CN112623181A - Shuttle-shaped structure for aircraft - Google Patents
Shuttle-shaped structure for aircraft Download PDFInfo
- Publication number
- CN112623181A CN112623181A CN202011489607.2A CN202011489607A CN112623181A CN 112623181 A CN112623181 A CN 112623181A CN 202011489607 A CN202011489607 A CN 202011489607A CN 112623181 A CN112623181 A CN 112623181A
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- Prior art keywords
- fixed
- shuttle
- frame
- fixing
- outer side
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
Abstract
The invention discloses a shuttle-shaped structure for an aircraft, which comprises a shell, wherein fixed shafts are symmetrically arranged at the two ends of the outer side of the shell in a penetrating way, a shuttle-shaped inner frame is connected at the position corresponding to the outer side of the fixed shafts in the shell, placing threaded grooves are uniformly formed at the top end of the shuttle-shaped inner frame, a stabilizing top ring is arranged at the position corresponding to the placing threaded grooves at the top end of the shuttle-shaped inner frame, and placing screw rods are embedded and installed at the position corresponding to the placing threaded grooves at the top end of the stabilizing top ring. The convenience of the shuttle-shaped structure of the aircraft in use is improved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a shuttle-shaped structure for an aircraft.
Background
The aircraft is an apparatus flying in the atmosphere or the space outside the atmosphere, and the aircraft is divided into 3 types: the aircraft flying in the atmosphere is called as an aircraft, such as a balloon, an airship, an airplane and the like, flies by virtue of the static buoyancy of air or the aerodynamic force generated by the relative motion of air, and flies in space is called as an aircraft, such as an artificial earth satellite, a manned spacecraft, a space detector, a space plane and the like, and the aircraft, the spacecraft and the space detector obtain the necessary speed to enter the space under the driving of a carrier rocket and then make orbital motion similar to a celestial body by virtue of inertia;
however, when the existing shuttle-shaped aircraft structure is used, aircraft parts cannot be well fixed in the shuttle-shaped aircraft structure, and the shuttle-shaped aircraft structure needs to be customized according to the size and shape of the aircraft parts, so that the use of the shuttle-shaped aircraft structure is easily influenced.
Disclosure of Invention
The technical scheme provided by the invention can effectively solve the problems that the aircraft parts proposed in the background technology cannot be well fixed in the shuttle-shaped structure, and the shuttle-shaped structure needs to be customized according to the size and shape of the aircraft parts, so that the use of the shuttle-shaped structure of the aircraft is easily influenced.
In order to achieve the purpose, the invention provides the following technical scheme: a shuttle-shaped structure for an aircraft comprises a shell, wherein fixing shafts are symmetrically arranged at two ends of the outer side of the shell in a penetrating mode, and a shuttle-shaped inner frame is connected to the outer side of the fixing shafts in the shell;
the top end of the shuttle-shaped inner frame is provided with a stable placement mechanism, and the stable placement mechanism comprises a placement thread groove, a stable top ring, a placement screw, a fixed top frame, an adjusting screw, an adjusting pressing plate, a placement bottom frame, a clamping telescopic rod, a clamping spring and a clamping arc plate;
the top of fusiformis internal frame has evenly been seted up and has been placed the thread groove, the top of fusiformis internal frame corresponds places thread groove position department and installs and stabilize the apical ring, the top of stabilizing the apical ring corresponds places thread groove position department embedding and installs and place the screw rod, the inner wall connection of stabilizing the apical ring has fixed roof-rack, the top of fixed roof-rack is run through and is installed adjusting screw, adjusting screw's bottom is rotated and is installed the adjustment pressing plate, the inboard of fusiformis internal frame corresponds fixed roof-rack below position department and is connected with and places the chassis, the inboard of placing the chassis is connected with the centre gripping telescopic link, the centre gripping spring has been cup jointed in the outside of centre gripping telescopic link, the one end of centre gripping telescopic link is connected.
