CN103466496A - Airplane jacking device - Google Patents
Airplane jacking device Download PDFInfo
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- CN103466496A CN103466496A CN2013103743942A CN201310374394A CN103466496A CN 103466496 A CN103466496 A CN 103466496A CN 2013103743942 A CN2013103743942 A CN 2013103743942A CN 201310374394 A CN201310374394 A CN 201310374394A CN 103466496 A CN103466496 A CN 103466496A
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- jack
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- gusseted
- bulb
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Abstract
The invention belongs to design technologies of airplane body structures and particularly relates to an airplane jacking device. The airplane jacking device is characterized by comprising a jack triangular support (1), a jacking ball head (2), two connector components (3), a pull bar (4) and a wall plate support (5). The airplane jacking device is light in weight and capable of transmitting high load to other structures of an airplane body quickly. The existing airplane support structure is generally used for supporting small- and medium-sized airplanes. The airplane jacking device is used as a support structure for large-sized transport airplanes and is new in the field of support structures for large airplanes in China. The airplane jacking device weighs 60Kg, is capable of bearing and transmitting 130t load, and is a lightweight structure, so that the cost is reduced. 130t load from the a jack can be quickly spread to sidewall and lower wall structures of the airplane through the support structure, so that stress concentration is avoided; the airplane jacking device has fine mechanical property. The airplane jacking device is reusable and durable. Production process of parts of the airplane jacking device is simple and easily implemented.
Description
Technical field
The invention belongs to the aircraft fuselage structure designing technique, be specifically related to a kind of aircraft jacking system.
Background technology
External some large aircraft does not arrange the body jacking system, and over-borrowing, with wing or alighting gear jack-up, is furnished with high requirement to jack-up point, and outside jack is had relatively high expectations, and has increased expense and the difficulty of aircraft flight-line service.
The Some Domestic aircraft has bracing or strutting arrangement, but, for being applicable to the bracing or strutting arrangement of middle-size and small-size aircraft, jack-up load is less, and the structural arrangement design difficulty is little.The remainder aircraft does not arrange the body jacking system, such as low wing aircrafts such as Arj21 aircrafts, is the zone that choice structure is firm on wing, load is beneficial to diffusion, directly arranges the jack-up point, with jack, coordinates, for the jack-up of aircraft.Although such structure is simple, applicable surface is narrower, and the aircraft higher for wing is also inapplicable, can't be used in conjunction with jack.Jacking system of the present invention, for the support of large aircraft, still belong to pioneering at home.
Summary of the invention
The objective of the invention is: design a kind of light structures that can support large aircraft.In existing aircraft, some does not arrange the body jacking system, or at wing, alighting gear, the jack-up point is set, or is only applicable to the jack-up structure of middle-size and small-size aircraft, for the Special top lifting device that is applicable to large aircraft, also belongs to pioneering.This cover jacking system is less demanding to outside jack, even aircraft jack-up function also can be realized in relatively simple and crude outfield in condition, and can be for a long time, frequent repeated usage, reduced expense and the difficulty of aircraft flight-line service.
