Low-overload skid-type landing gear capable of actively increasing stability and control method of low-overload skid-type landing gear
By designing a low-overload skid-type landing gear with active stabilization, and utilizing the hydraulic control of the dynamic damper and torque arm assembly, the aircraft achieves landing cushioning and runway correction, solving the problems of insufficient cushioning and lack of correction in traditional skid-type landing gear, and is suitable for hypersonic aircraft.
Patent Information
- Application Number
- CN202511865471.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-11
- Publication Date
- 2026-01-16
AI Technical Summary
Traditional skid landing gear cannot provide effective cushioning, leading to increased landing overload on aircraft. At the same time, it lacks active correction capabilities and cannot cope with heading deviation problems.
A low-overload skid-type landing device with active stabilization was designed, including a landing gear outer cylinder, landing gear piston rod, rotary joint, skid assembly, dynamic damper and torque arm assembly. The device achieves buffer compression and taxiing correction through hydraulic control. The dynamic damper adjusts the pressure distribution of the skid on the ground during the taxiing phase to generate yaw torque for correction.
It effectively reduces the landing overload of the aircraft, ensures the stability of the landing process, and achieves active correction during the taxiing phase, reducing the space occupied by the device when it is retracted and improving the efficiency of internal space utilization.
Smart Images
Figure CN121341407A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of aircraft landing unloading and deviation correction, and particularly relates to a low-overload skid landing gear with active stability augmentation and a control method thereof. BACKGROUND
[0002] Traditional aircraft generally adopt wheel landing gears, which rely on the compressibility of tires to achieve one-stage buffering during landing, effectively reducing the landing overload of the aircraft. However, with the development of hypersonic aircraft, the requirements for aerodynamic shape are increasingly stringent, especially the flattened layout significantly limits the space for landing device retraction. The wheel landing gear has defects such as large volume, high weight and insufficient high-temperature resistance, and has been difficult to meet the design requirements of such aircraft. In contrast, the skid landing gear has unique advantages such as simple structure, light weight and excellent high-temperature resistance. However, the traditional skid landing gear also has obvious defects: on the one hand, it cannot provide effective buffering like the wheel landing gear, resulting in a significant increase in the landing overload of the aircraft; on the other hand, it lacks active deviation correction capability during the taxiing stage, and cannot cope with the heading deviation problem. Therefore, it is urgent to develop a skid landing gear with low-overload buffering and active taxiing deviation correction functions to fill the technical gap in this field. SUMMARY
[0003] The purpose of the present application is to provide a low-overload skid landing gear with active stability augmentation and a control method thereof, to solve the above technical problems existing in the prior art.
[0004] To achieve the above-mentioned purpose, the present application provides the following solution: a low-overload skid landing gear with active stability augmentation, comprising: a landing gear outer cylinder; a landing gear piston rod coaxial with the landing gear outer cylinder and axially elastically connected; a rotary joint hinged to the bottom end of the landing gear piston rod; a skid assembly comprising a first skid, a second skid and a skid connecting plate connected between the two, the skid connecting plate being hinged to the first skid and the second skid through a connecting pin shaft, allowing the first skid and the second skid to rotate within a certain angle range to adapt to uneven landing surfaces; a first dynamic buffer and a second dynamic buffer, the first dynamic buffer being connected to the rotary joint and the first skid, and the second dynamic buffer being connected to the rotary joint and the second skid.
[0005] Further, the low-overload skid landing gear with active stability augmentation further comprises a torsion arm group, the torsion arm group comprising an upper torsion arm, a lower torsion arm and a torsion arm pivot shaft, one end of the upper torsion arm being hinged to the landing gear outer cylinder, the other end being hinged to the upper end of the lower torsion arm through the torsion arm pivot shaft, and the lower end of the lower torsion arm being hinged to the landing gear piston rod.
[0006] Further, the torsion arm group is arranged on the front side or the rear side of the landing gear.
[0007] Further, the first power buffer and the second power buffer are of the same structure, each comprising a power buffer outer cylinder, a power buffer piston rod, and a second buffer device arranged in the power buffer outer cylinder.
[0008] Further, the second buffer device is a hydraulic buffer, and the power buffer outer cylinder is provided with an upper oil hole and a lower oil hole for connecting an external hydraulic system.
[0009] Further, the upper end of the power buffer outer cylinder of the first power buffer is hinged to the rotary joint, and the lower end of the power buffer piston rod of the first power buffer is hinged to the first skid; the upper end of the power buffer outer cylinder of the second power buffer is hinged to the rotary joint, and the lower end of the power buffer piston rod of the second power buffer is hinged to the second skid.
[0010] Further, the landing gear outer cylinder is provided with a first buffer device, and the first buffer device is in driving connection with the landing gear piston rod.
[0011] Further, the landing gear outer cylinder and the landing gear piston rod are made of high-strength titanium alloy material.