According to the technical characteristics, cotton pads are uniformly stuck on the outer side of the shuttle-shaped inner frame, and a gasket is stuck at the position, corresponding to the shuttle-shaped inner frame, of the bottom end of the stable top ring.
According to the technical characteristics, the bottom end of the placing screw rod penetrates through the stable top ring and is meshed with the placing thread groove, and the cushion is pasted at the bottom end of the adjusting pressing plate.
According to the technical characteristics, the adjusting screw is meshed with the fixed top frame, and the outer side of the clamping arc plate is sleeved with the anti-skid rubber sleeve.
According to the technical characteristics, convenient mounting mechanisms are mounted at the positions, corresponding to the fixed shafts, of the outer sides of the shells and at the connecting positions of the fixed shafts and the shuttle-shaped inner frames, and each convenient mounting mechanism comprises a fixed connecting seat, a fixing hole, a fixing bolt, an inner connecting seat, a connecting plate, a connecting bolt, a concave hole, a rotating connecting rod and a fixing block;
the outside of shell corresponds fixed axle position department embedding and installs fixed seat even, the outside of fixed axle corresponds fixed seat position department and has evenly seted up the fixed orifices even, fixed outside of seat even corresponds fixed orifices position department embedding and installs fixing bolt, the one end of fixed axle is connected with interior seat even, the one end fixed mounting of interior seat has the connecting plate even, connecting bolt is installed in the one end embedding of connecting plate, the shrinkage pool has evenly been seted up in the outside of interior seat even, the inboard of shrinkage pool is rotated and is installed and rotate the connecting rod, the outside of fusiform internal frame corresponds rotation connecting rod position department fixedly connected with fixed block.
According to the technical characteristics, one end of the fixing bolt penetrates through the fixing connecting seat to be in meshed connection with the fixing hole, and one end of the connecting bolt penetrates through the connecting plate to be in meshed connection with the other connecting plate.
According to the technical characteristics, one end of the rotating connecting rod is rotatably connected with the fixed block, and the inner wall of the concave hole is a smooth arc surface.
According to the technical characteristics, a convenient supporting mechanism is arranged at the lower position of the outer side of the shell and comprises a supporting block, a dismounting bolt, a fixing screw hole, a fixing arc plate, a supporting rod and a supporting gasket;
the supporting shoe is evenly installed to inboard below position department of shell, the one end embedding of supporting shoe is installed and is dismantled the bolt, the outside of shell corresponds dismantlement bolt position department and has seted up fixed screw, fixed arc board has been placed to the outside of shell corresponding fixed screw position department, the outside of fixed arc board evenly is connected with the bracing piece, the bottom of bracing piece is connected with the support gasket.
According to the technical characteristics, one end of the dismounting bolt penetrates through the supporting block and the fixed bolt to be meshed and connected with the fixed arc plate, and the outer side corners of the fixed arc plate are smooth round corners.
According to the technical characteristics, the number of the support rods is 12, and the bottom end surfaces of the support gaskets at the bottom ends of the 12 support rods are positioned on the same horizontal plane.
Compared with the prior art, the invention has the beneficial effects that: the invention has scientific and reasonable structure and safe and convenient use:
1. through the stable placement mechanism who sets up, can place aircraft spare part and placing the chassis top, use centre gripping telescopic link and centre gripping spring to carry out the centre gripping to the aircraft spare part of placing to will stabilize the apical ring and move down, press the aircraft spare part of placing, the centre gripping of the aircraft spare part of being convenient for is placed, has improved the stability when aircraft spare part is placed, has increased the convenience when this aircraft fusiformis structure uses.
2. Through the convenient installation mechanism that sets up, can carry out fixed mounting between fixed axle and the shell to can be through the rotation connecting rod of interior seat outside shrinkage pool internal rotation installation of company, when the shell appears rocking, make the stability of fusiformis internal frame holding position, reduce rocking that leads to fusiformis internal frame when the shell rocks, also be convenient for the dismantlement and the installation between fusiformis internal frame and the shell.
