CN112407309A - External hanging structure of aircraft wing - Google Patents
External hanging structure of aircraft wing Download PDFInfo
- Publication number
- CN112407309A CN112407309A CN202011209943.7A CN202011209943A CN112407309A CN 112407309 A CN112407309 A CN 112407309A CN 202011209943 A CN202011209943 A CN 202011209943A CN 112407309 A CN112407309 A CN 112407309A
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- wing
- hanging
- cable
- tooth
- clamp plate
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- 238000000034 method Methods 0.000 abstract description 13
- 238000005516 engineering process Methods 0.000 abstract description 2
- 239000000725 suspension Substances 0.000 description 11
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 239000003973 paint Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The invention belongs to the technology of hanging aerial geophysical prospecting cables, and relates to an external hanging structure for an airplane wing. The method comprises the following steps: the aircraft comprises a connecting rod assembly, a hanging cabin body, a wing fixed joint and a hanging fixed joint, wherein the connecting rod assembly comprises a plurality of connecting rods, one end of each connecting rod is fixedly connected with the corresponding wing through the wing fixed joint, the other end of each connecting rod is fixedly connected with the hanging cabin body through the hanging fixed joint, and the angles of the connecting rods can be adjusted. The invention adopts the connection modes of fixing the rod system and the cable clamp plate, effectively controls the weight of the external hanging single side of the wing, and realizes the operation requirement of manual handling of personnel. In addition, the aerodynamic loads generated by the external hanging of the wings are effectively reduced through the connection of the rod systems, and the difficulty in airplane refitting operation is reduced.
Description
Technical Field
The invention belongs to the technology of hanging aerial geophysical prospecting cables, and relates to an external hanging structure for an airplane wing.
Background
At present, the external hanging/nacelle structure applied to the wing tip of the wing in the field of aviation geophysical prospecting is less, and aviation geophysical prospecting equipment is mainly internally arranged in a wing tip nacelle or directly connected with the wing. The aircraft wing external hanging/nacelle structure is suitable for the structural composition of the aircraft wing external hanging/nacelle, two process methods of integral welding and composite material forming are adopted, and the gap compensation method is adopted for gap compensation adjustment in connection with the aircraft. However, although the hanging structure which is mainly made of steel materials and integrally formed by adopting a welding method and the full-composite nacelle structure which is mainly made of composite materials effectively control the structural weight, the aerodynamic resistance and the cost and the manufacturing cost, the welding process method, the structural strength, the using conditions and the like cannot meet the using requirements of the cable hanging of the aerial geophysical prospecting aircraft.
Disclosure of Invention
The purpose of the invention is as follows: the external wing hanging structure can be applied to time domain airplanes.
The technical scheme is as follows:
in a first aspect, an external hanging structure of an aircraft wing is provided, including: the aircraft comprises a connecting rod assembly, a hanging cabin body, a wing fixed joint and a hanging fixed joint, wherein the connecting rod assembly comprises a plurality of connecting rods, one end of each connecting rod is fixedly connected with the corresponding wing through the wing fixed joint, the other end of each connecting rod is fixedly connected with the hanging cabin body through the hanging fixed joint, and the angles of the connecting rods can be adjusted.
Furthermore, the wing fixed joint comprises a wing connecting surface and a single lug joint, the wing connecting surface is fixedly connected with the wing, a double lug joint is arranged at one end of the connecting rod, and one end of the connecting rod is fixedly connected with the wing fixed joint through a single-double lug structure.
Furthermore, the connecting rod comprises a pull rod and two screw rods with double-lug structures, wherein reverse internal threads are arranged on the inner walls of the two ends of the pull rod, and the two ends of the pull rod are respectively in threaded connection with the two screw rods with the double-lug structures.
The connecting rod further comprises a first tooth-shaped gasket, a second tooth-shaped gasket and a locking nut, wherein tooth-shaped structures matched with each other are arranged on the contact surfaces of the first tooth-shaped gasket and the second tooth-shaped gasket, a boss is arranged on the inner wall of the first tooth-shaped gasket, a groove is arranged on the outer surface of the screw rod with the double-lug structure, the first tooth-shaped gasket and the screw rod with the double-lug structure are relatively fixed through the matching of the boss and the groove, a boss is arranged on one side of the non-tooth-shaped structure of the second tooth-shaped gasket, a groove is arranged on the end face of the pull rod, the second tooth-shaped gasket and the pull rod are relatively fixed through the matching of the boss and the groove, and the locking nut presses the first tooth-shaped gasket.
