CN111645851A - Embedded electrically-driven course stability-increasing type skid landing device and working method thereof - Google Patents
Embedded electrically-driven course stability-increasing type skid landing device and working method thereof Download PDFInfo
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- CN111645851A CN111645851A CN202010575837.4A CN202010575837A CN111645851A CN 111645851 A CN111645851 A CN 111645851A CN 202010575837 A CN202010575837 A CN 202010575837A CN 111645851 A CN111645851 A CN 111645851A
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 239000003638 chemical reducing agent Substances 0.000 claims description 17
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 230000006641 stabilisation Effects 0.000 claims description 4
- 238000011105 stabilization Methods 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 abstract description 6
- 230000008569 process Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000003416 augmentation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/52—Skis or runners
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Abstract
The invention discloses an embedded electrically-driven course stability-increasing type skid landing device and a working method thereof. When deviation occurs in the sliding direction of an aircraft, a system controls a brushless motor to drive a rocker arm connecting rod mechanism to press a friction plate down a road surface to generate pressure, so that the binding force between a unilateral landing device and the road surface is changed, the airframe is subjected to yawing moment, the sliding direction of the aircraft is corrected, the sliding course stability of the aircraft is enhanced, a load sensor can measure the pressure of the friction plate on the road surface and provide feedback, the friction plate is made of a heat-resistant composite material, and specific lines are machined at the bottom of the friction plate to provide additional lateral force and reduce the tail-flicking phenomenon of the aircraft.
Description
Technical Field
The invention relates to the technical field of running and landing of hypersonic flight vehicles, in particular to an embedded electrically-driven course stabilization type skid landing device and a working method thereof.
Background
The landing gear mainly comprises a wheel type landing gear and a skid type landing gear, the traditional aircraft mainly adopts the wheel type landing gear, landing is stable, sliding is easy, and the problems of complex structure, heavy weight, large occupied space and the like exist. The skid landing gear has the advantages of simple structure, light weight, low cost, reliable performance and small occupied space. For some hypersonic aircraft models, in order to reduce the design limit of the landing gear on the retraction space and the structural weight, a skid type landing gear is also adopted, and the skid and the road surface are subjected to deceleration braking through friction. U.S. X-15A used skid landing and trial flight verification. However, for a hypersonic aircraft landing by using a skid landing gear, the direction of a traditional skid landing gear is unstable, and the like, and in part of published patents of the skid landing gear, the problems of incompact mechanism, poor course stability and the like exist, and most of the prior art rely on the actuation of a hydraulic system, and compared with an electric landing gear system which replaces a hydraulic system by an electric power system, the all-electric landing gear has advantages in many aspects, and the all-electric course stability-increasing type skid landing gear has a great research value.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an embedded electrically-driven course stabilization increasing type skid landing device and a working method thereof aiming at the requirement of landing stability of a hypersonic aircraft landing by using the skid landing device.