3. Through the convenient supporting mechanism who sets up, can install the bracing piece in the fixed arc board outside, carry out fixed mounting to fixed arc board, fix the position of bracing piece, can carry out the outrigger to the shell through bracing piece and supporting pad piece, the outrigger when being convenient for this aircraft fusiformis structure overhauls.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view showing a mounting structure of a fixing shaft and a shuttle-shaped inner frame according to the present invention;
FIG. 3 is a schematic structural view of the stabilizing placement mechanism of the present invention;
FIG. 4 is a schematic view of the installation structure of the placing chassis and the clamping telescopic rod of the present invention;
FIG. 5 is a schematic structural view of a convenient mounting mechanism of the present invention;
FIG. 6 is a schematic view of the installation structure of the rotating link and the fixing block according to the present invention;
FIG. 7 is a schematic structural view of a convenient support mechanism of the present invention;
reference numbers in the figures: 1. a housing; 2. a fixed shaft; 3. a shuttle-shaped inner frame;
4. a stable placement mechanism; 401. placing a thread groove; 402. a stabilizing top ring; 403. placing a screw rod; 404. fixing the top frame; 405. adjusting the screw rod; 406. adjusting the pressing plate; 407. placing the underframe; 408. clamping the telescopic rod; 409. a clamping spring; 410. clamping the arc plate;
5. a convenient installation mechanism; 501. fixing the connecting seat; 502. a fixing hole; 503. fixing the bolt; 504. an inner connecting seat; 505. a connecting plate; 506. a connecting bolt; 507. concave holes; 508. rotating the connecting rod; 509. a fixed block;
6. a convenient support mechanism; 601. a support block; 602. disassembling the bolt; 603. fixing screw holes; 604. fixing the arc plate; 605. a support bar; 606. and supporting the gasket.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Example (b): as shown in fig. 1-7, the invention provides a technical solution, a shuttle-shaped structure for an aircraft, comprising a housing 1, fixing shafts 2 symmetrically penetrate through two outer ends of the housing 1, and a shuttle-shaped inner frame 3 is connected to the inner part of the housing 1 corresponding to the outer side of the fixing shafts 2;
the top end of the shuttle-shaped inner frame 3 is provided with a stable placing mechanism 4, and the stable placing mechanism 4 comprises a placing thread groove 401, a stable top ring 402, a placing screw 403, a fixed top frame 404, an adjusting screw 405, an adjusting pressing plate 406, a placing bottom frame 407, a clamping telescopic rod 408, a clamping spring 409 and a clamping arc plate 410;
the top end of the fusiform inner frame 3 is uniformly provided with placing thread grooves 401, the top end of the fusiform inner frame 3 is provided with a stable top ring 402 corresponding to the position of the placing thread grooves 401, the top end of the stable top ring 402 is provided with a placing screw 403 corresponding to the position of the placing thread grooves 401 in an embedding manner, the inner wall of the stable top ring 402 is connected with a fixed top frame 404, the top end of the fixed top frame 404 is provided with an adjusting screw 405 in a penetrating manner, the bottom end of the adjusting screw 405 is provided with an adjusting pressing plate 406 in a rotating manner, the inner side of the fusiform inner frame 3 is connected with a placing bottom frame 407 corresponding to the lower position of the fixed top frame 404, the inner side of the placing bottom frame 407 is connected with a clamping telescopic rod 408, the outer side of the clamping telescopic rod 408 is sleeved with a clamping spring 409, one end of the clamping telescopic rod 408 is connected with a clamping arc plate, stability between stable apical ring 402 and the internal frame 3 of fusiformis has been increased, the bottom of placing screw rod 403 passes stable apical ring 402 and places the thread groove 401 between the meshing be connected, the bottom of adjustment press plate 406 is pasted and is had the cushion, increased adjustment press plate 406 and place the frictional force between the article, adjusting screw 405 and fixed roof-rack 404 between the meshing be connected, the antiskid rubber cover has been cup jointed in the outside of centre gripping arc board 410, the non-skid property of centre gripping arc board 410 has been improved.
A convenient mounting mechanism 5 is mounted at the position, corresponding to the fixed shaft 2, of the outer side of the shell 1 and at the joint of the fixed shaft 2 and the shuttle-shaped inner frame 3, and the convenient mounting mechanism 5 comprises a fixed connecting seat 501, a fixing hole 502, a fixing bolt 503, an inner connecting seat 504, a connecting plate 505, a connecting bolt 506, a concave hole 507, a rotating connecting rod 508 and a fixing block 509;
a fixed connecting seat 501 is embedded and installed at the position, corresponding to the fixed shaft 2, of the outer side of the shell 1, fixing holes 502 are uniformly formed at the position, corresponding to the fixed holes 501, of the outer side of the fixed shaft 2, fixing bolts 503 are embedded and installed at the position, corresponding to the fixing holes 502, of the outer side of the fixed connecting seat 501, one end of the fixed shaft 2 is connected with an inner connecting seat 504, one end of the inner connecting seat 504 is fixedly provided with a connecting plate 505, one end of the connecting plate 505 is embedded and installed with a connecting bolt 506, the outer side of the inner connecting seat 504 is uniformly provided with a concave hole 507, the inner side of the concave hole 507 is rotatably provided with a rotating connecting rod 508, the outer side of the fusiform inner frame 3 is fixedly connected with a fixing block 509 corresponding to the rotating connecting rod 508, one end of the fixing bolt 503 penetrates through the fixed connecting seat 501 to be connected with the fixing holes 502 in, one end of the rotating connecting rod 508 is rotatably connected with the fixed block 509, and the inner wall of the concave hole 507 is a smooth arc surface, so that the friction force between the rotating connecting rod 508 and the concave hole 507 is reduced.
A convenient supporting mechanism 6 is arranged at the lower position of the outer side of the shell 1, and the convenient supporting mechanism 6 comprises a supporting block 601, a dismounting bolt 602, a fixing screw hole 603, a fixing arc plate 604, a supporting rod 605 and a supporting gasket 606;
the supporting blocks 601 are uniformly installed at the lower position of the inner side of the shell 1, the dismounting bolts 602 are installed at one end of the supporting blocks 601 in an embedded mode, the fixing screw holes 603 are formed in the outer side of the shell 1 corresponding to the positions of the dismounting bolts 602, the fixing arc plate 604 is placed at the position of the outer side of the shell 1 corresponding to the position of the fixing screw holes 603, the supporting rods 605 are uniformly connected to the outer side of the fixing arc plate 604, the bottom end of each supporting rod 605 is connected with a supporting gasket 606, one end of each dismounting bolt 602 penetrates through the supporting blocks 601 and the fixing screw holes 603 to be connected with the fixing arc plate 604 in a meshed mode, the outer side corners of the fixing arc plate 604 are smooth fillets, the fixing arc plate 604, and the bottom end surfaces of the support gaskets 606 at the bottom ends of the 12 support rods 605 are positioned on the same horizontal plane, so that the support stability of the support rods 605 and the support gaskets 606 on the shell 1 is improved.