Technical scheme of the present invention is: a kind of aircraft jacking system, it is characterized in that, comprise jack gusseted 1, jack-up bulb 2, two joinies 3, pull bar 4 and wallboard bearings 5, jack gusseted 1 is to be the triangular structure of arc surface 6 on one side, at two straight flange position of intersecting point places of triangular structure side surface direction, processes an ears joint 7 and a stepped hole 8; Jack-up bulb 2 bottoms are hemispherical bulb 9 structures, end is stepped shaft 10 structures, the stepped shaft upper end diameter of axle is less than the lower end diameter of axle, the upper shaft end is processed with outside thread, it between bulb and stepped shaft, is disk 11, the plane of lower disk surface and bulb joins, and under upper surface and stepped shaft, transverse plane joins; Joint 3 comprises joint 12, hex-head nut 13, stop washer 14, bolt 15, packing ring 16, nut 17, joint one end is tubular structure, this tubular structure one end closure, above-mentioned closing end and monaural structure are joined, the monaural structural bolts is vertical with the axis of tubular structure by the axis in hole, tubular structure is external thread structure, and outside face has locking groove vertically; Hex-head nut and tubular structure outside thread screw; Pull bar 4 is the tubular structures of two ends with negative thread, and both ends have circular gap; Wallboard bearing 5 is the platy structure with curvature, and the back side one end of its base 18 arc surfaces is with ears joint 19;
The arc surface of the arc surface of jack gusseted 1 and wallboard bearing 5 all is fixed on the fuselage sidewall, pull bar 4 two ends are connected with the tubular structure of joint 12 respectively, the monaural joint of two joints 12 is connected with the ears joint of jack gusseted 1 and the ears joint of wallboard bearing 5 by bolt 15 respectively, the stepped shaft free-running fit of the stepped hole of jack gusseted 1 and jack-up bulb 2, stepped shaft length is greater than the degree of depth of stepped hole, screw and tighten in stepped shaft upper end exposed portions serve with nut, jack-up bulb 2 and jack gusseted 1 are fastenedly connected, guarantee that the stepped shaft axis is perpendicular to the ground.
Described jack gusseted 1 edge is edge strip, and middle part is web, has lightening hole on web.
Described stepped shaft and disk end face are hollow structure.
Described disk end face peripheral surface is processed with attachment face.
Described jack gusseted 1, jack-up bulb 2, pull bar 4, wallboard bearing 5 and joint 6 add structure for machine.
The jack gusseted adopts integrated machine to add the truss structure formed, arc surface 6 and the laminating of fuselage sidewall, and connect with bolt; On another cusp, machine adds ears joint 7, is used for being connected with pull bar, increases its course stability; Also leave stepped hole 8 herein, be used for connecting the jack-up bulb.
The jack-up bulb adopts high-intensity 300M steel to process.Lower end disc 11, process two planes, can fix this part with instrument, is convenient to install.Be a cavity in this part, increased the quenching degree of steel part, alleviated structural weight, and little for the strength character impact.
Joint is comprised of joint 12, hex-head nut 13, stop washer 14, bolt 15, packing ring 15, nut 17.
Joint 12 adopts 30CrMnSiA to be processed into, and an end machining screw is in order to cylinder lever connecting rod.Joint is hollow structure, and the quenching degree of reinforcing material significantly alleviates pts wt.
Hex-head nut 13 adopts 30CrMnSiA to be processed into, inboard machining screw.
Stop washer 14 adopts 30CrMnSiA to be processed into.
Pull bar is processed into tubular structure by the steel bar, and the two ends machining screw is in order to the jointing assembly.
The wallboard bearing adopts aluminium alloy thick plate material machine to add and forms, and wherein base 18 and the laminating of fuselage sidewall, in order to fixing brace bar, increase the course stability of structure.After ears joint 19 is pressed into lining, with joint, be connected.
The arc surface of jack gusseted 1 and wallboard bearing 5 all is fixed on the fuselage sidewall, at first pull bar 4 two ends are connected with joint 3, then be connected with jack gusseted 1, wallboard bearing 5 respectively by bolt, jack-up bulb 2 finally is installed on jack gusseted 1.
The invention has the beneficial effects as follows: the present invention has lighter weight, large load can be delivered to fast to other structural advantages of fuselage.
1. existing aircraft supporting construction is generally used for and supports middle-size and small-size aircraft, and the present invention is the supporting construction for large transport airplane, and it is pioneering that the domestic supporting construction for large aircraft also belongs to;
2. structural weight of the present invention is 60Kg, can carry and transmit the load of 130t, is a kind of light structures, thereby has reduced cost;
3. 130 tons of load coming from jack transmission, can be diffused on aircraft sidewall, lower wall construction by fast speed by supporting construction, avoided stress to concentrate, and has good mechanical characteristic;
The present invention can be for a long time, repeated usage.
5. part of the present invention, processing technology is simple, is convenient to realize.