The technical scheme adopted by the invention is as follows: an embedded electrically-driven course stability-increasing type skid landing device comprises an outer cylinder, an upper torsion arm, a lower torsion arm, a support, a skid, a guide wheel, an upper end cover, a piston rod, a rocker arm, an installation plate, a friction plate, a load sensor, a buffer, a skid pitching buffer and an actuator cylinder module;
the upper end of the piston rod is coaxially connected with the outer barrel, and the piston rod is arranged in the outer barrel in a sliding manner;
the upper torsion arm is hinged with the outer cylinder, the lower torsion arm is hinged with the piston rod, and the upper torsion arm is hinged with the lower torsion arm;
the support is connected with the lower end of the piston rod, two sides of the middle part of the skid are hinged with the lower part of the support, and the support 4 provides pitching freedom for the skid so as to adapt to different road surface conditions;
the guide wheels are fixedly arranged at two ends of the rear part of the skid;
two ends of the skid pitching buffer are respectively hinged with the support and the skid;
the skid pitching buffer comprises a skid pitching buffer piston rod and a skid pitching buffer outer barrel, the skid pitching buffer outer barrel is hinged with the skid, the skid pitching buffer piston rod is coaxially connected with the skid pitching buffer outer barrel, the skid pitching buffer piston rod is arranged in the skid pitching buffer outer barrel in a sliding mode, and the skid pitching buffer piston rod is hinged with the support;
the upper end cover is fixedly arranged at the upper end of the outer barrel;
the upper end of the rocker arm is hinged with the support, and the mounting plate is hinged with the lower end of the rocker arm;
the upper surface of the friction plate is fixedly connected with the lower surface of the mounting plate through screws;
the actuating cylinder module is integrated in the piston rod, so that the space can be saved;
the load sensor is fixedly arranged in the outer cylinder, the upper end load sensor comprises a first load sensor and a second load sensor, the first load sensor is fixedly arranged on the buffer, the buffer is fixedly arranged between the first load sensor and the actuating cylinder module, and the second load sensor is arranged on the actuating cylinder module;
the actuating cylinder module comprises a brushless motor, a speed reducer, a coupler, a screw rod limiting slide rail, a nut sleeve, a screw rod and a thimble;
the brushless motor and the speed reducer are both fixed in the piston rod;
the speed reducer is connected with the brushless motor;
the second load sensor is fixed on the brushless motor;
the shaft coupling is connected with an output shaft of the speed reducer and the screw rod, and the screw rod converts the rotary motion output by the speed reducer into linear motion through the shaft coupling;
the nut sleeve is mounted on the screw rod;
the ejector pin is connected to the lower end of the nut sleeve and is positioned outside the screw rod;
the screw rod limiting slide rail is fixedly arranged in the piston rod and is positioned outside the thimble;
the lower end of the thimble is hinged with a connecting rod, and the lower end of the connecting rod is hinged with the middle part of the rocker arm;
the actuating cylinder module controls the mounting plate and the friction plate to put down or put up through the rocker arm and the connecting rod, and controls the pressure of the friction plate pressing down the road surface according to the yaw degree of the aircraft and the feedback of the load sensor.
Furthermore, the friction plate is made of heat-resistant composite materials, specific lines are machined at the bottom of the friction plate, lateral force in the sliding process is increased, and the tail of the aircraft is prevented from drifting during deviation rectification.
The invention also discloses a working method of the embedded electrically-driven course stability-increasing type skid landing device, which comprises the following processes:
landing the aircraft, enabling the skid to contact the road surface, buffering through the skid pitching buffer, and braking the aircraft in a sliding way; if the aircraft runs in the correct direction, the brushless motor is not started, the friction plate is kept at the upper position and is separated from the road surface, when the aircraft runs in the correct direction, the brushless motor rotates, the actuating cylinder module presses the friction plate down to the road surface through the rocker arm to generate pressure, so that the binding force between the single-side landing device and the road surface is changed, the airframe is subjected to yawing moment, the running direction of the aircraft is corrected, and the heat-resistant composite material friction plate with specific grains at the bottom can provide extra lateral force to reduce the tail flicking phenomenon of the aircraft.
The invention with the structure has the following beneficial effects:
(1) compared with a skid landing device of a traditional hypersonic aircraft, the invention provides the embedded electrically-driven course stability augmentation landing device, which can correct the sliding direction of the aircraft and enhance the course stability of the landing sliding of the aircraft;
(2) compared with a skid landing device of a traditional hypersonic aircraft, the skid landing device has the advantages that the pressure of the friction plate and the road surface is controllable, and the sliding deceleration rate of the aircraft can be controlled;
(3) compared with the traditional skid landing device of the hypersonic aircraft, the skid landing device of the hypersonic aircraft adopts the heat-resistant composite friction plate with special lines, provides extra lateral force when the friction plate is put down, and can prevent the aircraft from drifting when the deviation is corrected.
