CN105109673A - Large-loading multi-point coordinated undercarriage fixed connection structure - Google Patents
Large-loading multi-point coordinated undercarriage fixed connection structure Download PDFInfo
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- CN105109673A CN105109673A CN201510527840.8A CN201510527840A CN105109673A CN 105109673 A CN105109673 A CN 105109673A CN 201510527840 A CN201510527840 A CN 201510527840A CN 105109673 A CN105109673 A CN 105109673A
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Abstract
The invention relates to a large-loading multi-point coordinated undercarriage fixed connection structure which comprises a main undercarriage fixed connection joint girder, an inside pressure bar, an outside pressure bar and an undercarriage diagonal draw bar joint, and an undercarriage diagonal draw bar adaptor can be selectively arranged according to practical situations. An undercarriage diagonal draw bar is connected to the undercarriage diagonal draw bar joint through the undercarriage diagonal draw bar adaptor, the undercarriage diagonal draw bar joint is connected with an undercarriage bulkhead stiffening girder and an undercarriage intersection frame, and two ends of the inside pressure bar and the outside pressure bar are respectively connected with the main undercarriage fixed connection joint girder and the undercarriage diagonal draw bar adaptor so as to form an integral force transfer system, thereby dispersing the load of the main undercarriage fixed connection joint girder, effectively reducing the load transferred from the undercarriage diagonal draw bar joint to the undercarriage bulkhead stiffening girder and the undercarriage intersection frame, also reducing the load transferred from the main undercarriage fixed connection joint girder to a fuselage, and further effectively solving the problem of large landing load of the undercarriage.
Description
Technical field
The present invention relates to a kind of large posting coordinated multi-point alighting gear fixed connection structure, belong to unmanned plane structure-design technique field.
Background technology
Advanced High Performance Unmanned Aerial Vehicle bears heavy shock loads when landing, and due to factors such as housing construction general layouts, cannot directly utilize body longeron directly to transmit main landing gear landing load.
According to documentary investigation, current domestic relevant design scheme is mainly conventional confguration configuration, to be directly connected transmitted load by comprehensive application fuselage frame, beam or wing rib, beam or wall joint and main landing gear, can not be applicable to the advanced unmanned plane structure of a class.
How solving the posting of unmanned plane speed landing heavy shock loads (as more than 30t load), is the difficult point of unmanned plane structure design.
Summary of the invention
How the present invention bears the problem of heavy shock loads when being and solving UAV Landing, provide a kind of large posting coordinated multi-point alighting gear fixed connection structure.
The object of the invention is achieved by following technical solution:
A kind of large posting coordinated multi-point alighting gear fixed connection structure is provided, comprises: main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar and alighting gear diagonal draw bar;
Described main landing gear is fixedly connected with joint beam and has the medial surface, trailing flank and the lateral surface that connect successively, is positioned at the beam section of three lateral inner, and is positioned at the first connecting portion and second connecting portion of beam pars infrasegmentalis; Described medial surface is fixed on landing gear compartment opening side bar, and the outside face of medial surface mates with the web surface of landing gear compartment opening side bar; Described trailing flank is fixed on after landing gear compartment opening on reinforcing frame, and the outside face of described trailing flank mates with the web surface of reinforcing frame after landing gear compartment opening; Described lateral surface is fixed on fuselage side wall plate, and the outside face of described lateral surface mates with the inside face of fuselage side wall plate; Described first connecting portion, is connected to lower coupling end and the main landing gear upper inner fork ear of inner side depression bar; Described second connecting portion is connected to lower coupling end and the main landing gear upper outside fork ear of outside depression bar;
Described inner side depression bar has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the first connecting portion that described main landing gear is fixedly connected with joint beam;
Described outside depression bar has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the second connecting portion that described main landing gear is fixedly connected with joint beam;
Described alighting gear diagonal draw bar has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam and alighting gear intersection point frame; The coupling end of described alighting gear diagonal draw bar has through hole, installs plain radial bearing in through hole; The through hole of coupling end on the depression bar of inner side, on the through hole of the coupling end of main landing gear digonal link upper left-hand through hole, described alighting gear diagonal draw bar, main landing gear digonal link upper right through hole, described outside depression bar, the through hole of coupling end is coaxially arranged according to order from inside to outside, and shear-pin is fixedly connected with through five through holes.
