CN217893214U - Landing support device for aircraft test flight - Google Patents
Landing support device for aircraft test flight Download PDFInfo
- Publication number
- CN217893214U CN217893214U CN202221044869.2U CN202221044869U CN217893214U CN 217893214 U CN217893214 U CN 217893214U CN 202221044869 U CN202221044869 U CN 202221044869U CN 217893214 U CN217893214 U CN 217893214U
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- base
- fixed
- connecting piece
- aircraft
- landing
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- 239000003381 stabilizer Substances 0.000 claims abstract description 11
- 238000009434 installation Methods 0.000 claims description 22
- 238000013016 damping Methods 0.000 claims description 13
- 230000010006 flight Effects 0.000 claims description 2
- 230000035939 shock Effects 0.000 claims description 2
- 239000006096 absorbing agent Substances 0.000 claims 1
- 230000003139 buffering effect Effects 0.000 abstract description 8
- 230000001681 protective effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft tries on to fly with strutting arrangement that falls, including base, mounting panel and stabilizer blade, the top of base is provided with the mounting panel, the bottom four corners position department of base all rotates and installs the stabilizer blade, the top fixed mounting of base has support ball festival pole, contact base has been placed in the outside of support ball festival pole, the even fixed mounting in the top outside of base has vertical buffer spring, the utility model has the advantages of being scientific and reasonable in structure, through the high-efficient buffer gear who sets up, be convenient for diversely cushion the descending of aircraft, reduce the loss that receives when the aircraft descends, increased the buffering protective properties when this landing strutting arrangement uses, through the adjustment fixed establishment who sets up, can carry out the rigidity to this landing strutting arrangement, the gliding phenomenon of position appears when avoiding this landing strutting arrangement to use, improved the stability when this landing strutting arrangement uses.
Description
Technical Field
The utility model relates to an aircraft auxiliary device technical field specifically is an aircraft is tried on flights and is used strutting arrangement that falls.
Background
The aircraft is the most applied in present aerial photography technique, but the aircraft often has certain inertial force when taking off and land, has caused certain harm to the flight, and the undercarriage shock-absorbing capacity of present aircraft is not good enough, and the engine compartment sets up the top in the cabin, and the focus of aircraft all is in the upper end of aircraft like this, though its mobility is good, but its structure is complicated, has just so improved the technical requirement and the material requirement that it made, and the degree of difficulty and the cost of operation and maintenance also greatly increased, in the chinese patent of patent No. 202122364412.1, specifically mentions a type aircraft undercarriage part takes precautions against earthquakes, the utility model discloses the device is when installing the aircraft, can reach the effect of quick installation, and fixed effectual convenient aircraft's normal use, when using, shock attenuation effect and protection effect when falling to the ground are good for the staff conveniently uses.
However, when the shockproof aircraft landing gear component is used, the buffering of the aircraft during landing is limited to the buffering in the vertical direction, the aircraft is easy to cause the inclined direction and the transverse impact force to the landing gear part during landing, so that the buffering effect of the aircraft during landing is poor, and the existing use requirements are difficult to meet.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft is tried to fly and is used landing support device to the buffering limitation when solving the aircraft that proposes among the above-mentioned background art and taking off and rise is cushioned in vertical direction, still causes incline direction and horizontal impact force to the undercarriage position easily when the aircraft plays to fall, and the buffering effect when consequently leading to the aircraft to take off and rise easily is not good, is difficult to satisfy current user demand's problem.
