CN102139757A - Framed front center fuselage suitable for unmanned plane and model plane - Google Patents
Framed front center fuselage suitable for unmanned plane and model plane Download PDFInfo
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- CN102139757A CN102139757A CN2010102390070A CN201010239007A CN102139757A CN 102139757 A CN102139757 A CN 102139757A CN 2010102390070 A CN2010102390070 A CN 2010102390070A CN 201010239007 A CN201010239007 A CN 201010239007A CN 102139757 A CN102139757 A CN 102139757A
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Abstract
The invention provides a framed front center fuselage suitable for an unmanned plane and a model plane, which comprises a plurality of bulkheads and a plurality of carbon fiber beams, wherein the plurality of bulkheads form and keep the outline of the front center fuselage; and the plurality of carbon fiber beams are arranged longitudinally along the outline of the front center fuselage and connect the bulkheads together to form a main structure of the front center fuselage. The front center fuselage has the advantages that: 1) a framed mode is adopted in the structure, the common bulkheads and the reinforcing bulkheads are spaced, the common bulkheads are conical, the reinforcing bulkheads are used for connecting wings, an undercarriage, a rear body, a front body and the like, and the common bulkheads and the reinforcing bulkheads play a role in supporting skin, trussed beams and purline; 2) the layered design of the internal space can meet the requirements of loading and throwing, the upper layer and the lower layer are used for arranging an oil tank and pipelines and the like, and the middle is used for placing goods to be thrown and airborne equipment, so the utilization rate of the space is high; 3) the reinforcing bulkheads are reasonably arranged on the middle part of the fuselage, and installation of the wings and the undercarriage is implemented through connecting lugs; and 4) the front fuselage and the middle fuselage are connected through a hinge, so the fuselage can be opened and is convenient for overhauling and loading and unloading the goods.
Description
Technical field
The present invention relates to a kind of design that is applicable to the preceding middle machine body of framework type of the unmanned plane and the large scale model of an airplane, belong to aviation aircraft component design field.
Background technology
Fuselage is the matrix that each structure member of aircraft, each function system are installed.Fuselage is installed the basis except providing for other parts (for example wing, empennage and alighting gear etc.), and provide outside the installing space for airborne equipment, also to bear the load that these parts transmit, need satisfy mechanics requirements such as intensity, rigidity, and require to accomplish that architecture quality is the lightest, to improve structure efficiency.
The modern unmanned plane and the large scale model of an airplane have higher designing requirement for fuselage, often require the big and lightweight construction in inner space.Adopting the framework type fuselage of high structure efficiency on this class aircraft is a kind of better solution.
Summary of the invention
According to an aspect of the present invention, provide a kind of preceding middle machine body of framework type that is applicable to the unmanned plane and the model of an airplane, it is characterized in that comprising:
A plurality of bulkheads, they constitute and keep the appearance profile of described preceding middle machine body,
The many carbon fiber beams that the described appearance profile of middle machine body is vertically arranged before described, be used for each described bulkhead couple together form described before the keystone configuration of middle machine body.
Description of drawings
Fig. 1 has shown the position of middle machine body according to an embodiment of the invention in aircaft configuration.
Fig. 2 has shown the structure composition of middle machine body according to an embodiment of the invention.
Fig. 3 has shown the spatial division generalized section of middle machine body embodiment illustrated in fig. 2.
Fig. 4 has shown middle machine body fuel tank layout scheme drawing according to an embodiment of the invention.
Fig. 5 has shown middle machine body according to an embodiment of the invention and wing attachment lug scheme drawing.
Fig. 6 has shown middle machine body according to an embodiment of the invention and main landing gear attachment lug scheme drawing.
Fig. 7 has shown middle machine body according to an embodiment of the invention and preceding head connection diagram.
Fig. 8 has shown middle machine body according to an embodiment of the invention and rear body connection diagram.