Preferably, the lower coupling end of inner side depression bar and outside depression bar all has through hole, described first connecting portion has the first auricle and the second auricle, described first auricle and the second auricle have through hole, the through hole that the through hole of the through hole of described first auricle, the lower coupling end of inner side depression bar, main landing gear upper inner pitch ear through hole and the second auricle is coaxially arranged successively, and the first bearing pin is fixedly connected with through four through holes; Described second connecting portion has third ear sheet and the 4th auricle, described third ear sheet and the 4th auricle have through hole, the through hole that the through hole of the through hole of described third ear sheet, the lower coupling end of outside depression bar, main landing gear upper outside pitch ear through hole and the 4th auricle is coaxially arranged successively, and the second bearing pin is fixedly connected with through four through holes; Described first bearing pin is coaxial with the second bearing pin.
Preferably, described main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar be wholely set.
Preferably, described main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar, and alighting gear diagonal draw bar adopts titanium alloy to make.
Preferably, the bearing beam of described inner side depression bar and outside depression bar adopts composite material rectangular to cut section bar, and titanium alloy or steel mosaic part are inlayed in upper coupling end and lower coupling end through hole inside.
A kind of large posting coordinated multi-point alighting gear fixed connection structure, comprising: main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar and alighting gear diagonal draw bar and alighting gear digonal link adaptor simultaneously;
Described main landing gear is fixedly connected with joint beam and has the medial surface, trailing flank and the lateral surface that connect successively, is positioned at the beam section of three lateral inner, and is positioned at the first connecting portion and second connecting portion of beam pars infrasegmentalis; Described medial surface is fixed on landing gear compartment opening side bar, and the outside face of medial surface mates with the web surface of landing gear compartment opening side bar; Described trailing flank is fixed on after landing gear compartment opening on reinforcing frame, and the outside face of described trailing flank mates with the web surface of reinforcing frame after landing gear compartment opening; Described lateral surface is fixed on fuselage side wall plate, and the outside face of described lateral surface mates with the inside face of fuselage side wall plate; Described first connecting portion, is connected to lower coupling end and the main landing gear upper inner fork ear of inner side depression bar; Described second connecting portion is connected to lower coupling end and the main landing gear upper outside fork ear of outside depression bar;
Described inner side depression bar has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the first connecting portion that described main landing gear is fixedly connected with joint beam;
Described outside depression bar has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the second connecting portion that described main landing gear is fixedly connected with joint beam;
Described alighting gear diagonal draw bar has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam and alighting gear intersection point frame; The coupling end of described alighting gear diagonal draw bar has through hole; Described alighting gear diagonal draw bar connects the upper coupling end of alighting gear digonal link adaptor;
Alighting gear digonal link adaptor has upper coupling end and lower coupling end, the upper coupling end of described alighting gear digonal link adaptor has the 5th auricle and the 6th auricle, the through hole of the described through hole of the 5th auricle, the coupling end of alighting gear diagonal draw bar and the through hole of the 6th auricle are coaxially arranged successively, and the first shear-pin is fixedly connected with through three through holes successively; The lower coupling end of described alighting gear digonal link adaptor has the 7th auricle and the 8th auricle, the through hole of coupling end on the depression bar of inner side, the through hole of the 7th auricle, on main landing gear digonal link upper through-hole, the through hole of the 8th auricle, described outside depression bar, the through hole of coupling end is coaxially arranged successively, and the second shear-pin is fixedly connected with through five through holes successively.
Preferably, the lower coupling end of inner side depression bar and outside depression bar all has through hole, described first connecting portion has the first auricle and the second auricle, described first auricle and the second auricle have through hole, the through hole that the through hole of the through hole of described first auricle, the lower coupling end of inner side depression bar, main landing gear upper inner pitch ear through hole and the second auricle is coaxially arranged successively, and the first bearing pin is fixedly connected with through four through holes; Described second connecting portion has third ear sheet and the 4th auricle, described third ear sheet and the 4th auricle have through hole, the through hole that the through hole of the through hole of described third ear sheet, the lower coupling end of outside depression bar, main landing gear upper outside pitch ear through hole and the 4th auricle is coaxially arranged successively, and the second bearing pin is fixedly connected with through four through holes; Described first bearing pin is coaxial with the second bearing pin.
