CN107600392B - Retractable truss-supported landing gear - Google Patents
Retractable truss-supported landing gear Download PDFInfo
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- CN107600392B CN107600392B CN201710806914.0A CN201710806914A CN107600392B CN 107600392 B CN107600392 B CN 107600392B CN 201710806914 A CN201710806914 A CN 201710806914A CN 107600392 B CN107600392 B CN 107600392B
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Abstract
The invention relates to the technical field of airplane structure design, and particularly provides a retractable truss support type undercarriage which comprises a front fixing part, a rear fixing part, a fixing support, a driving part and a transmission part, wherein the front fixing part is used for providing support for the front part of the undercarriage, the rear fixing part is used for providing support for the rear part of the undercarriage, the front end of the fixing support is hinged with the front fixing part through a front pin shaft, the rear end of the fixing support is hinged with the rear fixing part through a rear pin shaft, the driving part is used for providing thrust and tension, the transmission part comprises a pull rod A and a pull rod B, one end of the pull rod A is hinged with the fixing support, the other end of the pull rod A is hinged with one end of the pull rod B, the middle of the pull rod A is hinged with one end of the driving part, the other end of the pull rod B is hinged with a.
Description
Technical Field
The invention relates to the technical field of aircraft structure design, in particular to a retractable truss-supported undercarriage.
Background
The existing small aircraft generally adopts a strut type undercarriage or a rocker arm type undercarriage, and all large parts of the undercarriage participate in the retraction and extension processes when the undercarriage is retracted and extended, so that a large retraction actuator cylinder is needed, and the undercarriage has complex force transmission and large weight.
Disclosure of Invention
In order to overcome at least one of the above-mentioned drawbacks of the prior art, the present invention provides a retractable truss-supported undercarriage, wheels of which are connected by wheel rocker arms, the truss-supported undercarriage comprising:
the front fixing part is connected with the fuselage and is used for providing support for the front part of the landing gear;
the rear fixing part is connected with the fuselage and is used for providing support for the rear part of the landing gear;
the front end of the fixed support is provided with a front pin shaft, the front pin shaft is hinged with the fixed support, the fixed support is connected with the front fixed part through the front pin shaft, the rear end of the fixed support is provided with a rear pin shaft, the rear pin shaft is hinged with the fixed support, and the fixed support is connected with the rear fixed part through the rear pin shaft;
the driving part is hinged with the machine body at one end and is used for providing pushing force and pulling force;
the transmission part comprises a pull rod A and a pull rod B, one end of the pull rod A is hinged with the fixed support, the other end of the pull rod A is hinged with one end of the pull rod B, the middle of the pull rod A is hinged with the other end of the driving part, the airplane wheel rocker arm is provided with a lug, and the other end of the pull rod B is hinged with the lug; wherein,
be equipped with the lantern ring on the wheel rocking arm, the lantern ring is articulated through back round pin axle and fixed bolster, and the lantern ring is located the outside of fixed bolster rear end, produces thrust or pulling force and acts on transmission portion through drive division, and then makes the wheel pack up or emit.
Preferably, the front fixing part includes:
one end of the front connecting rod A is hinged with the machine body, the other end of the front connecting rod A is hinged with the front pin shaft, and a convex block is arranged at one end of the front connecting rod A, which is hinged with the front pin shaft;
one end of the front connecting rod B is hinged with the machine body, and the other end of the front connecting rod B is hinged with the convex block of the front connecting rod A.
Preferably, the front link a and the front link B are both perpendicular to the fuselage axis.
Preferably, the device also comprises a front support rod for bearing the course load, wherein one end of the front support rod is hinged with the machine body, the hinged position is a first hinged position, the hinged position of the front connecting rod A and the machine body is a second hinged position, the hinged position of the front connecting rod B and the machine body is a third hinged position, and the first hinged position is far away from the fixed support relative to the second hinged position and the third hinged position;
one end of the front pin shaft, which is far away from the airplane wheel, is provided with a front lug, and the other end of the front stay bar is hinged with the front lug.
Preferably, a gap is formed between the front connecting rod A and the front pin shaft.
Preferably, the rear fixing part comprises a support frame which is in a U shape, the bending section of the support frame extends towards the machine body and is hinged with the machine body, two support legs of the support frame are hinged with a rear pin shaft, and the support legs are located on the outer side of the lantern ring.
Preferably, the rear support rod is used for bearing side loads, one end of the rear support rod is hinged with the machine body, a rear lug is arranged at one end, close to the machine body, of the rear pin shaft, and the other end of the rear support rod is hinged with the rear lug.