The specific embodiment
The inventor contracts than the designing requirement of this class unmanned plane of proof machine and the needed big inner space of large scale model fuselage at large transport airplane and passenger plane, has proposed a kind of framework type middle machine body design plan.This design plan by top ceiling and floor are installed, is divided into upper, middle and lower three layer with the middle machine body inner space for utilizing the fuselage interior space effectively and rationally.Conformal Fuel Tanks is arranged in the upper and lower.The anterior lower floor of middle machine body arranges nose-gear installation basis and noselanding gear well.Middle machine body upper strata, middle part and central wing box constitute the integrally closed structure.Middle machine body middle part lower floor connects main landing gear by the switching auricle.The middle machine body rear portion is connected with rear body by the end face docking mode.
Contracting than this class unmanned plane of proof machine and the large scale model of an airplane of large transport airplane and passenger plane has higher requirement for the inner space of fuselage and architecture quality and carrying usefulness.Adopting which kind of technical scheme is key issue in the design of this class airframe.The present invention passes through the form to the framework type fuselage, the appropriate design that structure and space and function are distributed; Realize the design of the middle machine body of high-mechanic usefulness, big inner space.
The concrete technical scheme of implementing of the present invention below is described.
1) form of framework type middle machine body and structure.
According to the overall aircraft contour structures of an embodiment of the present invention as shown in Figure 1, middle machine body is positioned at the middle part and the front portion of airframe, is connected wing, rear body, head and alighting gear as a whole.Position shown in Fig. 1 (10) is the scheme drawing of middle machine body in the residing position of aircraft.
The structure of central fuselage is formed as shown in Figure 2, mainly contain several bulkheads (1) and constitute appearance profile, vertically arrange many (as 4) carbon fiber beams (3) along fuselage, each bulkhead is coupled together the keystone configuration that forms the framework type fuselage with some stringers (8).Forebody is reserved nose-gear mounting portion (5), and is provided with reinforcement bulkhead (7) in the middle part, in order to parts such as installation alighting gears.
Waist and wing connecting portion are furnished with reinforced bulkhead (7), and are connected with wing by auricle.By ingenious design to auricle, both satisfied the loading transfer requirement, accurately guaranteed designing requirements such as the true angle of incidence, sweepback angle simultaneously.In the embodiments of the invention as shown in fig. 5, aluminum alloy auricle (52) is fixed on the middle machine body reinforced bulkhead (51) by bolt (53), and the corresponding auricle on the wing is plugged on together by the connecting pin that passes hole (54), realize the assembling of wing and fuselage, thereby realize installing succinctly, the location accurately.
But but middle machine body of the present invention reaches folding and unfolding, can turn to nose-gear to link to each other with the folding and unfolding main landing gear by reinforced bulkhead.In the embodiment of the invention as shown in Figure 6, with the bolt that passes hole (62) auricle (63) will be installed and be fixed on the reinforcement bulkhead (7), by pin (64) main landing gear (65) is installed on the fuselage, realize installing and locating.Utilize a plurality of auricles altogether, with the loading transfer of a pair of main landing gear to fuselage.In the main landing gear position design rectification bulge cabin is arranged, hold main landing gear, reduce the fuselage resistance, and in main landing gear rectification bulge, be furnished with the maintenance flap, so that Maintenance and Repair.
According to one embodiment of present invention, forebody and middle machine body are connected through the hinge, and can open, convenient maintenance and handling goods.As in the embodiment shown in fig. 7, mmi machine head (73) inwall is equipped with crooked rocking arm (72), at the pre-buried pedestal of middle machine body inwall (74), by hinge rocking arm (72) and pedestal (74) is coupled together, can be easily forward/upwardly open preceding head.
Adopt the end face docking mode to link to each other according to middle machine body of the present invention with rear body.Connection mode according to an embodiment of the invention as shown in Figure 8, wherein polished rod (81) is installed at middle machine body, bury dress enclasp device (82) in end face bulkhead (84) inside of rear body (80), reserve screw fastener hole (83) at the rear body sidewall, the screw that fastener hole (83) is passed in utilization makes enclasp device (82) deformation that polished rod (81) is locked, realizes the location.