[0012] The application also provides a control method of the low-overload skid-type landing gear with active stability augmentation, comprising:
[0013] When the aircraft lands, the first power buffer and the second power buffer are compressed under the action of load, and at the same time, the landing gear piston rod is compressed under the action of load, thereby reducing the landing overload of the aircraft.
[0014] When the aircraft slides in a direction deviating from the intended direction, the first power buffer and / or the second power buffer on the corresponding side of the aircraft are controlled to extend, so as to increase the pressure of the skid assembly on the ground and generate a yawing moment to correct the sliding direction.
[0015] When the landing gear is retracted, the first power buffer and the second power buffer are controlled to retract, so as to drive the skid assembly to retract inwardly and reduce the storage space.
[0016] Compared with the prior art, the application at least has the following beneficial effects:
[0017] The low-overload skid type landing gear device with active stability enhancement designed by the application forms a stable buffer structure through the coaxial elastic connection of the landing gear outer cylinder and the landing gear piston rod, effectively absorbs and disperses the impact energy during landing, and significantly reduces the landing overload of the aircraft; the hinge design of the rotary joint and the skid assembly endows the device with flexible adaptability on uneven ground, ensuring the stability and reliability of the landing process; at the same time, the configuration of the first and second power buffers not only improves the overall shock absorption efficiency, but also uses hydraulic control to adjust the pressure distribution of the skid on the ground in real time, thereby generating a controllable yawing moment in the taxiing stage and realizing active correction of the aircraft heading; in addition, when the landing gear is retracted, the retraction action of the power buffer drives the skid assembly to fold inward, greatly reducing the occupied space of the device and improving the utilization efficiency of the internal space of the aircraft. BRIEF DESCRIPTION OF DRAWINGS
[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings described in the following only constitute some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.
[0019] Figure 1 It is the overall structural diagram of the low-overload skid type landing gear device with active stability enhancement of the embodiment of the present application.
[0020] Figure 2 It is the partial structural diagram of the low-overload skid type landing gear device with active stability enhancement of the embodiment of the present application.
[0021] Figure 3 It is the schematic diagram of the device in the retracted state of the embodiment of the present application.
[0022] Figure 4 It is the schematic diagram of the device in the non-compressed state of the power buffer when it is put down in the embodiment of the present application.
[0023] Figure 5 It is the schematic diagram of the device in the compressed state of the power buffer after landing in the embodiment of the present application.
[0024] In the figure: 1, landing gear outer cylinder; 2, landing gear piston rod; 3, upper torsion arm; 4, torsion arm rotating shaft; 5, lower torsion arm; 6, ear plate; 7, rotary joint; 8, first power buffer; 9, second power buffer; 10, skid connecting plate; 11, first skid; 12, second skid; 13, connecting pin; 14, hinge seat; 15, power buffer outer cylinder; 16, power buffer piston rod; 17, upper oil hole; 18, lower oil hole. DETAILED DESCRIPTION
[0025] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.
[0026] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.
[0027] Embodiment one
[0028] Referring to Figures 1 to 5 The embodiment provides a low-overload skid-type landing gear device capable of active stability enhancement, which comprises a landing gear outer cylinder 1, a landing gear piston rod 2, a torsion arm group, a rotary joint 7, a first power buffer 8, a second power buffer 9 and a skid assembly. The landing gear outer cylinder 1 is coaxially connected with the landing gear piston rod 2, and the two can move relative to each other in the axial direction and be limited in stroke by the first buffer device to ensure that excessive displacement does not occur under extreme load.
[0029] In a specific embodiment, an ear plate 6 is fixed to the top end of the landing gear outer cylinder 1 for fixed connection with the aircraft. The landing gear outer cylinder 1 is hollow inside and open at the bottom end, and can accommodate the landing gear piston rod 2 and the first buffer device to be put in. One end of the landing gear piston rod 2 extends into the landing gear outer cylinder 1 and is connected with the first buffer device installed in the landing gear outer cylinder 1. The first buffer device can absorb the impact force from the landing gear piston rod 2 to achieve buffering.
[0030] Further optimization scheme, in order to ensure the strength and durability under high load conditions such as high-speed landing, the landing gear outer cylinder 1 and the landing gear piston rod 2 are preferably made of high-strength titanium alloy material to achieve the balance between light weight and high temperature resistance.
[0031] In a specific embodiment, the torsion arm group comprises an upper torsion arm 3, a lower torsion arm 5 and a torsion arm pivot shaft 4 between the two. One end of the upper torsion arm 3 is hinged to the landing gear outer cylinder 1, the other end is hinged to the upper end of the lower torsion arm 5 through the torsion arm pivot shaft 4, and the lower end of the lower torsion arm 5 is hinged to the landing gear piston rod 2. This torsion arm structure not only transmits load, but also maintains stability during the unfolding and folding of the landing gear. The rotary joint 7 is hinged to the bottom end of the landing gear piston rod 2, providing a rotational degree of freedom around the hinge axis, so that the device can be folded flexibly when folded, significantly reducing the storage space.