Furthermore, lock wire holes are formed in the lock nut and the second toothed washer and used for fixing the pull rod and the screw rod with the double-lug structure relatively through the lock wires.
Further, hang the cabin body and include cable fixed splint and cable movable clamp plate, wherein all be provided with the arc recess on cable fixed splint and the cable movable clamp plate, the arc recess of cable fixed splint and cable movable clamp plate is used for the centre gripping cable relatively, and cable fixed splint and cable movable clamp plate pass through splint connecting bolt to connect fixedly.
Furthermore, the hanging cabin body further comprises a hanging upper fixed fairing and a hanging lower movable fairing, and the hanging upper fixed fairing and the hanging lower movable fairing are arranged on the outer sides of the fixed clamping plate and the cable movable clamping plate.
Further, the cable disassembling device further comprises auxiliary mounting bolts, and the auxiliary mounting bolts are used at the positions of the symmetrically distributed clamping plate connecting bolts in the process of disassembling and assembling the cable so as to facilitate disassembling the cable.
Has the advantages that: the invention adopts the connection modes of fixing the rod system and the cable clamp plate, effectively controls the weight of the external hanging single side of the wing to be not more than 30KG, and realizes the operation requirement of manual handling by personnel. In addition, the aerodynamic loads generated by the external hanging of the wings are effectively reduced through the connection of the rod systems, and the difficulty of airplane refitting operation is reduced by nearly 30%.
Drawings
FIG. 1 is a schematic view of an external hanging connection of a wing according to an embodiment of the invention;
FIG. 2 is a schematic view of an external hanging structure of a wing according to an embodiment of the invention;
FIG. 3 is a schematic view of the connection of the upper end of the linkage of the external wing suspension structure according to the embodiment of the invention;
FIG. 4 is a schematic view of the lower end connection of a linkage of an outboard wing suspension structure according to an embodiment of the invention;
FIG. 5 is an exploded view of the upper end structure of the spar system of the external wing suspension structure according to the embodiment of the invention;
FIG. 6 is an exploded view of the lower end structure of the spar system of the outboard pylon structure of an embodiment of the wing in accordance with the invention;
FIG. 7 is an exploded view of a cable suspension nacelle structure of an external wing suspension structure according to an embodiment of the invention;
FIG. 8 is an assembly diagram of a cable suspension nacelle structure of an external wing suspension structure according to an embodiment of the invention;
FIG. 9 is a schematic diagram of an anti-skid paint spraying area of a cable cleat of an external wing hanging structure according to an embodiment of the invention;
FIG. 10 is a schematic view of a hanging auxiliary mounting bolt connection of an outboard wing hanging structure according to an embodiment of the invention;
FIG. 11 is a cross-sectional view of a hanging auxiliary mounting bolt connection of an outboard wing suspension structure according to an embodiment of the invention.
The auxiliary mounting bolt comprises a wing 1, a wing 2, a cable 3, an external wing hanger 31, a wing fixed joint 32, a hanger fixed joint 33, a connecting rod assembly 34, a hanger cabin body 331, a connecting bolt 332, a right screw threaded joint 333, a right screw threaded locking nut 334, a first tooth-shaped washer 335, a pull rod 336, a left screw threaded locking nut 337, a left screw threaded joint 338, a second tooth-shaped washer 341, a hanger upper fixed fairing 342, a hanger lower movable fairing 343, a cable fixed clamp 344, a cable movable clamp 345, a reinforcing beam 346, a clamp plate connecting bolt 347 and an anti-skid paint 348.
Detailed Description
The time domain fixed wing aircraft is an aerial geophysical prospecting modified aircraft which is formed by coiling a cable along the head → the end parts of a left wing and a right wing → the tail of an aircraft body and is fixed outside the aircraft, and the cable is exposed outside the aircraft body, so that great additional aerodynamic resistance is generated on the aircraft. In addition, due to the heavy structure of the cable, the cable has great influence on the installation, fixation and turn number adjustment of the cable during the outfield flying. In the process of airplane modification, under the condition that the use performance of the airplane and the detection depth of the aerial geophysical prospecting are not influenced, the manufacturing cost of airplane modification is strictly controlled to obtain the maximum economic benefit.