The accompanying drawing explanation
Fig. 1 is jack gusseted structural representation
Fig. 2 is jack-up ball head structure schematic diagram
Fig. 3 is the joint module structure schematic diagram
Fig. 4 is the joint design schematic diagram
Fig. 5 is the hex-head nut structural representation
Fig. 6 is the stop washer structural representation
Fig. 7 is the Tiebar structure schematic diagram
Fig. 8 is wallboard seat structure schematic diagram
Fig. 9 is the high aircraft jack-up structural representation that carries of lightweight
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
A kind of aircraft jacking system, it is characterized in that, comprise jack gusseted 1, jack-up bulb 2, two joinies 3, pull bar 4 and wallboard bearings 5, jack gusseted 1 is to be the triangular structure of arc surface 6 on one side, at two straight flange position of intersecting point places of triangular structure side surface direction, processes an ears joint 7 and a stepped hole 8; Jack-up bulb 2 bottoms are hemispherical bulb 9 structures, end is stepped shaft 10 structures, the stepped shaft upper end diameter of axle is less than the lower end diameter of axle, the upper shaft end is processed with outside thread, it between bulb and stepped shaft, is disk 11, the plane of lower disk surface and bulb joins, and under upper surface and stepped shaft, transverse plane joins; Joint 3 comprises joint 12, hex-head nut 13, stop washer 14, bolt 15, packing ring 16, nut 17, joint one end is tubular structure, this tubular structure one end closure, above-mentioned closing end and monaural structure are joined, the monaural structural bolts is vertical with the axis of tubular structure by the axis in hole, tubular structure is external thread structure, and outside face has locking groove vertically; Hex-head nut and tubular structure outside thread screw; Pull bar 4 is the tubular structures of two ends with negative thread, and both ends have circular gap; Wallboard bearing 5 is the platy structure with curvature, and the back side one end of its base 18 arc surfaces is with ears joint 19;
The arc surface of the arc surface of jack gusseted 1 and wallboard bearing 5 all is fixed on the fuselage sidewall, pull bar 4 two ends are connected with the tubular structure of joint 12 respectively, the monaural joint of two joints 12 is connected with the ears joint of jack gusseted 1 and the ears joint of wallboard bearing 5 by bolt 15 respectively, the stepped shaft free-running fit of the stepped hole of jack gusseted 1 and jack-up bulb 2, stepped shaft length is greater than the degree of depth of stepped hole, screw and tighten in stepped shaft upper end exposed portions serve with nut, jack-up bulb 2 and jack gusseted 1 are fastenedly connected, guarantee that the stepped shaft axis is perpendicular to the ground.
Described jack gusseted 1 edge is edge strip, and middle part is web, has lightening hole on web.
Described stepped shaft and disk end face are hollow structure.
Described disk end face peripheral surface is processed with attachment face.
Described jack gusseted 1, jack-up bulb 2, pull bar 4, wallboard bearing 5 and joint 6 add structure for machine.
The jack gusseted adopts integrated machine to add the truss structure formed, arc surface 6 and the laminating of fuselage sidewall, and connect with bolt; On another cusp, machine adds ears joint 7, is used for being connected with pull bar, increases its course stability; Also leave stepped hole 8 herein, be used for connecting the jack-up bulb.
The jack-up bulb adopts high-intensity 300M steel to process.Lower end disc 11, process two planes, can fix this part with instrument, is convenient to install.Be a cavity in this part, increased the quenching degree of steel part, alleviated structural weight, and little for the strength character impact.
Joint is comprised of joint 12, hex-head nut 13, stop washer 14, bolt 15, packing ring 15, nut 17.
Joint 12 adopts 30CrMnSiA to be processed into, and an end machining screw is in order to cylinder lever connecting rod.Joint is hollow structure, and the quenching degree of reinforcing material significantly alleviates pts wt.
Hex-head nut 13 adopts 30CrMnSiA to be processed into, inboard machining screw.
Stop washer 14 adopts 30CrMnSiA to be processed into.
Pull bar is processed into tubular structure by the steel bar, and the two ends machining screw is in order to the jointing assembly.