Preferably, described main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar be wholely set.
Preferably, described main landing gear is fixedly connected with joint beam, inner side depression bar, outside depression bar, and alighting gear diagonal draw bar adopts titanium alloy to make.
Preferably, the bearing beam of described inner side depression bar and outside depression bar adopts composite material rectangular to cut section bar, and titanium alloy or steel mosaic part are inlayed in upper coupling end and lower coupling end through hole inside.
The present invention compared with prior art tool has the following advantages:
(1) connection of main landing gear joint beam and alighting gear diagonal draw bar is realized by layout two pressure rod structures, form overall force transfer system, main landing gear has been disperseed to be fixedly connected with the load of joint beam, effectively reduce the load that alighting gear diagonal draw bar is passed to alighting gear bulkhead strength beam and alighting gear intersection point frame, also reduce main landing gear simultaneously and be fixedly connected with the load that joint beam reaches fuselage.Efficiently solve the large posting problem of alighting gear landing load.
(2) alighting gear is fixedly connected with joint beam is whole titanium alloy product, and beam and joint one, can adopt mechanical processing technique or 3D printing shaping, structure efficiency is high.
(3) alighting gear is fixedly connected with joint beam and can be used for the reinforcement of housing construction opening and the reinforcement of wing body connection structure, improves the strength and stiffness of housing construction critical area, implementation structure comprehensive application, improves structure efficiency.
(4) can arrange that needs increase or delete main landing gear digonal link adapter coupling, strong adaptability according to structure space.
Accompanying drawing explanation
Fig. 1 is alighting gear fixed connection structure of the present invention and fuselage scheme of installation; Wherein scheme fixed connection structure that (a) be band alighting gear digonal link adaptor and fuselage scheme of installation, wherein figure (b) is fixed connection structure not with alighting gear digonal link adaptor and fuselage scheme of installation;
Fig. 2 is alighting gear fixed connection structure rough package drawing of the present invention;
Fig. 3 is alighting gear fixed connection structure of the present invention composition schematic diagram; Wherein scheme the fixed connection structure composition schematic diagram that (a) is band alighting gear digonal link adaptor; Wherein figure (b) is the fixed connection structure composition schematic diagram not with alighting gear digonal link adaptor;
Fig. 4 is that alighting gear of the present invention is fixedly connected with joint girder construction front view;
Fig. 5 is that alighting gear of the present invention is fixedly connected with joint girder construction back view;
Fig. 6 is pressure rod structure schematic diagram of the present invention;
Fig. 7 is alighting gear digonal link of the present invention and body connection diagram; Wherein scheme alighting gear digonal link that (a) be band alighting gear digonal link adaptor and body connection diagram, wherein figure (b) is alighting gear digonal link not with alighting gear digonal link adaptor and body connection diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention will be further described.
Fig. 1 and Fig. 2 is alighting gear fixed connection structure and fuselage overall installation schematic diagram.Fixed connection structure mainly comprises: main landing gear is fixedly connected with joint beam 1, inner side depression bar 2, outside depression bar 3, alighting gear diagonal draw bar 5, can select to increase alighting gear digonal link adaptor 4 according to actual conditions.Fixed connection structure with aircraft as lower component is connected: the part such as reinforcing frame 10, fuselage side wall plate 11, main landing gear 12 main landing gear digonal link 13 after landing gear compartment opening side bar 6, alighting gear bulkhead 7, alighting gear bulkhead strength beam 8, alighting gear intersection point frame 9, landing gear compartment opening.Alighting gear 12 and main landing gear are fixedly connected with joint beam 1 and are connected by shear-pin, bear landing impact load, and reinforcing frame 10 and landing gear compartment opening side bar 6 etc. after load being diffused to fuselage side wall plate 11, landing gear compartment opening.