[0032] In one embodiment, the torsion arm group composed of the upper torsion arm 3, the lower torsion arm 5 and the torsion arm pivot 4 is arranged at the front side of the landing gear (i.e. the front side in the length direction of the skid), or the torsion arm group is arranged at the rear side of the landing gear.
[0033] In the embodiment of the present application, the bottom end of the landing gear piston rod 2 is hinged with a rotary joint 7, the front and rear sides of the rotary joint 7 are respectively hinged with a group of power buffers, the other ends of the two power buffers are respectively hinged on the first skid 11 and the second skid 12, and the first skid plate and the second skid plate are connected through the intermediate skid connecting plate 10.
[0034] In one embodiment, the first power buffer 8 and the second power buffer 9 have the same structure, and one of them is taken as an example for structural description. The power buffer includes a power buffer outer cylinder 15, a power buffer piston rod 16 and a second buffer device connecting the two. The power buffer outer cylinder 15 is hinged with the rotary joint 7 and can rotate relative to the hinge axis. The power buffer outer cylinder 15 is provided with an upper oil hole 17 and a lower oil hole 18, which are respectively connected with an external hydraulic oil circuit system for supplying oil to the second buffer device. The power buffer piston rod 16 is coaxially connected with the power buffer outer cylinder 15 and can extend and retract along the axis under the drive of the second buffer device. The end of the power buffer piston rod 16 is connected with the skid by hinging to ensure that the skid can adapt to the uneven ground.
[0035] In one embodiment, the skid of the device includes the first skid 11 and the second skid 12, and the first skid 11 and the second skid 12 are connected through the skid connecting plate 10. The skid connecting plate 10 is hinged with the first skid 11 and the second skid 12 through the connecting pin shaft 13, allowing the skid to rotate within a certain angle range. This design plays a supporting role when the aircraft lands with a large load, preventing the landing gear piston rod 2 from bearing too large bending moment.
[0036] Specifically, as shown in Figure 2 the first power buffer 8 connects the rotary joint 7 and the first skid 11, and the second power buffer 9 connects the rotary joint 7 and the second skid 12. The upper surfaces of the first skid 11 and the second skid 12 are respectively fixedly connected with a hinge seat 14. The free end of the power buffer piston rod 16 of the first power buffer 8 is hinged on the hinge seat 14 on the first skid 11, and the upper end of the power buffer outer cylinder 15 is hinged on one side of the rotary joint 7. The free end of the power buffer piston rod 16 of the second power buffer 9 is hinged on the hinge seat 14 on the second skid 12, and the upper end of the power buffer outer cylinder 15 is hinged on the other side of the rotary joint 7.
[0037] It should be understood that the first buffer device and the second buffer device in the embodiment can also be oil-gas buffers, hydraulic buffers, mechanical springs, gas springs and other mechanisms or devices capable of dissipating impact energy.
[0038] The working principle and beneficial effects of Embodiment 1 of the present invention are as follows:
[0039] During the aircraft landing phase, when the skid landing gear is not touching down, the skid buffer is in an extended state. After the skid landing gear touches down, the ground load is transferred from the skid to the power buffer, and then from the rotary joint to the landing gear piston rod. At this time, the power buffer is compressed and buffered. The outer cylinder of the power buffer rotates around the hinge axis of the rotary joint, and the power buffer piston rod rotates around the hinge axis of the skid, causing the landing gear piston rod to move downward, providing a primary buffering effect and reducing the aircraft's landing overload. When the aircraft deviates from its taxiing direction, pressure is supplied to the power buffer oil hole, causing the power buffer piston rod to extend, increasing the skid pressure, thereby increasing the frictional resistance with the ground and generating a yaw moment to achieve the purpose of correcting the aircraft's taxiing direction. When the landing gear is retracted, pressure is supplied to the power buffer oil hole, driving the power buffer piston rod to retract and move the skid, saving storage space.
[0040] Example 2
[0041] Embodiment 2 of the present invention also provides a control method for a low-overload skid-type landing device with active stabilization, comprising:
[0042] During the aircraft's landing phase, when the skid landing gear has not yet touched down, the power buffer is in an extended state, such as... Figure 4 As shown. Once the skid contacts the ground, the ground load is transmitted through the first skid 11 and the second skid 12 to the dynamic buffer piston rod 16, and then through the rotary joint 7 to the landing gear piston rod 2. At this time, the dynamic buffer is compressed under the load, the outer cylinder 15 of the dynamic buffer rotates around the hinge axis of the rotary joint 7, and at the same time, the dynamic buffer piston rod 16 rotates around the skid hinge axis, pushing the landing gear piston rod 2 downward, completing the first-stage buffering effect, effectively reducing the aircraft landing overload, as... Figure 5 As shown.