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 view of the overall structure of the present invention;
FIG. 2 is a schematic view of the internal structure of the present invention;
fig. 3 is a schematic view of the actuator module of the present invention;
FIG. 4 is a schematic structural view of a thimble of the actuator cylinder module of the present invention;
FIG. 5 is a schematic view of the construction of the nut socket and lead screw of the actuator module of the present invention;
FIG. 6 is a schematic view of the structure of the skid of the present invention;
FIG. 7 is a schematic view of a friction plate of the present invention;
FIG. 8 is a schematic view of the friction plate according to the present invention in an operating state.
The device comprises a main body, an outer cylinder, a main body, an upper torsion arm, a lower torsion arm, a support, a skid, a guide wheel, a mounting plate, a friction plate, a load sensor, a buffer, a brushless motor, a speed reducer, a coupling, a coupler, a lead screw limiting slide rail, a nut sleeve, a lead screw, a thimble, a connecting rod, a piston rod, a rocker arm, a guide wheel, a piston rod, a rocker arm, a mounting plate, a friction plate, a load sensor, a buffer, a 16, a brushless motor, a.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; 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.
It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.
An embedded electrically-driven course stability-increasing type skid landing device comprises an outer cylinder 1, an upper torsion arm 2, a lower torsion arm 3, a support 4, a skid 5, a guide wheel 6, an upper end cover 9, a piston rod 10, a rocker arm 11, an installation plate 12, a friction plate 13, a load sensor 14, a buffer 15, a skid pitching buffer and an actuator cylinder module;
as shown in fig. 1 and 6, the upper end of the piston rod 10 is coaxially connected with the outer cylinder 1, and the piston rod 10 is slidably disposed in the outer cylinder 1; the upper torsion arm 2 is hinged with the outer cylinder 1, the lower torsion arm 3 is hinged with the piston rod 10, and the upper torsion arm 2 is hinged with the lower torsion arm 3; the support 4 is connected with the lower end of the piston rod 10, two sides of the middle part of the skid 5 are hinged with the lower part of the support 4, and the support 4 provides pitching freedom for the skid 5 so as to adapt to different road surface conditions; the guide wheels 6 are fixedly arranged at two ends of the rear part of the skid 5 and are used for being in contact with the sliding rails when the landing gear is folded to be in an upper position, so that the skid 5 rotates and is close to the piston rod 10 to reduce the folding and unfolding space; two ends of the skid pitching buffer are respectively hinged with the support 4 and the skid 5; the skid pitching buffer comprises a skid pitching buffer piston rod 7 and a skid pitching buffer outer cylinder 8, the skid pitching buffer outer cylinder 8 is hinged with the skid 5, the skid pitching buffer piston rod 7 is coaxially connected with the skid pitching buffer outer cylinder 8, the skid pitching buffer piston rod 7 is slidably arranged in the skid pitching buffer outer cylinder 8, and the skid pitching buffer piston rod 7 is hinged with the support 4; the upper end cover 9 is fixedly arranged at the upper end of the outer cylinder 1 and is used for fixing the outer cylinder 1 and internal devices of the buffer 15; the upper end of the rocker arm 11 is hinged with the support 4, and the mounting plate 12 is hinged with the lower end of the rocker arm 11; the upper surface of the friction plate 13 is fixedly connected with the lower surface of the mounting plate 12 through screws; the actuator cylinder module is integrated inside the piston rod 10, which saves space.
As shown in fig. 2, the load sensor 14, the buffer 15 and the actuator module are disposed at the upper end of the piston rod 10 and inside the outer cylinder 1, the load sensor 14 is fixedly disposed in the outer cylinder 1, the upper end load sensor 14 includes a first load sensor and a second load sensor, the first load sensor is fixed on the buffer 15, the buffer 15 is fixedly disposed between the first load sensor and the actuator module to absorb energy generated by impact when the aircraft lands, the second load sensor is disposed on the actuator module, and the two load sensors 14 respectively collect vertical loads applied to the skid 5 and the friction mechanism.