In view of the above, the present invention contemplates: a) the aerodynamic resistance of the external hanging structure of the wing is effectively reduced, the lightweight design of the structure is realized, and the convenience of installation, disassembly and maintenance of the hanging structure is improved; b) the cable hanging and mounting reliability is guaranteed, and the use requirements such as controllability adjustment of the number of turns of the cable during the flying-holding period of the aircraft outfield are met; c) and the cost control requirement is strictly followed, and the use of an auxiliary positioning tool is reduced or avoided.
According to the embodiment of the invention, the external hanging structure of the airplane wing comprises: the aircraft comprises a connecting rod assembly, a hanging cabin body, a wing fixed joint and a hanging fixed joint, wherein the connecting rod assembly comprises a plurality of connecting rods, one end of each connecting rod is fixedly connected with the corresponding wing through the wing fixed joint, the other end of each connecting rod is fixedly connected with the hanging cabin body through the hanging fixed joint, and the angles of the connecting rods can be adjusted.
Furthermore, the wing fixed joint comprises a wing connecting surface and a single lug joint, the wing connecting surface is fixedly connected with the wing, a double lug joint is arranged at one end of the connecting rod, and one end of the connecting rod is fixedly connected with the wing fixed joint through a single-double lug structure.
Furthermore, the connecting rod comprises a pull rod and two screw rods with double-lug structures, wherein reverse internal threads are arranged on the inner walls of the two ends of the pull rod, and the two ends of the pull rod are respectively in threaded connection with the two screw rods with the double-lug structures.
The connecting rod further comprises a first tooth-shaped gasket, a second tooth-shaped gasket and a locking nut, wherein tooth-shaped structures matched with each other are arranged on the contact surfaces of the first tooth-shaped gasket and the second tooth-shaped gasket, a boss is arranged on the inner wall of the first tooth-shaped gasket, a groove is arranged on the outer surface of the screw rod with the double-lug structure, the first tooth-shaped gasket and the screw rod with the double-lug structure are relatively fixed through the matching of the boss and the groove, a boss is arranged on one side of the non-tooth-shaped structure of the second tooth-shaped gasket, a groove is arranged on the end face of the pull rod, the second tooth-shaped gasket and the pull rod are relatively fixed through the matching of the boss and the groove, and the locking nut presses the first tooth-shaped gasket.
Furthermore, lock wire holes are formed in the lock nut and the second toothed washer and used for fixing the pull rod and the screw rod with the double-lug structure relatively through the lock wires.
Further, hang the cabin body and include cable fixed splint and cable movable clamp plate, wherein all be provided with the arc recess on cable fixed splint and the cable movable clamp plate, the arc recess of cable fixed splint and cable movable clamp plate is used for the centre gripping cable relatively, and cable fixed splint and cable movable clamp plate pass through splint connecting bolt to connect fixedly.
Furthermore, the hanging cabin body further comprises a hanging upper fixed fairing and a hanging lower movable fairing, and the hanging upper fixed fairing and the hanging lower movable fairing are arranged on the outer sides of the fixed clamping plate and the cable movable clamping plate.
Further, the cable disassembling device further comprises auxiliary mounting bolts, and the auxiliary mounting bolts are used at the positions of the symmetrically distributed clamping plate connecting bolts in the process of disassembling and assembling the cable so as to facilitate disassembling the cable.
The following detailed description is made with reference to the accompanying drawings.
The invention adopts a rod system connection mode to realize the connection between the external wing hanger 3 and the wing 1, as shown in figure 1.
The outboard hangings 3 of the wings are composed of a connecting rod assembly 33, a hangar cabin 34, a wing fixed joint 31, a hangar fixed joint 32 and a matching fastener, as shown in fig. 2.
The connecting rod assembly 33 is connected to the wing fixing joint 31 and the hanging fixing joint 32 by using an insert lug joint, and the connecting bolt 331 is a hexagon bolt, as shown in fig. 3 and 4. All the connecting rods, the joints and the connecting bolts are exposed outside the machine body, so that the installation, the disassembly and the daily maintenance and inspection of the external hanging of the wing are facilitated.