[0043] If the aircraft deviates from its course during takeoff, the control system will supply pressure to the upper oil port 17 or the lower oil port 18. This will cause the hydraulic damper to extend the power damper piston rod 16, increasing the pressure of the first skid 11 and the second skid 12 on the ground. This significantly increases the frictional resistance between the skids and the ground, generating a controllable yaw moment, thereby achieving active correction of the aircraft's takeoff direction.
[0044] When the skid landing gear retracts, the control system supplies pressure to the downward oil port 18, causing the power damper piston rod 16 to retract, which in turn drives the first skid 11 and the second skid 12 to retract inward. Figure 3 As shown. The rotary joint 7 rotates around the axis during this process, further optimizing storage efficiency and ensuring the adaptability of the device in confined spaces.
[0045] In summary, the embodiment realizes multiple functions of low overload buffering, active taxiing correction and efficient storage through ingenious structural design and hydraulic control, makes up for the deficiencies of traditional wheel type and skid type landing gears, and is particularly suitable for application scenarios of hypersonic aircrafts.
[0046] In the description of the present application, it should be understood that the terms "longitudinal", "transverse", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.
[0047] The above-described embodiments are only preferred modes of the present application, and do not limit the scope of the present application. Various modifications and improvements to the technical solutions of the present application made by those skilled in the art without departing from the design spirit of the present application shall fall within the protection scope of the present application as defined by the claims.
Claims
1. An actively stabilizable low-overload skid-type landing gear characterized by, The landing gear outer cylinder (1) is provided with a first buffer device and a second buffer device. The landing gear piston rod (2) is coaxial with the landing gear outer cylinder (1) and is axially elastically connected. The rotary joint (7) is hinged to the bottom end of the landing gear piston rod (2). The skid assembly includes a first skid (11), a second skid (12), and a skid connecting plate (10) connected between the two, the skid connecting plate (10) being hinged to the first skid (11) and the second skid (12) through a connecting pin shaft (13), allowing the first skid (11) and the second skid (12) to rotate within a certain angle range to adapt to uneven landing surfaces. The first power buffer (8) is connected to the rotary joint (7) and the first skid (11), and the second power buffer (9) is connected to the rotary joint (7) and the second skid (12). The torsion arm group includes an upper torsion arm (3), a lower torsion arm (5), and a torsion arm pivot shaft (4), one end of the upper torsion arm (3) being hinged to the landing gear outer cylinder (1), the other end being hinged to the upper end of the lower torsion arm (5) through the torsion arm pivot shaft (4), and the lower end of the lower torsion arm (5) being hinged to the landing gear piston rod (2).
2. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 1, characterized in that The torsion arm group is arranged on the front side or the rear side of the landing device.
3. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 2, characterized in that The first power buffer (8) and the second power buffer (9) are structurally identical, each including a power buffer outer cylinder (15), a power buffer piston rod (16), and a second buffer device arranged in the power buffer outer cylinder (15).
4. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 1, characterized in that The second buffer device is a hydraulic buffer, and the power buffer outer cylinder (15) is provided with an upper oil hole (17) and a lower oil hole (18) for connecting an external hydraulic system.
5. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 4, characterized in that The upper end of the power buffer outer cylinder (15) of the first power buffer (8) is hinged to the rotary joint (7), and the lower end of the power buffer piston rod (16) of the first power buffer (8) is hinged to the first skid (11); the upper end of the power buffer outer cylinder (15) of the second power buffer (9) is hinged to the rotary joint (7), and the lower end of the power buffer piston rod (16) of the second power buffer (9) is hinged to the second skid (12).
6. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 4, characterized in that The landing gear outer cylinder (1) is provided with a first buffer device and a second buffer device.
7. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 1, characterized in that The landing gear outer cylinder (1) and the landing gear piston rod (2) are made of high-strength titanium alloy material.
8. The actively stabilizable low-overload skid-type landing gear arrangement according to claim 1, characterized in that When the aircraft lands, the first power buffer (8) and the second power buffer (9) are compressed under load, and at the same time, the landing gear piston rod (2) is compressed under load, reducing the landing overload of the aircraft.
9. A method of controlling an actively stabilizable low-overload skid-type landing gear according to any one of claims 1 to 8, characterized in that, When the aircraft slides in a direction deviating from the runway, the first power buffer (8) and / or the second power buffer (9) on the corresponding side of the aircraft is controlled to extend, increasing the pressure of the skid assembly on the ground and generating a yawing moment to correct the sliding direction. The first and second power buffers (8, 9) are controlled to retract to bring the sled assembly inwards to reduce the stowage space when the landing gear is stowed.