As shown in fig. 3-5, the actuator cylinder module includes a brushless motor 16, a reducer 17, a coupling 18, a screw rod limiting slide rail 19, a nut sleeve 20, a screw rod 21 and a thimble 22; the brushless motor 16 is fixed in the piston rod 10 and is controlled by an aircraft system to be used as a deviation rectifying drive; the speed reducer 17 is fixed in the piston rod 10, connected with the brushless motor 16 and used for reducing the output rotating speed of the brushless motor 16; the upper end of the coupling 18 is connected with the output shaft of the reducer 17, and the lower end is connected with the screw rod 21; the screw rod 21 is connected with the speed reducer 17 through a coupler 18, and the rotary motion output by the speed reducer 17 is converted into linear motion; the upper part of the nut sleeve 20 is connected with the screw rod 21, and the lower part of the nut sleeve 20 is connected with the thimble 22; the upper end of the thimble 22 is fixed on the screw rod 21, and the lower end is hinged with the connecting rod 23 to drive the connecting rod 23 mechanism of the rocker 11; the screw rod limits the slide rail 19 to limit the rotation of the nut sleeve 20, and the rotation motion is ensured to be converted into linear motion; the brushless motor 16, the speed reducer 17, the coupling 18, the screw 21, the nut sleeve 20, the thimble 22 and the screw limiting slide rail 19 are integrated in the piston rod 10, so that the space is further saved.
As shown in fig. 7 and 8, the upper end of the connecting rod 23 is hinged with the thimble 22, and the lower end of the connecting rod 23 is hinged with the rocker arm 11; the friction plate 13 is fixed on the mounting plate 12 through screws and is convenient to replace after being worn, and the friction plate 13 is made of heat-resistant composite materials with specific grains processed at the bottom, so that the lateral force in the sliding process is increased, and the tail flicking of the aircraft during deviation correction is prevented.
As shown in fig. 7 and 8, when the embedded electrically-driven course stabilization type skid landing device works, an aircraft lands, a skid 5 contacts a road surface, buffering and sliding braking are performed through a skid pitching buffer 15, if the sliding direction of the aircraft is correct, a brushless motor 16 is not started, and a friction plate 13 is kept at an upper position and is separated from the road surface. When the sliding direction of the aircraft deviates, the brushless motor 16 rotates, the actuator cylinder module presses the friction plate 13 down the road surface through the rocker arm 11 to generate pressure, so that the binding force between the single-side landing device and the road surface is changed, the airframe is subjected to yawing moment, the sliding direction of the aircraft is corrected, the heat-resistant composite friction plate 13 with specific lines at the bottom can provide additional lateral force, and the tail-flicking phenomenon of the aircraft is reduced.
When the landing and running course of the aircraft is correct, the friction plate 13 mechanism is kept at the upper position, as shown in fig. 7, and when the course is deviated, the actuator cylinder module drives the thimble 22 to press down, and the friction plate 13 is pressed down to the road surface through the rocker arm 11 and connecting rod 23 mechanism to generate pressure, as shown in fig. 8.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (3)
1. An embedded electrically-driven course stability-increasing type skid landing device is characterized by comprising an outer cylinder, an upper torsion arm, a lower torsion arm, a support, a skid, a guide wheel, an upper end cover, a piston rod, a rocker arm, a mounting plate, a friction plate, a load sensor, a buffer, a skid pitching buffer and an actuator cylinder module;
the upper end of the piston rod is coaxially connected with the outer barrel, and the piston rod is arranged in the outer barrel in a sliding manner;
the upper torsion arm is hinged with the outer cylinder, the lower torsion arm is hinged with the piston rod, and the upper torsion arm is hinged with the lower torsion arm;
the support is connected with the lower end of the piston rod, and two sides of the middle part of the skid are hinged with the lower part of the support;
the guide wheels are fixedly arranged at two ends of the rear part of the skid;
two ends of the skid pitching buffer are respectively hinged with the support and the skid;