The connecting rod assembly 33 is composed of a right-hand threaded joint 332, a right-hand threaded lock nut 333, a first tooth washer 334, a pull rod 335, a left-hand threaded lock nut 336, a left-hand threaded joint 337, and a second tooth washer 338, as shown in fig. 5 and 6. Wherein, the two ends of the pull rod are respectively connected with the left spiral thread joint and the right spiral thread joint by adopting left spiral pipe threads and right spiral pipe threads, so as to realize the end clearance compensation of the connecting rod component and the adjustment of the posture of the hanging cabin body. The left spiral thread locking nut, the right spiral thread locking nut, the first tooth-shaped washer and the second tooth-shaped washer are used for locking the pull rod to prevent the connecting rod assembly from loosening.
The nacelle 34 is composed of a suspended upper fixed cowl 341, a suspended lower movable cowl 342, a cable fixing clamp 343, a cable movable clamp 344, a reinforcing beam 345, and a clamp connection bolt 346, as shown in fig. 7.
A gap of 2 mm-3 mm is reserved between the cable fixing clamp plate and the cable movable clamp plate for compressing and fixing the cable, and anti-slip paint 347 is sprayed on the surface of a cable groove of the clamp plate to increase the friction force between the cable and the clamp plate and ensure that the cable cannot slide in the cable hanging cabin body, as shown in fig. 7, 8 and 9.
In order to improve the convenience of cable detachment and installation, ensure the controllability of the number of turns of the cable during the flying-off process at the outfield of the aircraft and avoid the use requirements of users such as the use of auxiliary fixture tools, the invention adopts the suspension auxiliary mounting bolt 348 connected with the movable clamping plate 344 for suspending the cable, as shown in fig. 10 and 11. The cable can be temporarily suspended from the cable movable clamp, and after the number of turns of the cable is adjusted and tightened, the clamp connection bolt 346 can be gradually tightened and the auxiliary suspension mounting bolt 348 can be removed.
The invention solves and realizes the following functions:
the invention adopts the connection modes of fixing the rod system and the cable clamp plate, realizes the requirements of low aerodynamic resistance and light structure, effectively controls the weight of the external hanging single side of the wing to be not more than 30KG, and realizes the operation requirement of manual handling of personnel. In addition, the connecting rod is connected through the rod system, and the end of the connecting rod is respectively connected with the lug inserting joint through two pipe threads of a left screw and a right screw, so that the requirements of hanging posture adjustment, clearance compensation adjustment and the like are met, the pneumatic load generated by external hanging of the wing is effectively reduced, and the difficulty of plane modification operation is reduced by nearly 30%. The method for regulating and controlling the mounting bolt by using the suspension assistance meets the use requirements of users on the dismounting and mounting convenience of the cable during the flying-holding period of the outfield of the airplane and the controllability and adjustment of the number of turns of the cable, such as avoiding the use of an auxiliary clamp tool and the like. The invention reasonably arranges the external hanging structure of the wing by a design method of 'product, namely tooling', realizes the aim of airplane modification by avoiding using an auxiliary positioning tooling for the external hanging of the wing, saves about 30 ten thousand of tooling cost for the airplane wing structure modification, and saves about 10 ten thousand of manufacturing cost for part manufacturing.
Claims (8)
1. The utility model provides an external suspended structure of aircraft wing which characterized in that includes: the aircraft comprises a connecting rod assembly, a hanging cabin body, a wing fixed joint and a hanging fixed joint, wherein the connecting rod assembly comprises a plurality of connecting rods, one end of each connecting rod is fixedly connected with the corresponding wing through the wing fixed joint, the other end of each connecting rod is fixedly connected with the hanging cabin body through the hanging fixed joint, and the angles of the connecting rods can be adjusted.
2. The structure of claim 1, wherein the wing fixing joint comprises a wing connecting surface and a single lug joint, the wing connecting surface is fixedly connected with the wing, a double lug joint is arranged at one end of the connecting rod, and the other end of the connecting rod is fixedly connected with the wing fixing joint through the single double lug structure.
3. The structure of claim 2, wherein the connecting rod comprises a pull rod and two screw rods with double-lug structures, wherein reverse internal threads are arranged on the inner walls of the two ends of the pull rod, and the two ends of the pull rod are respectively in threaded connection with the two screw rods with double-lug structures.