The wallboard bearing adopts aluminium alloy thick plate material machine to add and forms, and wherein base 18 and the laminating of fuselage sidewall, in order to fixing brace bar, increase the course stability of structure.After ears joint 19 is pressed into lining, with joint, be connected.
The arc surface of jack gusseted 1 and wallboard bearing 5 all is fixed on the fuselage sidewall, at first pull bar 4 two ends are connected with joint 3, then be connected with jack gusseted 1, wallboard bearing 5 respectively by bolt, jack-up bulb 2 finally is installed on jack gusseted 1.
Participate in Fig. 9, the high aircraft jack-up structure of carrying of lightweight of the present invention, be comprised of jack gusseted 1, jack-up bulb 2, joint 3, pull bar 4, wallboard bearing 5.During installation, first, by the arc surface of jack gusseted 1 and wallboard bearing 5, all be secured by bolts on the fuselage sidewall.The threaded end of joint 3 is screwed to the two ends of pull bar 4, forms a complete rod assembly.Be pressed into lining respectively on the ears joint of jack gusseted 1, wallboard bearing 5 after, the bolt that the rod assembly assembled is passed through to two Φ 20 is connected with jack gusseted 1, wallboard bearing 5 respectively.Jack-up bulb 2 finally is installed on jack gusseted 1, is used for being used in conjunction with jack, as the strong point of jack-up aircraft.
Claims (5)
1. an aircraft jacking system, it is characterized in that, comprise jack gusseted [1], jack-up bulb [2], two joinies [3], pull bar [4] and wallboard bearing [5], jack gusseted [1] is to be the triangular structure of arc surface [6] on one side, at two straight flange position of intersecting point places of triangular structure side surface direction, processes an ears joint [7] and a stepped hole [8]; Jack-up bulb [2] bottom is hemispherical bulb [9] structure, end is stepped shaft [10] structure, the stepped shaft upper end diameter of axle is less than the lower end diameter of axle, the upper shaft end is processed with outside thread, it between bulb and stepped shaft, is disk [11], the plane of lower disk surface and bulb joins, and under upper surface and stepped shaft, transverse plane joins; Joint [3] comprises joint [12], hex-head nut [13], stop washer [14], bolt [15], packing ring [16], nut [17], joint one end is tubular structure, this tubular structure one end closure, above-mentioned closing end and monaural structure are joined, the monaural structural bolts is vertical with the axis of tubular structure by the axis in hole, tubular structure is external thread structure, and outside face has locking groove vertically; Hex-head nut and tubular structure outside thread screw; Pull bar [4] is the tubular structures of two ends with negative thread, and both ends have circular gap; Wallboard bearing [5] is the platy structure with curvature, and the back side one end of its base [18] arc surface is with ears joint [19];
The arc surface of the arc surface of jack gusseted [1] and wallboard bearing [5] all is fixed on the fuselage sidewall, pull bar [4] two ends are connected with the tubular structure of joint [12] respectively, the monaural joint of two joints [12] is connected with the ears joint of wallboard bearing [5] with the ears joint of jack gusseted [1] by bolt [15] respectively, the stepped shaft free-running fit of the stepped hole of jack gusseted [1] and jack-up bulb [2], stepped shaft length is greater than the degree of depth of stepped hole, screw and tighten in stepped shaft upper end exposed portions serve with nut, jack-up bulb [2] and jack gusseted [1] are fastenedly connected, guarantee that the stepped shaft axis is perpendicular to the ground.
2. aircraft jacking system according to claim 1, is characterized in that, described jack gusseted [1] edge is edge strip, and middle part is web, has lightening hole on web.
3. aircraft jacking system according to claim 1, is characterized in that, described stepped shaft and disk end face are hollow structure.
4. aircraft jacking system according to claim 1, is characterized in that, described disk end face peripheral surface is processed with attachment face.