Preferably, the fixed bolster is the strip, and its front end and both sides are equipped with ascending leg, and preceding round pin axle is perpendicular to the connecting axle of wheel and runs through the leg of fixed bolster front end, and back round pin axle is on a parallel with the connecting axle of wheel and runs through the leg of fixed bolster both sides.
Preferably, the drive part is a ram.
Preferably, joint bearings are arranged between the front stay bar and the machine body, between the driving part and the machine body, between the front connecting rod A and the machine body, between the front connecting rod B and the machine body, between the supporting frame and the machine body and between the rear stay bar and the machine body.
The retractable truss support type undercarriage provided by the invention has the advantages that the undercarriage can be retracted in a limited space in the aircraft body in the flying process, the resistance is reduced, the flying performance is improved, the undercarriage has sufficient strength and rigidity, and better feasibility and reliability are realized.
Drawings
FIG. 1 is an isometric schematic view of a retractable truss-supported landing gear in a deployed condition;
FIG. 2 is a rear elevational schematic of the retractable truss-supported landing gear in the deployed condition;
FIG. 3 is a schematic view of the connection at the front pin;
FIG. 4 is a schematic view of the connection at the rear pin;
FIG. 5 is a schematic view showing the connection relationship between the front link A and the front link B;
FIG. 6 is a schematic elevational view of the retractable truss-supported landing gear in the retracted state;
figure 7 is a rear schematic view of the retractable truss-supported landing gear in the stowed condition.
Reference numerals: the airplane wheel connecting rod comprises a front connecting rod A11, a front connecting rod B12, a supporting frame 2, a fixed support 3, a front pin shaft 31, a rear pin shaft 32, a front lug 33, a rear lug 34, a driving part 4, a pull rod A51, a pull rod B52, a front support rod 61, a rear support rod 62, an airplane wheel 81, an airplane wheel rocker arm 82, a lug 83, a lantern ring 84 and an airplane body 9.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
It should be noted that: the embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are some embodiments of the present invention, not all embodiments, and features in embodiments and embodiments in the present application may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are used for convenience in describing the invention and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the scope of the invention.
Example A:
the invention provides a retractable truss support type undercarriage, a static structure is arranged between the whole undercarriage and an undercarriage body, the internal stress of structural installation can be reduced, and wheels 81 of the undercarriage are connected through wheel rocker arms 82 as shown in fig. 1 and 2, and the undercarriage comprises a front fixing part, a rear fixing part, a fixing support 3, a driving part 4 and a transmission part.
As shown in fig. 3 and 4, the front end of the fixing support 3 is provided with a front pin 31, the front pin 31 is hinged to the fixing support 3, the fixing support 3 is connected with the front fixing part through the front pin 31, the rear end of the fixing support 3 is provided with a rear pin 32, the rear pin 32 is hinged to the fixing support 3, the fixing support 3 is connected with the rear fixing part through the rear pin 32, in this embodiment, the fixing support 3 is in a strip shape, the front end and the two sides of the fixing support are provided with upward surrounding walls, the front pin 31 is perpendicular to the connecting shaft of the wheel 81 and penetrates through the surrounding walls at the front end of the fixing support 3, and the rear pin 32 is parallel to the connecting shaft of the wheel 81 and penetrates through the.
In the embodiment, as shown in fig. 5, the front fixing portion includes a front connecting rod a11 and a front connecting rod B12, one end of the front connecting rod a11 is hinged to the fuselage 9, the other end of the front connecting rod a11 is hinged to the front pin 31, one end of the front connecting rod a11 hinged to the front pin 31 is provided with a convex block, one end of the front connecting rod B12 is hinged to the fuselage 9, the other end of the front connecting rod a11 is hinged to the convex block, the front connecting rod a11 and the front connecting rod B12 form a triangular fixing surface, in the embodiment, the front connecting rod a11 and the front connecting rod B12 are both perpendicular to the axis of the fuselage 9, and joint bearings are arranged between the front connecting rod a11 and the fuselage and between the front connecting rod B12 and the fuselage to eliminate heading displacement caused by landing of the landing gear.
The rear fixing part is connected with the fuselage 9 and used for providing support for the rear part of the landing gear, in the embodiment, the rear fixing part comprises a support frame 2 which is U-shaped, the bending section of the support frame 2 extends towards the fuselage 9 and is hinged with the fuselage 9, two support legs of the support frame 2 are hinged with a rear pin shaft 32, the support legs are located on the outer side of the lantern ring 84, and preferably, a joint bearing is arranged between the support frame 2 and the fuselage to eliminate course displacement caused when the landing gear lands.
The driving part 4 is hinged to the body 9 at one end for providing a pushing force and a pulling force, in this embodiment, the driving part 4 is a ram, and in this embodiment, it is preferable that a joint bearing is provided between the driving part 4 and the body to eliminate the course displacement caused by landing of the landing gear.