the skid pitching buffer comprises a skid pitching buffer piston rod and a skid pitching buffer outer barrel, the skid pitching buffer outer barrel is hinged with the skid, the skid pitching buffer piston rod is coaxially connected with the skid pitching buffer outer barrel, the skid pitching buffer piston rod is arranged in the skid pitching buffer outer barrel in a sliding mode, and the skid pitching buffer piston rod is hinged with the support;
the upper end cover is fixedly arranged at the upper end of the outer barrel;
the upper end of the rocker arm is hinged with the support, and the mounting plate is hinged with the lower end of the rocker arm;
the upper surface of the friction plate is fixedly connected with the lower surface of the mounting plate through screws;
the actuating cylinder module is integrated inside the piston rod;
the load sensor is fixedly arranged in the outer cylinder, the upper end load sensor comprises a first load sensor and a second load sensor, the first load sensor is fixedly arranged on the buffer, the buffer is fixedly arranged between the first load sensor and the actuating cylinder module, and the second load sensor is arranged on the actuating cylinder module;
the actuating cylinder module comprises a brushless motor, a speed reducer, a coupler, a screw rod limiting slide rail, a nut sleeve, a screw rod and a thimble;
the brushless motor and the speed reducer are both fixed in the piston rod;
the speed reducer is connected with the brushless motor;
the second load sensor is fixed on the brushless motor;
the shaft coupling is connected with an output shaft of the speed reducer and the screw rod, and the screw rod converts the rotary motion output by the speed reducer into linear motion through the shaft coupling;
the nut sleeve is mounted on the screw rod;
the ejector pin is connected to the lower end of the nut sleeve and is positioned outside the screw rod;
the screw rod limiting slide rail is fixedly arranged in the piston rod and is positioned outside the thimble;
the lower end of the ejector pin is hinged with a connecting rod, and the lower end of the connecting rod is hinged with the middle of the rocker arm.
2. The embedded electrically driven course stabilization ski landing gear of claim 1, wherein the friction plate is a heat resistant composite material.
3. A working method of an embedded electrically-driven course stability-increasing type skid landing device is characterized by comprising the following steps:
landing the aircraft, enabling the skid to contact the road surface, buffering through the skid pitching buffer, and braking the aircraft in a sliding way; if the aircraft runs in the correct direction, the brushless motor is not started, the friction plate is kept at the upper position and is separated from the road surface, when the aircraft runs in the correct direction, the brushless motor rotates, the actuating cylinder module presses the friction plate down to the road surface through the rocker arm to generate pressure, so that the binding force between the single-side landing device and the road surface is changed, the airframe is subjected to yawing moment, the running direction of the aircraft is corrected, and the heat-resistant composite material friction plate with specific grains at the bottom can provide extra lateral force to reduce the tail flicking phenomenon of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010575837.4A CN111645851A (en) | 2020-06-22 | 2020-06-22 | Embedded electrically-driven course stability-increasing type skid landing device and working method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010575837.4A CN111645851A (en) | 2020-06-22 | 2020-06-22 | Embedded electrically-driven course stability-increasing type skid landing device and working method thereof |
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| CN111645851A true CN111645851A (en) | 2020-09-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010575837.4A Pending CN111645851A (en) | 2020-06-22 | 2020-06-22 | Embedded electrically-driven course stability-increasing type skid landing device and working method thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722251A (en) * | 2021-01-19 | 2021-04-30 | 南京航空航天大学 | Multi-stage buffering anti-crosswind skid landing device and working method thereof |
| CN113008779A (en) * | 2021-03-24 | 2021-06-22 | 南京航空航天大学 | Friction test device and friction test method |
-
2020
- 2020-06-22 CN CN202010575837.4A patent/CN111645851A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722251A (en) * | 2021-01-19 | 2021-04-30 | 南京航空航天大学 | Multi-stage buffering anti-crosswind skid landing device and working method thereof |
| CN112722251B (en) * | 2021-01-19 | 2022-03-22 | 南京航空航天大学 | Multi-stage buffering anti-crosswind skid landing device and working method thereof |
| CN113008779A (en) * | 2021-03-24 | 2021-06-22 | 南京航空航天大学 | Friction test device and friction test method |
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