite sheet (poly-methyl-prop is known sour methyl esters) or EVOH (comprise the MULTILAYER COMPOSITE extrudate piece, its main stor(e)y is a polyolefin, nylon, barrier layer is EVOH and polyesteramine 6, adhesive layer is a polyolefin resin) plastic sheet, its thickness is 0.1～2mm.
Claims (10)
1. an aircraft casing includes the model aircraft, and the housing that it is characterized in that aircraft is by lightweight sheet material thermoplastic shaping, and the skeleton of housing (1) is provided with network-like iliacus (1.2) and loss of weight window (1.1), and the iliacus cross section is arch.
2. according to the described aircraft casing of claim 1, fuselage (4), host wing (5), aileron (5.1), tailplane (3) and the vertical tail (2) that it is characterized in that described housing respectively by about or up and down two skeletons butt joints form, outer surface covers the heat shrinkage film covering.
3. according to claim 1 or 2 described aircraft casings, that the arch cross section that it is characterized in that described iliacus is is inverted U-shaped, inverted V-shaped, trapezoidal, channel steel shape, m shape or waveform, and the arch width W is 1～10mm, and height H is 0.5～15mm; Wherein, host wing is connected with fuselage by intubate, its inner corresponding intubate is provided with Ω shape locating slot (1.4), support chip (1.3) is extended under the iliacus one or both sides in the surface, support chip end and skeleton bottom surface maintain an equal level, highly be 5～50mm, dock to form symmetrical airfoil or asymmetric airfoil up and down naturally by last lower skeleton.
4. according to the described aircraft casing of claim 3, it is characterized in that being provided with in the described fuselage bracing frame (6), power set are arranged on fuselage or plug-in host wing both sides; Afterbody is provided with groove (4.1), and bottom portion of groove is provided with flat hole (4.2), vertical tail end rounding, and be arranged in the groove, hinged by pin-joint piece (9) and fiber major axis (8) with afterbody; Pin-joint piece one end both sides are provided with projection (9.2) and snap onto end face both sides, flat hole, and the other end is provided with hinge hole (9.1), pass flat hole and insert in the vertical tail, and the fiber major axis passes hinge hole, and is positioned in the vertical tail.
5. aircraft casing moulding process, it is characterized in that going out mould (10) according to aircraft shape size design earlier, die surface is provided with convex tendon (10.2), the position that convex tendon centers on is pit (10.1), the lightweight sheet material is arranged in the mould processes the housing that the surface has convex tendon and pit by thermoplastic shaping; With the pit portion hollow out of housing, be left the convex tendon part then, have the skeleton of iliacus and loss of weight window with formation.
6. according to the described aircraft casing moulding process of claim 5, the height that it is characterized in that mould is in 5～300mm scope the time, its pit may extend to the mould bottom surface, the outer bottom of pit also docks when making two skeleton butt joints, again with the pit of two skeletons hollow out simultaneously, the sidewall sections of remaining pit is to form the support chip of support frame.
7. according to the described aircraft casing moulding process of claim 6, that the convex tendon cross section that it is characterized in that described mould is is inverted U-shaped, inverted V-shaped, trapezoidal, channel steel shape, m shape or waveform.
8. according to the described aircraft casing moulding process of claim 7, it is characterized in that between described skeleton and the skeleton that edge by arch connection strap (11) and skeleton adopts the mode of hot melt butt joint, bonding, ultrasonic bonding or high-frequency welding to be connected.
9. that described according to Claim 8 aircraft casing moulding process, the cross section that it is characterized in that described arch connection strap are is inverted U-shaped, inverted V-shaped, trapezoidal or channel steel shape, pitch of arch H
1Be 2～15mm, arch span degree W
1Be 2～15mm.
10. according to the described aircraft casing moulding process of claim 9, it is characterized in that described lightweight sheet material is PVC, HDPE, PP/BOPP, BOPS, ABS, PET, APET sheet, CPET sheet, GPET/PETG sheet, PET co-extrusion slice, PC, lucite sheet or EVOH plastic sheet, its thickness is 0.1～2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2007100330336A CN101214429B (en) | 2007-12-28 | 2007-12-28 | Aircraft casing and shaping technique thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2007100330336A CN101214429B (en) | 2007-12-28 | 2007-12-28 | Aircraft casing and shaping technique thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101214429A true CN101214429A (en) | 2008-07-09 |
| CN101214429B CN101214429B (en) | 2010-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2007100330336A Expired - Fee Related CN101214429B (en) | 2007-12-28 | 2007-12-28 | Aircraft casing and shaping technique thereof |
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| Country | Link |
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| CN (1) | CN101214429B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126549A (en) * | 2010-01-20 | 2011-07-20 | 苏章仁 | Clockwise-course asymmetric simulation structure of flight carrier shell with circular cross section |
| CN103635385A (en) * | 2011-07-01 | 2014-03-12 | 空中客车西班牙运营有限责任公司 | Reinforced aircraft fuselage |
| CN105966596A (en) * | 2016-06-13 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Thickness-variable thin-wall skin structure |
| RU227262U1 (en) * | 2024-04-10 | 2024-07-12 | Станислав Викторович Каштанов | Airframe model wing |
-
2007
- 2007-12-28 CN CN2007100330336A patent/CN101214429B/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126549A (en) * | 2010-01-20 | 2011-07-20 | 苏章仁 | Clockwise-course asymmetric simulation structure of flight carrier shell with circular cross section |
| CN103635385A (en) * | 2011-07-01 | 2014-03-12 | 空中客车西班牙运营有限责任公司 | Reinforced aircraft fuselage |
| CN103635385B (en) * | 2011-07-01 | 2016-04-06 | 空中客车西班牙运营有限责任公司 | Strengthen aircraft fuselage |
| CN105966596A (en) * | 2016-06-13 | 2016-09-28 | 江西洪都航空工业集团有限责任公司 | Thickness-variable thin-wall skin structure |
| RU227262U1 (en) * | 2024-04-10 | 2024-07-12 | Станислав Викторович Каштанов | Airframe model wing |
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| Publication number | Publication date |
|---|---|
| CN101214429B (en) | 2010-10-20 |
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Granted publication date: 20101020 Termination date: 20111228 |