The transmission part comprises a pull rod A51 and a pull rod B52, one end of the pull rod A51 is hinged with the fixed support 3, the other end of the pull rod A51 is hinged with one end of the pull rod B52, the middle of the pull rod A51 is hinged with the other end of the driving part 4, a lug 83 is arranged on the wheel rocker arm 82, and the other end of the pull rod B52 is hinged with the lug 83.
The wheel rocker arm 82 is provided with a lantern ring 84, the lantern ring 84 is hinged with the fixed support 3 through the rear pin shaft 32, the lantern ring 84 is located on the outer side of the rear end of the fixed support 3, a pushing force or a pulling force is generated through the driving portion 4 and acts on the transmission portion, and then the wheel 81 is retracted or released.
The working principle of the retractable truss-supported landing gear is as follows:
as shown in fig. 6 and 7, when the landing gear is in the extended state, when the landing gear needs to be retracted, the driving portion 4 applies a pulling force to the pull rod a, so that the pull rod a rotates around a hinge point of the pull rod a and the driving portion 4, the other end of the pull rod a is lifted along with the rotation and is away from the fixed bracket 3, the pull rod B52 is lifted along with the pull rod a, the pull rod B52 drives the wheel rocker 82 and enables the wheel rocker 82 to rotate around the rear pin shaft 32, and the wheel 81 is lifted and retracted.
In the retractable truss-supported landing gear, the front link a11, the front link B12, the support frame 2, the fixed bracket 3, the front stay 61, and the rear stay 62 all play a role in fixing and supporting, and the drive unit 4, the tie rod a51, and the tie rod B52 play a role in driving the landing gear to perform retraction.
Example B:
the invention also provides a retractable truss-supported landing gear, as shown in fig. 1 to 4, which has a partial structure similar to that of embodiment a, except that the retractable truss-supported landing gear further comprises a front stay 61 for bearing course load, one end of the front stay is hinged with the body 9, the hinged position is a first hinged position, the hinged position of the front link a11 and the body 9 is a second hinged position, the hinged position of the front link B12 and the body 9 is a third hinged position, and the first hinged position is far away from the fixed bracket 3 relative to the second hinged position and the third hinged position; one end of the front pin shaft 31, which is far away from the wheel 81, is provided with a front lug 33, and the other end of the front stay 61 is hinged with the front lug 33; preferably, in this embodiment, a knuckle bearing is provided between the front stay 61 and the fuselage to eliminate any directional displacement of the landing gear caused by landing.
The front link a11 has a clearance with the front pin 31 to allow the heading load to be transferred to the front stay 61 along the fixed bracket 3.
In this embodiment, the vehicle body structure further comprises a rear stay 62 for bearing a side load, wherein one end of the rear stay 62 is hinged to the vehicle body 9, one end of the rear pin shaft 32, which is close to the vehicle body 9, is provided with a rear lug 34, and the other end of the rear stay 62 is hinged to the rear lug 34; preferably, in this embodiment, a knuckle bearing is provided between the rear stay 62 and the fuselage to eliminate any directional displacement of the landing gear caused by landing.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (8)
1. A retractable truss-supported landing gear having wheels (81) connected by wheel rockers (82), comprising:
a forward fixed part connected to the fuselage (9) for providing support to the forward part of the landing gear;
a rear fixed part connected with the fuselage (9) and used for providing support for the rear part of the landing gear;
the front end of the fixed support (3) is provided with a front pin shaft (31), the front pin shaft (31) is hinged with the fixed support (3), the fixed support (3) is connected with the front fixed part through the front pin shaft (31), the rear end of the fixed support (3) is provided with a rear pin shaft (32), the rear pin shaft (32) is hinged with the fixed support (3), and the fixed support (3) is connected with the rear fixed part through the rear pin shaft (32);
the driving part (4) is hinged with the machine body (9) at one end and is used for providing pushing force and pulling force;
the transmission part comprises a pull rod A (51) and a pull rod B (52), one end of the pull rod A (51) is hinged with the fixed support (3), the other end of the pull rod A is hinged with one end of the pull rod B (52), the middle of the pull rod A (51) is hinged with the other end of the driving part (4), a lug piece (83) is arranged on the airplane wheel rocker arm (82), and the other end of the pull rod B (52) is hinged with the lug piece (83); wherein,
a lantern ring (84) is arranged on the wheel rocker arm (82), the lantern ring (84) is hinged with the fixed support (3) through a rear pin shaft (32), the lantern ring (84) is located on the outer side of the rear end of the fixed support (3), a pushing force or a pulling force is generated through the driving part (4) and acts on the transmission part, and then the wheel (81) is retracted or released; the front fixing portion includes:
one end of the front connecting rod A (11) is hinged with the machine body (9), the other end of the front connecting rod A (11) is hinged with the front pin shaft (31), and a convex block is arranged at one end of the front connecting rod A (11) hinged with the front pin shaft (31);
one end of the front connecting rod B (12) is hinged with the machine body (9), and the other end of the front connecting rod B is hinged with the convex block of the front connecting rod A (11);
knuckle bearings are arranged between the front stay bar (61) and the machine body, between the driving part (4) and the machine body, between the front connecting rod A (11) and the machine body, between the front connecting rod B (12) and the machine body, between the support frame (2) and the machine body and between the rear stay bar (62) and the machine body.