4. The structure of claim 3, wherein the connecting rod further comprises a first tooth-shaped washer, a second tooth-shaped washer and a locking nut, wherein the contact surfaces of the first tooth-shaped washer and the second tooth-shaped washer are provided with tooth-shaped structures which are matched with each other, the inner wall of the first tooth-shaped washer is provided with a boss, the outer surface of the screw rod with the double-lug structure is provided with a groove, the first tooth-shaped washer and the screw rod with the double-lug structure are relatively fixed through matching of the boss and the groove, one side of the non-tooth-shaped structure of the second tooth-shaped washer is provided with a boss, the end surface of the pull rod is provided with a groove, the second tooth-shaped washer and the pull rod are relatively fixed through matching of the boss and the groove, and the locking nut presses the first tooth-shaped washer and.
5. The structure of claim 4, wherein a lockwire hole is provided on the locknut and the second toothed washer for fixing the pull rod and the screw rod with the double-lug structure by the lockwire.
6. The structure of claim 1, wherein the hanging cabin comprises a cable fixing clamp plate and a cable movable clamp plate, wherein the cable fixing clamp plate and the cable movable clamp plate are provided with arc-shaped grooves, the arc-shaped grooves of the cable fixing clamp plate and the cable movable clamp plate are opposite to each other for clamping the cable, and the cable fixing clamp plate and the cable movable clamp plate are fixedly connected through a clamp plate connecting bolt.
7. The structure of claim 1, wherein the hanging nacelle further comprises a hanging upper fixed fairing and a hanging lower movable fairing, the hanging upper fixed fairing and the hanging lower movable fairing being disposed outside the fixed clamp plate and the cable movable clamp plate.
8. The structure of claim 1, further comprising auxiliary mounting bolts used at symmetrically distributed cleat attachment bolt locations to facilitate cable removal during cable removal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011209943.7A CN112407309A (en) | 2020-11-03 | 2020-11-03 | External hanging structure of aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011209943.7A CN112407309A (en) | 2020-11-03 | 2020-11-03 | External hanging structure of aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112407309A true CN112407309A (en) | 2021-02-26 |
Family
ID=74828296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011209943.7A Pending CN112407309A (en) | 2020-11-03 | 2020-11-03 | External hanging structure of aircraft wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112407309A (en) |
Citations (8)
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|---|---|---|---|---|
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| CN2419441Y (en) * | 1999-12-13 | 2001-02-14 | 常州市瞬通通讯器材有限公司 | Trunking clip |
| CN102392915A (en) * | 2011-11-04 | 2012-03-28 | 哈尔滨飞机工业集团有限责任公司 | Rack for aircraft wing externally-hung cable |
| US20130206914A1 (en) * | 2012-02-13 | 2013-08-15 | Fidelitad, Inc. | Sensor Pod Mount for an Aircraft |
| CN205538222U (en) * | 2016-01-13 | 2016-08-31 | 哈尔滨飞机工业集团有限责任公司 | Engine performance tester equipment fixing support |
| CN106828950A (en) * | 2016-12-09 | 2017-06-13 | 上海航空电器有限公司 | A kind of mounting structure of control board bracket |
| CN207157560U (en) * | 2017-05-03 | 2018-03-30 | 陕西飞机工业（集团）有限公司 | A kind of integral truss-type aircraft wing structure of hanging rack |
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-
2020
- 2020-11-03 CN CN202011209943.7A patent/CN112407309A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0972471A (en) * | 1995-09-07 | 1997-03-18 | Sekisui Chem Co Ltd | Coupling for corrugated pipe |
| CN2419441Y (en) * | 1999-12-13 | 2001-02-14 | 常州市瞬通通讯器材有限公司 | Trunking clip |
| CN102392915A (en) * | 2011-11-04 | 2012-03-28 | 哈尔滨飞机工业集团有限责任公司 | Rack for aircraft wing externally-hung cable |
| US20130206914A1 (en) * | 2012-02-13 | 2013-08-15 | Fidelitad, Inc. | Sensor Pod Mount for an Aircraft |
| CN205538222U (en) * | 2016-01-13 | 2016-08-31 | 哈尔滨飞机工业集团有限责任公司 | Engine performance tester equipment fixing support |
| CN106828950A (en) * | 2016-12-09 | 2017-06-13 | 上海航空电器有限公司 | A kind of mounting structure of control board bracket |
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| CN107975664A (en) * | 2017-11-16 | 2018-05-01 | 北京宇航系统工程研究所 | A kind of six-freedom parallel formula throttleable motor leverage stent and installation method |
Non-Patent Citations (1)
| Title |
|---|
| 付友波等: "机翼吊挂结构设计技术研究", 《现代制造技术与装备》 * |
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Application publication date: 20210226 |