Provide two kinds of configurations (a) and (b) in Fig. 1, configuration (a) relative configuration (b) increases an alighting gear digonal link adaptor 4, specifically as shown in Figures 2 and 6.
Main landing gear is fixedly connected with joint beam 1 and has the interior plate 1-1, rear quarter panel 1-2 and the outer panel 1-3 that connect successively, is positioned at the beam section 1-4 of three side plate inside, and is positioned at the first connecting portion 1-5 and the second connecting portion 1-6 of beam section 1-4 bottom; Described interior plate 1-1 is fixed on landing gear compartment opening side bar 6, and the outside face of interior plate 1-1 mates with the web surface of landing gear compartment opening side bar 6; Described rear quarter panel 1-2 is fixed on after landing gear compartment opening on reinforcing frame 10, and the outside face of described rear quarter panel 1-2 mates with the web surface of reinforcing frame 10 after landing gear compartment opening; Described outer panel 1-2 is fixed on fuselage side wall plate 11, and the outside face of described outer panel 1-2 mates with the inside face of fuselage side wall plate 11; Described first connecting portion 1-5, is connected to lower coupling end and the main landing gear 12 upper inner fork ear 15 of inner side depression bar 2; Described second connecting portion 1-6 is connected to lower coupling end and the main landing gear 12 upper outside fork ear 14 of outside depression bar 3.
Described inner side depression bar 2 has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the first connecting portion that described main landing gear is fixedly connected with joint beam 1;
Described outside depression bar 3 has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the second connecting portion that described main landing gear is fixedly connected with joint beam 1; Outside depression bar 3 bearing beam is variable section structure, and stage casing is cuboid, two ends necking in, and transition is connected to coupling end and lower coupling end.
See accompanying drawing 7, described alighting gear diagonal draw bar 5 has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam 8 and alighting gear intersection point frame 9; The coupling end of described alighting gear diagonal draw bar 5 has through hole, installs plain radial bearing in through hole; See Fig. 3, the through hole of coupling end on the depression bar 2 of inner side, on the through hole of the coupling end of main landing gear digonal link 13 upper left-hand through hole, described alighting gear diagonal draw bar 5, main landing gear digonal link 13 upper right through hole, described outside depression bar 3, the through hole of coupling end is coaxially arranged according to order from inside to outside, and shear-pin is fixedly connected with through five through holes.
Fig. 1 (a) is adopted to the type connecting alighting gear digonal link adaptor 4, described alighting gear diagonal draw bar 5 has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam 8 and alighting gear intersection point frame 9; The coupling end of described alighting gear diagonal draw bar 5 has through hole; Described alighting gear diagonal draw bar 5 connects the upper coupling end of alighting gear digonal link adaptor 4.
Alighting gear digonal link adaptor 4 has upper coupling end and lower coupling end, the upper coupling end of described alighting gear digonal link adaptor 4 has the 5th auricle and the 6th auricle, the through hole of the described through hole of the 5th auricle, the coupling end of alighting gear diagonal draw bar 5 and the through hole of the 6th auricle are coaxially arranged successively, and the first shear-pin is fixedly connected with through three through holes successively; The lower coupling end of described alighting gear digonal link adaptor 4 has the 7th auricle and the 8th auricle, the through hole of coupling end on the depression bar 2 of inner side, the through hole of the 7th auricle, on main landing gear digonal link 13 upper through-hole, the through hole of the 8th auricle, described outside depression bar 3, the through hole of coupling end is coaxially arranged successively according to order from inside to outside, and the second shear-pin is fixedly connected with through five through holes successively.