5. aircraft jacking system according to claim 1, is characterized in that, described jack gusseted [1], jack-up bulb [2], pull bar [4], wallboard bearing [5] and joint [6] add structure for machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310374394.2A CN103466496B (en) | 2013-08-23 | 2013-08-23 | A kind of aircraft jack-up device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310374394.2A CN103466496B (en) | 2013-08-23 | 2013-08-23 | A kind of aircraft jack-up device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103466496A true CN103466496A (en) | 2013-12-25 |
| CN103466496B CN103466496B (en) | 2016-06-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310374394.2A Active CN103466496B (en) | 2013-08-23 | 2013-08-23 | A kind of aircraft jack-up device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950550A (en) * | 2014-04-28 | 2014-07-30 | 山东太古飞机工程有限公司 | Tool for supporting and protecting end parts of aircraft wings |
| CN109305382A (en) * | 2018-10-17 | 2019-02-05 | 江西洪都航空工业集团有限责任公司 | Tie-down point and jacking bracket structure on a kind of aircraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2240724A (en) * | 1940-05-29 | 1941-05-06 | Weaver Mfg Co | Airplane jack and supporting system |
| US2335692A (en) * | 1943-01-30 | 1943-11-30 | Thomas W Murray | Supporting table and jack |
| US5232203A (en) * | 1992-07-27 | 1993-08-03 | Butts Bobbie C | Jack for light aircraft |
| RU2067543C1 (en) * | 1992-04-14 | 1996-10-10 | Акционерное общество открытого типа "Таганрогская авиация" | Device for assembly of flying vehicle units |
| FR2757131A1 (en) * | 1996-12-12 | 1998-06-19 | Gabes Andre | Mobile adjustable platform for working around tail assemblies of large aircraft. |
| DE10328925B3 (en) * | 2003-06-26 | 2004-10-28 | Techman-Head Germany Gmbh | Three-point jack, for use with helicopters during maintenance and repair, has a telescopic lifting cylinder supported on three swing legs with safety locks in a compact structure giving a high lifting height with stability |
| EP1785350A2 (en) * | 2005-11-15 | 2007-05-16 | The Boeing Company | Apparatus for manipulating heavy loads |
| CN202116234U (en) * | 2011-05-17 | 2012-01-18 | 陕西鸿鼎机电科技有限公司 | Airplane lifting-up device |
-
2013
- 2013-08-23 CN CN201310374394.2A patent/CN103466496B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2240724A (en) * | 1940-05-29 | 1941-05-06 | Weaver Mfg Co | Airplane jack and supporting system |
| US2335692A (en) * | 1943-01-30 | 1943-11-30 | Thomas W Murray | Supporting table and jack |
| RU2067543C1 (en) * | 1992-04-14 | 1996-10-10 | Акционерное общество открытого типа "Таганрогская авиация" | Device for assembly of flying vehicle units |
| US5232203A (en) * | 1992-07-27 | 1993-08-03 | Butts Bobbie C | Jack for light aircraft |
| FR2757131A1 (en) * | 1996-12-12 | 1998-06-19 | Gabes Andre | Mobile adjustable platform for working around tail assemblies of large aircraft. |
| DE10328925B3 (en) * | 2003-06-26 | 2004-10-28 | Techman-Head Germany Gmbh | Three-point jack, for use with helicopters during maintenance and repair, has a telescopic lifting cylinder supported on three swing legs with safety locks in a compact structure giving a high lifting height with stability |
| EP1785350A2 (en) * | 2005-11-15 | 2007-05-16 | The Boeing Company | Apparatus for manipulating heavy loads |
| CN202116234U (en) * | 2011-05-17 | 2012-01-18 | 陕西鸿鼎机电科技有限公司 | Airplane lifting-up device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950550A (en) * | 2014-04-28 | 2014-07-30 | 山东太古飞机工程有限公司 | Tool for supporting and protecting end parts of aircraft wings |
| CN109305382A (en) * | 2018-10-17 | 2019-02-05 | 江西洪都航空工业集团有限责任公司 | Tie-down point and jacking bracket structure on a kind of aircraft |
| CN109305382B (en) * | 2018-10-17 | 2022-06-03 | 江西洪都航空工业集团有限责任公司 | Mooring joint and jack support structure on airplane |
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| Publication number | Publication date |
|---|---|
| CN103466496B (en) | 2016-06-01 |
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