The working principle and the using process of the invention are as follows: when the shuttle-shaped structure for the aircraft is used, the screw 403 can be rotated firstly, the stabilizing top ring 402 is taken down from the top end of the shuttle-shaped inner frame 3, aircraft parts can be placed at the top end of the placing bottom frame 407, when the aircraft parts are placed at the top end of the placing bottom frame 407, the clamping arc plate 410 is contacted, the clamping telescopic rod 408 and the clamping spring 409 are driven to contract, rebounding through the clamping telescopic rod 408 and the clamping spring 409 to clamp the placed aircraft parts, then the adjusting screw 405 is rotated to drive the stabilizing top ring 402 to move downwards, the placed aircraft parts are pressed, the aircraft parts are conveniently clamped and placed, and the stability of the aircraft parts when placed is also improved;
when the shuttle-shaped structure of the aircraft is installed, the fixed shaft 2 can be plugged into the fixed connecting seat 501, the two connecting plates 505 are fixedly installed through the connecting bolts 506, then the fixed bolts 503 are rotated into the fixed holes 502, the fixed shaft 2 and the outer shell 1 can be fixedly installed, the rotating connecting rod 508 which is rotatably installed in the concave hole 507 on the outer side of the inner connecting seat 504 is used for keeping the position of the shuttle-shaped inner frame 3 stable through the rotating connecting rod 508 when the outer shell 1 shakes, the shaking of the shuttle-shaped inner frame 3 caused by the shaking of the outer shell 1 is reduced, and the disassembly and the installation between the shuttle-shaped inner frame 3 and the outer shell 1 are also convenient;
when the installation is dismantled to shell 1, can place fixed arc board 604 in the shell 1 outside, install bracing piece 605 in the fixed arc board 604 outside afterwards, the bolt 602 is dismantled in the rotating again, will dismantle in bolt 602 rotating to fixed arc board 604, can carry out fixed mounting to fixed arc board 604, and fix the position of bracing piece 605, can carry out the outrigger through bracing piece 605 and support gasket 606 to shell 1, the outrigger when being convenient for this aircraft fusiformis structure overhauls is with placing.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. Shuttle structure for aircraft, comprising an outer shell (1), characterized in that: the outer side of the outer shell (1) is symmetrically provided with a fixed shaft (2) in a penetrating way at two ends, and the inner part of the outer shell (1) corresponding to the outer side of the fixed shaft (2) is connected with a shuttle-shaped inner frame (3);
the top end of the shuttle-shaped inner frame (3) is provided with a stable placement mechanism (4), and the stable placement mechanism (4) comprises a placement thread groove (401), a stable top ring (402), a placement screw (403), a fixed top frame (404), an adjusting screw (405), an adjusting pressing plate (406), a placement bottom frame (407), a clamping telescopic rod (408), a clamping spring (409) and a clamping arc plate (410);
the top end of the shuttle-shaped inner frame (3) is uniformly provided with a placing thread groove (401), the top end of the shuttle-shaped inner frame (3) is provided with a stable top ring (402) corresponding to the placing thread groove (401), the top end of the stable top ring (402) is provided with a placing screw rod (403) corresponding to the placing thread groove (401) in an embedded manner, the inner wall of the stable top ring (402) is connected with a fixed top frame (404), the top end of the fixed top frame (404) is provided with an adjusting screw rod (405) in a penetrating manner, the bottom end of the adjusting screw rod (405) is rotatably provided with an adjusting pressing plate (406), the inner side of the shuttle-shaped inner frame (3) is connected with a placing bottom frame (407) corresponding to the lower position of the fixed top frame (404), the inner side of the placing bottom frame (408) is connected with a clamping telescopic rod (408), and the outer side of the, one end of the clamping telescopic rod (408) is connected with a clamping arc plate (410).
2. A shuttle structure for aircraft according to claim 1, characterised in that the outer side of the inner shuttle frame (3) is uniformly glued with cotton pads and the bottom end of the stabilizing top ring (402) is glued with gaskets at the position corresponding to the inner shuttle frame (3).
3. The shuttle structure for the aircraft according to claim 1, wherein the bottom end of the placing screw rod (403) passes through the meshing connection between the stable top ring (402) and the placing thread groove (401), and the bottom end of the adjusting and pressing plate (406) is adhered with a soft cushion.