In order to achieve the above purpose, the utility model provides a following technical scheme: a landing and landing support device for test flight of an aircraft comprises a base, a mounting plate and support legs, wherein the mounting plate is arranged above the base, the support legs are rotatably mounted at four corners of the bottom end of the base, a high-efficiency buffer mechanism is mounted between the base and the mounting plate, and the high-efficiency buffer mechanism at least comprises a support ball joint rod, a connecting piece, a cross rod and a transverse buffer spring;
the top end of the base is provided with a supporting ball joint rod, a connecting piece is arranged below the base, cross rods are uniformly arranged on the outer sides of the connecting piece, and transverse buffer springs are arranged on the outer sides and one end of the cross rods;
the bottom end of the connecting piece is provided with an adjusting and fixing mechanism, and the adjusting and fixing mechanism at least comprises a supporting rod, a fixing cone, an installing sleeve and a supporting seat;
the supporting rod is arranged below the connecting piece, a fixed cone is arranged at the bottom end of the supporting rod, an installation sleeve is arranged on the outer side of the fixed cone, and a supporting seat is arranged on the outer side of the installation sleeve.
Preferably, the efficient buffer mechanism comprises a supporting ball joint rod, a contact seat, a vertical buffer spring, a guide wheel, a damping spring, a connecting piece, a cross rod and a transverse buffer spring;
a supporting ball joint rod is fixedly arranged at the top end of the base, a contact seat is arranged at the outer side of the supporting ball joint rod, vertical buffer springs are uniformly and fixedly arranged at the outer side of the top end of the base, guide wheels are arranged at the bottom ends of the support legs, the bottom of base is even fixed mounting has damping spring, damping spring's bottom fixed mounting has the connecting piece, the outside of stabilizer blade is rotated and is installed the horizontal pole, horizontal buffer spring is all installed in the one end and the outside of horizontal pole.
Preferably, the top end of the contact base is fixedly connected with the bottom end of the mounting plate, and the top end of the vertical buffer spring is fixedly connected with the bottom end of the mounting plate.
Preferably, the other end of the cross rod stays in the connecting piece, and the cross rod is connected with the connecting piece in a sliding mode.
Preferably, the adjusting and fixing mechanism comprises a fixed sleeve, a supporting rod, a fixed cone, an installation sleeve, a pushing handle and a supporting seat;
the bottom fixed mounting of connecting piece has fixed sleeve, the bracing piece has been placed to fixed sleeve's inboard, the bottom fixed mounting of bracing piece has fixed awl, the installation sleeve has been placed in the outside of fixed awl, the even fixedly connected with in fixed awl and the installation sheathed tube outside pushes away the handle, the supporting seat has been placed in the installation sheathed tube outside.
Preferably, the fixed cone and the mounting sleeve are fixed through bolts, and the mounting sleeve and the supporting seat are fixed through threads.
Compared with the prior art, the beneficial effects of the utility model are that:
1. through the high-efficient buffer gear who sets up, can descend the incline direction power on the mounting panel to the aircraft and cushion and absorb, also can use horizontal buffer spring to cushion horizontal power to can use damping spring to cushion vertical power, be convenient for diversely cushion the descending of aircraft, reduce the loss that receives when the aircraft descends, increased the buffering protective properties when this strutting arrangement uses.
2. Through the adjustment fixed establishment who sets up, can use the static friction on supporting seat and ground, carry out certain spacing to the base, also can carry out the rigidity to this strutting arrangement that rises and falls in the rotatory earth that gets into of fixed awl, the gliding phenomenon in position appears when avoiding this strutting arrangement that rises and falls to use, stability when having improved this strutting arrangement that rises and falls and using.
Drawings
The accompanying drawings 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 invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic view of the present invention;
fig. 2 is a schematic diagram of the explosion structure of the present invention;
FIG. 3 is a schematic structural view of the high-efficiency buffer mechanism of the present invention;
fig. 4 is a schematic structural view of the adjusting and fixing mechanism of the present invention;
in the drawings, the components represented by the respective reference numerals are listed below:
1. a base; 2. mounting a plate; 3. a support leg;
4. a high-efficiency buffer mechanism; 401. a support ball joint rod; 402. a contact base; 403. a vertical buffer spring; 404. a guide wheel; 405. a damping spring; 406. a connecting member; 407. a cross bar; 408. a lateral buffer spring;
5. adjusting the fixing mechanism; 501. fixing the sleeve; 502. a support bar; 503. a fixed cone; 504. installing a sleeve; 505. a push handle; 506. and (4) supporting the base.