2) each space dividing and utilization.
Fig. 3 and 4 has shown fuselage interior space dividing according to an embodiment of the invention and utilization; Top ceiling (4) and floor (6) are divided into three parts with the cabin, and two parts are used for installing fuel tank up and down, thereby have effectively utilized the fitfull corner areas, have increased the fuel loading amount, when having prolonged boat and voyage.Consider the annexation of wing, alighting gear and airborne equipment and fuselage simultaneously, according to different locational spaces, the fuel tank (2) of different size is installed in fuselage top and bottom.Top ceiling (4) can be installed several fuel tanks (2), and fuel tank (2) also can be installed in (6) below on the floor.Simultaneously top ceiling (4) and floor (6) are designed to demountable structure, easy access and loading and unloading fuel tank, convenient each systematic pipeline of arranging.Fuel tank adopts split type, is embedded between the bulkhead, also is convenient to control the influence of fuel oil consumption to center of gravity of airplane position.
Advantage/beneficial effect
Advantage of the present invention and/or beneficial effect comprise:
1) structure adopts the framework pattern.Common bulkhead and reinforced bulkhead are alternate, and the former ties up shape, and the latter also is used to connect wing, alighting gear, rear body, forebody etc., and both play a supportive role to covering, trusses and stringer.When having kept stiffness of fuselage, intensity, also guaranteed the space requirement of fuselage interior.
2) hierarchical design of inner space can satisfy the needs that load and throw in.Upper and lower two-layer be used to arrange fuel tank, the pipeline etc. of arranging, the centre is used to place goods to be put and airborne equipment, the space availability ratio height.
3) waist, reasonable Arrangement cloth reinforced bulkhead is realized the installation of wing, alighting gear by attachment lug.By ingenious design to auricle, both satisfied the loading transfer requirement, accurately guaranteed designing requirements such as the true angle of incidence, sweepback angle simultaneously.Directly link to each other with the reinforcement bulkhead but but the folding and unfolding main landing gear reaches folding and unfolding, can turn to nose-gear to pass through auricle, in the main landing gear position design rectification bulge cabin is arranged, hold main landing gear, reduce the fuselage resistance, and in main landing gear rectification bulge, be furnished with the maintenance flap, so that Maintenance and Repair.
4) forebody and middle machine body are connected through the hinge, and can open, convenient maintenance and handling goods.Adopt the end face docking mode to link to each other, and fast loading and unloading joint is installed on interface frame, mating frame with rear body, for convenience detach, be beneficial to transportation.
Used the example of embodiments of the invention: big aircraft contracts and designs than proof machine
Scale model free flight test cost is low, interference is little, condition simulation true, no aviator's safety problem, is bringing into play important effect in aircraft development.
Big according to an embodiment of the invention aircraft contracts and adopts shoulder-wing configuration than proof machine, have good stable, hang four turbojets under the wing, adopt the framework type middle machine body, bear pneumatic rationally and effectively and loading load, satisfied the space requirement of loading with aerial simulation input.By cutting apart cabin space, increased fuel load when not taking loading space, when having strengthened boat/voyage.The transmission and the balance of the beam of framework type fuselage, stringer and covering fellowship load have improved weight efficiency, have alleviated structural weight effectively.Middle machine body has also been realized being connected with the detachable, firm of wing, alighting gear, head and rear body by reinforced bulkhead.
Should be understood that, in above narration and explanation to just explanation but not determinate of description that the present invention carried out, and do not breaking away under the prerequisite of the present invention that limits as appended claims, can carry out various changes, distortion and/or correction the foregoing description.
Claims (9)
1. be applicable to the preceding middle machine body of framework type of unmanned plane and large-scale scale model aircraft, it is characterized in that comprising:
A plurality of bulkheads (1), they keep and constitute the appearance profile of described preceding middle machine body,
The many carbon fiber beams (3) that the described appearance profile of middle machine body is vertically arranged before described, be used for each described bulkhead (1) couple together form described before the keystone configuration of middle machine body.
2. according to middle machine body before the framework type of claim 1, it is characterized in that further comprising:
The nose-gear mounting portion (5) that the front portion of middle machine body is reserved before described is used to install alighting gear;
Be arranged on the reinforcement bulkhead (7,51) of the middle part of described preceding middle machine body.(7) be used to install main landing gear, (51) are used to install wing.
3. according to middle machine body before the framework type of claim 2, it is characterized in that
At least one described reinforcement bulkhead (51) is adapted to pass through bolt (53) and captives joint with wing attachment lug (52), and described wing attachment lug (52) has hole (54), be plugged on together with corresponding auricle on the wing thereby be adapted to pass through the connecting pin that passes hole (54), thereby realize being connected of wing and described preceding middle machine body.
4. according to middle machine body before the framework type of claim 2, it is characterized in that
At least one described reinforcement bulkhead (7);
Be adapted to pass through the bolt in the hole of passing on the alighting gear attachment lug (63) (62) and captive joint with described alighting gear attachment lug (63),
Wherein said alighting gear attachment lug (63) is adapted to pass through alighting gear connection pin (64) and main landing gear (65) is installed on the described alighting gear attachment lug (63), thereby described main landing gear (65) is installed on the described preceding middle machine body in road.
5. according to middle machine body before the framework type of claim 4, it is characterized in that
Described main landing gear (65) is connected with a plurality of bulkheads (1) and/or reinforcement bulkhead (7) by a plurality of described alighting gear attachment lugs (63), thereby the loading transfer of described main landing gear is arrived fuselage;
In the main landing gear position design rectification bulge cabin is arranged, hold main landing gear, reduce the fuselage resistance, and in main landing gear rectification bulge, be furnished with the maintenance flap, so that Maintenance and Repair.
6. according to middle machine body before any one the framework type among the claim 1-4, it is characterized in that
The middle machine body inwall is embedded with pedestal (74) before described, be used for coupling together by crooked rocking arm (72) and described pedestal (74) that hinge will be installed on a preceding head (73) inwall, thereby can be easily forward/upwardly open described before head.
7. according to middle machine body before any one the framework type among the claim 1-4, it is characterized in that
A polished rod (81) is installed on the middle machine body before described, and it is locked that described polished rod (81) is suitable for being buried end face bulkhead (a 84) enclasp device of in-to-in (82) institute that is contained in a rear body (80),
Wherein be reserved with screw fastener hole (83), utilize the screw that passes fastener hole (83) to make enclasp device (82) deformation that described polished rod (81) is locked at the rear body sidewall.
8. according to middle machine body before any one the framework type among the claim 1-4, it is characterized in that
The inside of middle machine body is divided into three parts by a top ceiling (4) and a floor (6) before described.
9. middle machine body before the framework type according to Claim 8 is characterized in that
Upper and lower two parts in described three parts are used for installing fuel tank;
Described top ceiling (4) and floor (6) they are demountable structure, thus easy access and loading and unloading fuel tank and/or arrange each systematic pipeline,
Described fuel tank adopts split type and is embedded between bulkhead (1) and/or the reinforced bulkhead (7), thereby is convenient to control the influence of fuel oil consumption to center of gravity of airplane position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102390070A CN102139757A (en) | 2010-07-28 | 2010-07-28 | Framed front center fuselage suitable for unmanned plane and model plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102390070A CN102139757A (en) | 2010-07-28 | 2010-07-28 | Framed front center fuselage suitable for unmanned plane and model plane |
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| CN102139757A true CN102139757A (en) | 2011-08-03 |
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| CN2010102390070A Pending CN102139757A (en) | 2010-07-28 | 2010-07-28 | Framed front center fuselage suitable for unmanned plane and model plane |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991665A (en) * | 2011-09-08 | 2013-03-27 | 空中客车运营简化股份公司 | Frame element of an aircraft fuselage |
| CN105000169A (en) * | 2015-07-22 | 2015-10-28 | 北京航空航天大学 | Novel folding wing and driving and deadlocking mechanism |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| CN106892083A (en) * | 2017-04-12 | 2017-06-27 | 北京建中数字科技有限公司 | A kind of bionical frame for intersecting twin-rotor helicopter |
| CN107117289A (en) * | 2017-05-09 | 2017-09-01 | 中安（天津）航空设备有限公司 | A kind of emergency management and rescue maneuver device |
| CN107933875A (en) * | 2018-01-08 | 2018-04-20 | 安阳全丰航空植保科技股份有限公司 | Lightweight adjusts rigidity truss-like unmanned aerial vehicle body |
| CN109157847A (en) * | 2018-11-06 | 2019-01-08 | 大连理工大学 | A kind of fixed-wing model plane structure and installation method based on carbon beam |
| CN111891331A (en) * | 2020-07-27 | 2020-11-06 | 中国航空工业集团公司西安飞机设计研究所 | Transport airplane |
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| US7234667B1 (en) * | 2003-12-11 | 2007-06-26 | Talmage Jr Robert N | Modular aerospace plane |
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Patent Citations (4)
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| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| US20050006525A1 (en) * | 2003-06-20 | 2005-01-13 | Byers David W. | Unmanned aerial vehicle for logistical delivery |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991665B (en) * | 2011-09-08 | 2017-04-12 | 空中客车运营简化股份公司 | Frame element of an aircraft fuselage |
| CN102991665A (en) * | 2011-09-08 | 2013-03-27 | 空中客车运营简化股份公司 | Frame element of an aircraft fuselage |
| CN105000169A (en) * | 2015-07-22 | 2015-10-28 | 北京航空航天大学 | Novel folding wing and driving and deadlocking mechanism |
| CN105000169B (en) * | 2015-07-22 | 2017-05-10 | 北京航空航天大学 | Novel folding wing and driving and deadlocking mechanism |
| CN105398582B (en) * | 2015-11-13 | 2018-06-19 | 中国人民解放军国防科学技术大学 | A kind of covering, bulkhead integration unmanned aerial vehicle body and preparation method thereof |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| CN106892083A (en) * | 2017-04-12 | 2017-06-27 | 北京建中数字科技有限公司 | A kind of bionical frame for intersecting twin-rotor helicopter |
| CN106892083B (en) * | 2017-04-12 | 2023-11-21 | 北京清航紫荆装备科技有限公司 | Bionic rack of crossed double-rotor helicopter |
| CN107117289A (en) * | 2017-05-09 | 2017-09-01 | 中安（天津）航空设备有限公司 | A kind of emergency management and rescue maneuver device |
| CN107117289B (en) * | 2017-05-09 | 2023-05-23 | 中安（天津）航空设备有限公司 | Emergency rescue exercise device |
| CN107933875A (en) * | 2018-01-08 | 2018-04-20 | 安阳全丰航空植保科技股份有限公司 | Lightweight adjusts rigidity truss-like unmanned aerial vehicle body |
| CN107933875B (en) * | 2018-01-08 | 2024-06-07 | 安阳全丰航空植保科技股份有限公司 | Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable |
| CN109157847A (en) * | 2018-11-06 | 2019-01-08 | 大连理工大学 | A kind of fixed-wing model plane structure and installation method based on carbon beam |
| CN109157847B (en) * | 2018-11-06 | 2023-11-24 | 大连理工大学 | Fixed wing aeromodelling structure based on carbon rod and installation method |
| CN111891331A (en) * | 2020-07-27 | 2020-11-06 | 中国航空工业集团公司西安飞机设计研究所 | Transport airplane |
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Application publication date: 20110803 |