4. Shuttle structure for aircraft according to claim 1, characterised in that said adjusting screw (405) is engaged with said fixed top frame (404), and said gripping arc plate (410) is sleeved on its outer side with an anti-slip rubber sleeve.
5. The shuttle structure for aircraft according to claim 1, wherein the outer side of the outer shell (1) corresponding to the position of the fixed shaft (2) and the connection of the fixed shaft (2) and the shuttle inner frame (3) are provided with convenient mounting mechanisms (5), and the convenient mounting mechanisms (5) comprise a fixed connecting seat (501), a fixed hole (502), a fixed bolt (503), an inner connecting seat (504), a connecting plate (505), a connecting bolt (506), a concave hole (507), a rotating connecting rod (508) and a fixed block (509);
the outside of shell (1) corresponds fixed axle (2) position department embedding and installs fixed seat (501) even, the outside of fixed axle (2) corresponds fixed seat (501) position department and evenly has seted up fixed orifices (502), the fixed outside of seat (501) corresponds fixed orifices (502) position department embedding and installs fixing bolt (503), the one end of fixed axle (2) is connected with interior seat (504), the one end fixed mounting of interior seat (504) has connecting plate (505), connecting bolt (506) are installed in the one end embedding of connecting plate (505), shrinkage pool (507) have evenly been seted up in the outside of interior seat (504), rotation connecting rod (508) are installed in the inboard rotation of shrinkage pool (507), the outside of fusiform internal frame (3) corresponds rotation connecting rod (508) position department fixedly connected with fixed block (509).
6. Shuttle structure for aircraft according to claim 5, characterised in that said fixing bolt (503) has one end passing through the engagement connection between the fixing attachment seat (501) and the fixing hole (502), and said connecting bolt (506) has one end passing through the engagement connection between the connecting plate (505) and the other connecting plate (505).
7. Shuttle for aircraft according to claim 5, characterised in that said rotating link (508) has one end connected in rotation to a fixed block (509), said recess (507) having an inner wall with a smooth curved surface.
8. The shuttle structure for the aircraft according to claim 1, wherein a convenient support mechanism (6) is installed at a position below the outer side of the outer shell (1), and the convenient support mechanism (6) comprises a support block (601), a detaching bolt (602), a fixing screw hole (603), a fixing arc plate (604), a support rod (605) and a support gasket (606);
supporting blocks (601) are evenly installed at the lower position of the inner side of the shell (1), a dismounting bolt (602) is installed in one end of the supporting blocks (601) in an embedded mode, a fixing screw hole (603) is formed in the position, corresponding to the dismounting bolt (602), of the outer side of the shell (1), a fixing arc plate (604) is placed in the position, corresponding to the fixing screw hole (603), of the outer side of the shell (1), a supporting rod (605) is evenly connected to the outer side of the fixing arc plate (604), and the bottom end of the supporting rod (605) is connected with a supporting gasket (606).
9. The shuttle structure for the aircraft according to claim 8, wherein one end of the dismounting bolt (602) passes through the supporting block (601) and the fixing screw hole (603) to be engaged and connected with the fixing arc plate (604), and the outer side corners of the fixing arc plate (604) are smooth and rounded.
10. Shuttle structure for aircraft according to claim 8, characterised in that said support rods (605) are 12 in number and that the bottom end faces of the support shims (606) at the bottom ends of the 12 support rods (605) are located in the same horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011489607.2A CN112623181B (en) | 2020-12-16 | 2020-12-16 | Shuttle-shaped structure for aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011489607.2A CN112623181B (en) | 2020-12-16 | 2020-12-16 | Shuttle-shaped structure for aircraft |
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| CN112623181A true CN112623181A (en) | 2021-04-09 |
| CN112623181B CN112623181B (en) | 2022-05-13 |
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| CN202011489607.2A Active CN112623181B (en) | 2020-12-16 | 2020-12-16 | Shuttle-shaped structure for aircraft |
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