2. Truss-supported landing gear according to claim 1, wherein the forward link a (11) and the forward link B (12) are both perpendicular to the axis of the fuselage (9).
3. The truss-supported landing gear according to claim 2, further comprising a front stay (61) for carrying a heading load, one end of which is hinged to the fuselage (9), the hinged position being a first hinged position, the position in which the front link a (11) is hinged to the fuselage (9) being a second hinged position, the position in which the front link B (12) is hinged to the fuselage (9) being a third hinged position, the first hinged position being remote from the fixed bracket (3) with respect to the second and third hinged positions;
one end of the front pin shaft (31) far away from the wheel (81) is provided with a front lug (33), and the other end of the front stay bar (61) is hinged with the front lug (33).
4. The truss-supported landing gear of claim 3, wherein there is a gap between the forward link A (11) and the forward pin (31).
5. Truss-supported landing gear according to claim 1, wherein the rear fixing part comprises a support frame (2) which is U-shaped, the curved section of the support frame (2) extending in the direction of the fuselage (9) and being hinged to the fuselage (9), two legs of the support frame (2) being hinged to the rear pin (32), and said legs being located outside the collar (84).
6. The truss-supported landing gear of claim 1, further comprising a rear stay (62) for carrying side loads, one end of the rear stay being hinged to the fuselage (9), one end of the rear pin (32) adjacent to the fuselage (9) being provided with a rear lug (34), and the other end of the rear stay (62) being hinged to the rear lug (34).
7. Truss-supported landing gear according to claim 1, wherein the fixed support (3) is in the form of a bar, with upward perimeter walls at the front end and at both sides, the front pin (31) being perpendicular to the connecting shaft of the wheels (81) and extending through the perimeter walls at the front end of the fixed support (3), and the rear pin (32) being parallel to the connecting shaft of the wheels (81) and extending through the perimeter walls at both sides of the fixed support (3).
8. Truss-supported landing gear according to claim 1, wherein the drive part (4) is a ram.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710806914.0A CN107600392B (en) | 2017-09-08 | 2017-09-08 | Retractable truss-supported landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710806914.0A CN107600392B (en) | 2017-09-08 | 2017-09-08 | Retractable truss-supported landing gear |
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| Publication Number | Publication Date |
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| CN107600392A CN107600392A (en) | 2018-01-19 |
| CN107600392B true CN107600392B (en) | 2020-09-18 |
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| CN201710806914.0A Active CN107600392B (en) | 2017-09-08 | 2017-09-08 | Retractable truss-supported landing gear |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109835470B (en) * | 2019-02-22 | 2020-09-08 | 武汉科技大学 | Tilt cylinder driven aircraft landing gear |
| CN111409853B (en) * | 2020-04-12 | 2023-06-20 | 中国飞机强度研究所 | Landing gear strength test tire grounding point load applying structure |
| CN112644692A (en) * | 2020-12-29 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear down position locking device |
| CN115447764B (en) * | 2022-10-13 | 2024-09-06 | 中国航空工业集团公司西安飞机设计研究所 | Lifting rotating wheel type landing gear |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101481015A (en) * | 2009-02-27 | 2009-07-15 | 北京航空航天大学 | Small-sized foldable multi-wheel multi-column support type landing gear |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104210653A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Rocker arm landing gear |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2887517B1 (en) * | 2005-06-28 | 2008-09-12 | Airbus France Sas | STEERING DEVICE WITH REDUCED SIZE FOR AIRCRAFT LANDFILL |
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2017
- 2017-09-08 CN CN201710806914.0A patent/CN107600392B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101481015A (en) * | 2009-02-27 | 2009-07-15 | 北京航空航天大学 | Small-sized foldable multi-wheel multi-column support type landing gear |
| CN104210653A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Rocker arm landing gear |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
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| CN107600392A (en) | 2018-01-19 |
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