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 presented herein only to illustrate and explain the present invention, and not to limit the present invention.
Example (b): as shown in fig. 1-4, the utility model provides a technical scheme, an aircraft is tried to fly and is used landing and landing strutting arrangement, including base 1, mounting panel 2 and stabilizer blade 3, the top of base 1 is provided with mounting panel 2, the bottom four corners position department of base 1 all rotates and installs stabilizer blade 3, install high-efficient buffer gear 4 between base 1 and the mounting panel 2, high-efficient buffer gear 4 includes support ball festival pole 401, contact base 402, vertical buffer spring 403, guide pulley 404, damping spring 405, connecting piece 406, horizontal pole 407 and horizontal buffer spring 408;
The bottom end of the connecting piece 406 is provided with an adjusting and fixing mechanism 5, and the adjusting and fixing mechanism 5 comprises a fixing sleeve 501, a supporting rod 502, a fixing cone 503, a mounting sleeve 504, a push handle 505 and a supporting seat 506;
fixed sleeve 501 is fixedly installed at the bottom end of connecting piece 406, bracing piece 502 has been placed to the inboard of fixed sleeve 501, the bottom end fixed mounting of bracing piece 502 has fixed awl 503, installation sleeve 504 has been placed to the outside of fixed awl 503, the even fixedly connected with in the outside of fixed awl 503 and installation sleeve 504 pushes away 505, supporting seat 506 has been placed in the outside of installation sleeve 504, fix through the bolt between fixed awl 503 and the installation sleeve 504, pass through threaded fixation between installation sleeve 504 and the supporting seat 506, be convenient for installation and dismantlement between supporting seat 506 and the installation sleeve 504.
The utility model discloses a theory of operation and use flow: when the landing and landing support device is used, after an aircraft falls on the mounting plate 2, the mounting plate 2 is stressed to generate angular deviation, the contact seat 402 at the bottom end of the mounting plate 2 and the support ball joint rod 401 are driven to rotate, the vertical buffer spring 403 at the bottom end of the mounting plate 2 is deformed, the force in the inclined direction of the aircraft landing on the mounting plate 2 can be buffered and absorbed, the landing force of the aircraft can be transmitted to the base 1, the supporting legs 3 are stressed to rotate with the base 1 and drive the guide wheels 404 to move, the supporting legs 3 rotate and drive the cross rods 407 to move transversely and vertically, when the cross rods 407 move transversely, the transverse buffer springs 408 can be driven to buffer the transverse force, when the cross rods 407 move vertically, the connecting pieces 406 can be driven to move vertically, the vertical force can be buffered by using the damping springs 405, so that the aircraft can be buffered efficiently when landing and the landing and landing of the aircraft can be buffered in multiple directions, the loss of the aircraft during landing and the buffering protection performance of the landing and landing protection device when the landing support device is used is increased;
when this supporting device rises and falls uses, can install supporting seat 506 in the installation sleeve pipe 504 outside, use supporting seat 506 and ground contact, and drive bracing piece 502 and remove along adapter sleeve 501, thereby use the static friction on supporting seat 506 and ground, carry out certain spacing to base 1, and can take off supporting seat 506 and installation sleeve pipe 504, promote again and push away 505, it is rotatory to drive fixed awl 503 and bracing piece 502, with fixed awl 503 rotatory entering earth, can be subaerial at earth, carry out the rigidity to this supporting device that rises and falls, the gliding phenomenon in position appears when avoiding this supporting device that rises and falls to use, stability when this supporting device that rises and falls uses has been improved.