As shown in Fig. 3 (a) and Fig. 2, in configuration (a), alighting gear digonal link 13 is connected to alighting gear diagonal draw bar 5 by alighting gear digonal link adaptor 4, alighting gear diagonal draw bar 5 is connected with alighting gear intersection point frame 9 with alighting gear bulkhead strength beam 8, inner side depression bar 2 is fixedly connected with joint beam 1 respectively with outside depression bar 3 two ends and is connected with alighting gear digonal link adaptor 4 with main landing gear, form an overall force transfer system.As shown in Fig. 3 (b) and Fig. 2, in configuration (b), alighting gear digonal link 13 is directly connected with alighting gear diagonal draw bar 5.Alighting gear diagonal draw bar 5 is connected with alighting gear intersection point frame 9 with alighting gear bulkhead strength beam 8, and inner side depression bar 2 and outside depression bar 3 two ends are fixedly connected with joint beam 1 respectively and are connected with alighting gear diagonal draw bar 5 with main landing gear, form an overall force transfer system.
Fig. 4,5 is fixedly connected with joint beam schematic diagram for alighting gear, and main landing gear is fixedly connected with joint beam 1 and is wholely set, and titanium alloy machine can be adopted to add or the advanced forming process such as 3D printing.For improving wear-resisting and bearer properties, main landing gear is fixedly connected with in joint beam 1 auricle axis hole can increase bronze bush as required.Bearing beam has and alleviates groove, when the rigidity do not affected, and expendable weight.Rear quarter panel 1-2 is divided into left section and right section, and two sections of centres have opening, and two sections are connected by beam section 1-4, owing to not bearing load in the middle part of rear quarter panel 1-2, arrange the further loss of weight of middle opening.
Fig. 6 is depression bar schematic diagram, and depression bar is important component part in this force transferring structure scheme, main landing gear is fixedly connected with joint beam 1 and is connected with alighting gear diagonal draw bar 5, and forms an overall force transfer system with fuselage surrounding structure.This part can adopt high-strength and high-modulus material (as high strength alumin ium alloy or titanium alloy) machine add-on type, also the establishment or Wrapping formed of carbon fiber composite material three-dimensional can be adopted, i shaped cross section or rectangular beam should be designed to improve rigidity according to load condition, interface coordination and selection, but certain damage tolerance requirements should be taken into account simultaneously.The i shaped cross section beam adopting metal machine to add structure can be designed to alleviating groove, adopt composite structure then can binding fiber be wound around or three-dimensional establishment etc. technological design is orthogonal cuts section bar, two ends are fixedly connected with joint beam 1 and alighting gear diagonal draw bar 5 (or alighting gear digonal link adaptor 4) junction respectively and inlay titanium alloy or steel mosaic part to improve Joint strenght with main landing gear.
As Fig. 1, shown in Fig. 2 and Fig. 3, during aircraft lands, main landing gear 12 is fixedly connected with joint beam 1 to main landing gear, inner side depression bar 2 and outside depression bar 3 transmitted load, simultaneously digonal link 13 is to depression bar 2 and outside depression bar 3 transmitted load inside alighting gear diagonal draw bar 5 or alighting gear digonal link adaptor 4, therefore, known a part of load from main landing gear 12 and digonal link 13 is passed through to arrange that inner side depression bar 2 and outside depression bar 3 realize self-balancing dexterously by analysis, effectively reduce the load that alighting gear diagonal draw bar 5 is passed to alighting gear bulkhead strength beam 8 and alighting gear intersection point frame 9, also reduce main landing gear simultaneously and be fixedly connected with the load that joint beam 1 reaches fuselage.
Through test and application attestation, this structure is applied to unmanned plane structure, can bear the landing load being greater than 30t from main landing gear 12 through appropriate design, and digonal link 13 is greater than the load of 20t.
The above; be only the detailed description of the invention of the best of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of professional and technical personnel in the field.
Claims (10)
1. a large posting coordinated multi-point alighting gear fixed connection structure, is characterized in that comprising: main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3) and alighting gear diagonal draw bar (5);
Described main landing gear is fixedly connected with joint beam (1) and has the interior plate (1-1), rear quarter panel (1-2) and the outer panel (1-3) that connect successively, be positioned at the beam section (1-4) of three side plate inside, and be positioned at the first connecting portion (1-5) and second connecting portion (1-6) of beam section (1-4) bottom; Described interior plate (1-1) is fixed on landing gear compartment opening side bar (6), and the outside face of interior plate (1-1) mates with the web surface of landing gear compartment opening side bar (6); Described rear quarter panel (1-3) is fixed on after landing gear compartment opening on reinforcing frame (10), and the outside face of described rear quarter panel (1-3) mates with the web surface of reinforcing frame (10) after landing gear compartment opening; Described outer panel (1-3) is fixed on fuselage side wall plate (11), and the outside face of described outer panel (1-3) mates with the inside face of fuselage side wall plate (11); Described first connecting portion (1-5), is connected to lower coupling end and main landing gear (12) upper inner fork ear (15) of inner side depression bar (2); Described second connecting portion (1-6) is connected to lower coupling end and main landing gear (12) upper outside fork ear (14) in outside depression bar (3);
Described inner side depression bar (2) has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the first connecting portion (1-5) that described main landing gear is fixedly connected with joint beam (1);
Described outside depression bar (3) has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the second connecting portion (1-6) that described main landing gear is fixedly connected with joint beam (1);
Described alighting gear diagonal draw bar (5) has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam (8) and alighting gear intersection point frame (9); The coupling end of described alighting gear diagonal draw bar (5) has through hole, installs plain radial bearing in through hole; The through hole of the upper coupling end in inner side depression bar (2), the through hole of the through hole of the coupling end of main landing gear digonal link (13) upper left-hand through hole, described alighting gear diagonal draw bar (5), main landing gear digonal link (13) upper right through hole, the upper coupling end in described outside depression bar (3) is coaxially arranged successively, and shear-pin is fixedly connected with through five through holes.
2. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 1, it is characterized in that, the lower coupling end of inner side depression bar (2) and outside depression bar (3) all has through hole, described first connecting portion (1-5) has the first auricle and the second auricle, described first auricle and the second auricle have through hole, the through hole of described first auricle, the through hole of the lower coupling end of inner side depression bar (2), the through hole of main landing gear (12) upper inner fork ear (15) through hole and the second auricle is coaxially arranged successively, first bearing pin is fixedly connected with through four through holes, described second connecting portion (1-6) has third ear sheet and the 4th auricle, described third ear sheet and the 4th auricle have through hole, the through hole that the through hole of the through hole of described third ear sheet, the lower coupling end of outside depression bar (3), main landing gear (12) upper outside pitch ear (14) through hole and the 4th auricle is coaxially arranged successively, and the second bearing pin is fixedly connected with through four through holes, described first bearing pin is coaxial with the second bearing pin.
3. posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 1 large, is characterized in that, described main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3) are wholely set.
4. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 1, it is characterized in that, described main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3), and alighting gear diagonal draw bar (5) adopts titanium alloy to make.
5. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 2, it is characterized in that, the bearing beam of described inner side depression bar (2) and outside depression bar (3) adopts composite material rectangular to cut section bar, and titanium alloy or steel mosaic part are inlayed in upper coupling end and lower coupling end through hole inside.
6. a large posting coordinated multi-point alighting gear fixed connection structure, is characterized in that comprising: main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3) and alighting gear diagonal draw bar (5) and alighting gear digonal link adaptor (4);
Described main landing gear is fixedly connected with joint beam (1) and has the interior plate (1-1), rear quarter panel (1-2) and the outer panel (1-3) that connect successively, be positioned at the beam section (1-4) of three side plate inside, and be positioned at the first connecting portion (1-5) and second connecting portion (1-6) of beam section (1-4) bottom; Described interior plate (1-1) is fixed on landing gear compartment opening side bar (6), and the outside face of interior plate (1-1) mates with the web surface of landing gear compartment opening side bar (6); Described rear quarter panel (1-2) is fixed on after landing gear compartment opening on reinforcing frame (10), and the outside face of described rear quarter panel (1-2) mates with the web surface of reinforcing frame (10) after landing gear compartment opening; Described outer panel (1-2) is fixed on fuselage side wall plate (11), and the outside face of described outer panel (1-2) mates with the inside face of fuselage side wall plate (11); Described first connecting portion (1-5), is connected to lower coupling end and main landing gear (12) upper inner fork ear (15) of inner side depression bar (2); Described second connecting portion (1-6) is connected to lower coupling end and main landing gear (12) upper outside fork ear (14) in outside depression bar (3);
Described inner side depression bar (2) has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the first connecting portion (1-5) that described main landing gear is fixedly connected with joint beam (1);
Described outside depression bar (3) has the upper coupling end, bearing beam and the lower coupling end that connect successively, and described upper coupling end has through hole; Described bearing beam has and alleviates groove; Described lower coupling end is connected to the second connecting portion (1-6) that described main landing gear is fixedly connected with joint beam (1);
Described alighting gear diagonal draw bar (5) has fixed end and coupling end, and described fixed end is fixed to alighting gear bulkhead strength beam (8) and alighting gear intersection point frame (9); The coupling end of described alighting gear diagonal draw bar (5) has through hole; Described alighting gear diagonal draw bar (5) connects the upper coupling end of alighting gear digonal link adaptor (4);
Alighting gear digonal link adaptor (4) has upper coupling end and lower coupling end, the upper coupling end of described alighting gear digonal link adaptor (4) has the 5th auricle and the 6th auricle, the through hole of described 5th auricle, the through hole of the coupling end of alighting gear diagonal draw bar (5) and the through hole of the 6th auricle are coaxially arranged successively, and the first shear-pin is fixedly connected with through three through holes successively; The lower coupling end of described alighting gear digonal link adaptor (4) has the 7th auricle and the 8th auricle, the through hole of the upper coupling end in inner side depression bar (2), the through hole of the 7th auricle, the through hole of main landing gear digonal link (13) upper through-hole, the through hole of the 8th auricle, the upper coupling end in described outside depression bar (3) is coaxially arranged successively, and the second shear-pin is fixedly connected with through five through holes successively.
7. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 6, it is characterized in that, the lower coupling end of inner side depression bar (2) and outside depression bar (3) all has through hole, described first connecting portion (1-5) has the first auricle and the second auricle, described first auricle and the second auricle have through hole, the through hole of described first auricle, the through hole of the lower coupling end of inner side depression bar (2), the through hole of main landing gear (12) upper inner fork ear (15) through hole and the second auricle is coaxially arranged successively, first bearing pin is fixedly connected with through four through holes, described second connecting portion (1-6) has third ear sheet and the 4th auricle, described third ear sheet and the 4th auricle have through hole, the through hole that the through hole of the through hole of described third ear sheet, the lower coupling end of outside depression bar (3), main landing gear (12) upper outside pitch ear (14) through hole and the 4th auricle is coaxially arranged successively, and the second bearing pin is fixedly connected with through four through holes, described first bearing pin is coaxial with the second bearing pin.
8. posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 6 large, is characterized in that, described main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3) are wholely set.
9. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 6, it is characterized in that, described main landing gear is fixedly connected with joint beam (1), inner side depression bar (2), outside depression bar (3), and alighting gear diagonal draw bar (5) adopts titanium alloy to make.
10. large posting coordinated multi-point alighting gear fixed connection structure as claimed in claim 8, it is characterized in that, the bearing beam of described inner side depression bar (2) and outside depression bar (3) adopts composite material rectangular to cut section bar, and titanium alloy or steel mosaic part are inlayed in upper coupling end and lower coupling end through hole inside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| EP3275780A1 (en) * | 2016-07-28 | 2018-01-31 | Goodrich Corporation | Thin-skin side stay beams and landing gear assemblies |
| CN107985560A (en) * | 2017-11-30 | 2018-05-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft main landing gear reinforced frame structure |
| CN112173084A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Retractable main landing gear bearing structure of unmanned high-speed helicopter and design method thereof |
| CN112173083A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
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| EP3275780A1 (en) * | 2016-07-28 | 2018-01-31 | Goodrich Corporation | Thin-skin side stay beams and landing gear assemblies |
| CN107985560A (en) * | 2017-11-30 | 2018-05-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft main landing gear reinforced frame structure |
| CN112173084A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Retractable main landing gear bearing structure of unmanned high-speed helicopter and design method thereof |
| CN112173083A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Tail undercarriage attach fitting |
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| CN105109673B (en) | 2017-05-03 |
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