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 modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. 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 (6)
1. The utility model provides an aircraft is tried on flights and is used landing support device, includes base (1), mounting panel (2) and stabilizer blade (3), the top of base (1) is provided with mounting panel (2), the bottom four corners position department of base (1) all rotates and installs stabilizer blade (3), its characterized in that: a high-efficiency buffer mechanism (4) is arranged between the base (1) and the mounting plate (2), and the high-efficiency buffer mechanism (4) at least comprises a supporting ball joint rod (401), a connecting piece (406), a cross rod (407) and a transverse buffer spring (408);
a supporting ball joint rod (401) is arranged at the top end of the base (1), a connecting piece (406) is arranged below the base (1), cross rods (407) are uniformly arranged on the outer sides of the connecting piece (406), and transverse buffer springs (408) are arranged on the outer sides and one end of the cross rods (407);
an adjusting and fixing mechanism (5) is installed at the bottom end of the connecting piece (406), and the adjusting and fixing mechanism (5) at least comprises a supporting rod (502), a fixing cone (503), an installation sleeve (504) and a supporting seat (506);
the supporting rod (502) is arranged below the connecting piece (406), the bottom end of the supporting rod (502) is provided with a fixed cone (503), the outer side of the fixed cone (503) is provided with an installation sleeve (504), and the outer side of the installation sleeve (504) is provided with a supporting seat (506).
2. A landing support device for aircraft test flight according to claim 1, wherein: the efficient buffer mechanism (4) comprises a supporting ball joint rod (401), a contact base (402), a vertical buffer spring (403), a guide wheel (404), a damping spring (405), a connecting piece (406), a cross rod (407) and a transverse buffer spring (408);
the utility model discloses a damping shock absorber, including base (1), guide pulley (404), the top fixed mounting of base (1) has support ball festival pole (401), contact base (402) have been placed in the outside of support ball festival pole (401), the even fixed mounting in the top outside of base (1) has vertical buffer spring (403), guide pulley (404) are installed to the bottom of stabilizer blade (3), the even fixed mounting in bottom of base (1) has damping spring (405), the bottom fixed mounting of damping spring (405) has connecting piece (406), the outside of stabilizer blade (3) is rotated and is installed horizontal pole (407), horizontal buffer spring (408) are all installed in the one end and the outside of horizontal pole (407).
3. A landing support device for aircraft test flight according to claim 2, wherein: the top of contact seat (402) and the bottom fixed connection of mounting panel (2), the top of vertical buffer spring (403) and the bottom fixed connection of mounting panel (2).
4. A landing support device for aircraft test flight according to claim 2, wherein: the other end of the cross rod (407) stays in the connecting piece (406), and the cross rod (407) is connected with the connecting piece (406) in a sliding mode.
5. A landing support device for aircraft test flight according to claim 2, wherein: the adjusting and fixing mechanism (5) comprises a fixing sleeve (501), a supporting rod (502), a fixing cone (503), an installation sleeve (504), a push handle (505) and a supporting seat (506);
the bottom fixed mounting of connecting piece (406) has fixed sleeve pipe (501), bracing piece (502) have been placed to the inboard of fixed sleeve pipe (501), the bottom fixed mounting of bracing piece (502) has fixed awl (503), install sleeve pipe (504) have been placed in the outside of fixed awl (503), the even fixedly connected with in the outside of fixed awl (503) and install sleeve pipe (504) pushes away handle (505), supporting seat (506) have been placed in the outside of install sleeve pipe (504).
6. A landing support device for aircraft test flight according to claim 5, wherein: the fixed cone (503) and the installation sleeve (504) are fixed through bolts, and the installation sleeve (504) and the support seat (506) are fixed through threads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221044869.2U CN217893214U (en) | 2022-04-29 | 2022-04-29 | Landing support device for aircraft test flight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221044869.2U CN217893214U (en) | 2022-04-29 | 2022-04-29 | Landing support device for aircraft test flight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217893214U true CN217893214U (en) | 2022-11-25 |
Family
ID=84110048
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221044869.2U Expired - Fee Related CN217893214U (en) | 2022-04-29 | 2022-04-29 | Landing support device for aircraft test flight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217893214U (en) |
-
2022
- 2022-04-29 CN CN202221044869.2U patent/CN217893214U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20221125 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |