Pitching type self-adaptive undercarriage

Abstract

The utility model discloses a pitching type self-adaptive undercarriage which comprises a rocker arm with a first-stage actuator, a buffer with a two-stage actuator and an airplane wheel tire, wherein the bottom end of the rocker arm is mounted on an airplane wheel tire through a bearing, the top end of the rocker arm is hinged to the airplane body, the top end of the buffer is hinged to the airplane body, and the bottom end of the buffer is hinged to the rocker arm; the rocker arm comprises a first-stage actuator and is installed on an airplane wheel tire through the first-stage actuator. The buffer comprises a first actuating oil cylinder and a second actuating oil cylinder which form a two-stage actuator, and the bottom end of the second actuating oil cylinder is hinged to the rocker arm. According to the technical scheme, the problems that when a rocker arm type undercarriage of an existing helicopter carries out landing on the ground with large unevenness, the operation difficulty is large, a helicopter body is prone to overturning and the like are solved, and the problem that the rocker arm is difficult to retract and release in a small space is solved.

Description

Technical Field

[0001] The utility model relates to, but is not limited to, the technical field of helicopter landing gear structure design, and particularly relates to a pitching type adaptive landing gear. Background Art

[0002] Helicopters have performance advantages such as vertical takeoff and landing, hovering, and ultra-low altitude missions. Although helicopters can take off and land vertically without the need for a professional runway, they still have requirements for the flatness and stability of the landing site.

[0003] When a helicopter lands on a ground with large unevenness, there are problems such as difficult operation and easy overturning of the fuselage. These problems limit the mission capabilities of helicopters under more severe conditions. Currently, helicopter landing gears do not have a retractable function, which increases aerodynamic drag; most of the retractable landing gears of existing fixed-wing aircraft also use strut-type landing gears. For the rocker-type landing gear of a helicopter, it is difficult to complete the retraction and extension of the rocker in a small space by referring to the retractable structure of the existing strut-type landing gear. Summary of the Utility Model

[0004] The purpose of the utility model: To solve the above problems, an embodiment of the utility model provides a pitching type adaptive landing gear to solve the problems that when the rocker-type landing gear of an existing helicopter lands on a ground with large unevenness, there are problems such as difficult operation and easy overturning of the fuselage, and it is difficult to complete the retraction and extension of the rocker in a small space.

[0005] The technical solution of the utility model:

[0006] An embodiment of the utility model provides a pitching type adaptive landing gear, including: a rocker arm 1 with a primary actuator, a buffer 3 with a two-stage actuator, and a wheel tire 6;

[0007] Wherein, the bottom end of the rocker arm 1 is installed on the wheel tire 6 through a bearing, the top end is hinged to the fuselage, the top end of the buffer 3 is hinged to the fuselage, and the bottom end is hinged to the rocker arm 1;

[0008] The rocker arm 1 includes a primary actuator 2 and is installed on the wheel tire 6 through the primary actuator 2; the buffer 3 includes a first actuator cylinder 4 and a second actuator cylinder 5 that form a two-stage actuator, and the bottom end of the second actuator cylinder 5 is hinged to the rocker arm 1.

[0009] Optionally, in the pitching type adaptive landing gear as described above,

[0010] The pitching type adaptive landing gear performs adaptive adjustment during landing and parking through the telescoping of the primary actuator 2, the first actuator cylinder 4, and the second actuator cylinder 5;

[0011] The pitching-type adaptive landing gear also performs longitudinal retraction or longitudinal extension through the telescoping of the primary actuator 2, the first actuator cylinder 4, and the second actuator cylinder 5.

[0012] Optionally, in the pitching-type adaptive landing gear as described above, it further includes: a first oil circuit a connected to the primary actuator 2, a second oil circuit b connected to the first actuator cylinder 4, and a third oil circuit c connected to the second actuator cylinder 5.

[0013] Optionally, in the pitching-type adaptive landing gear as described above,

[0014] The pitching-type adaptive landing gear controls the hydraulic oil of the corresponding actuators through the first oil circuit a, the second oil circuit b, and the third oil circuit c, so that the pitching-type adaptive landing gear is in the landing gear retracted state, the landing / landing-on-ship adaptive adjustment state, the parking adaptive adjustment state, or the landing gear extended state.

[0015] Optionally, in the pitching-type adaptive landing gear as described above,

[0016] The pitching-type adaptive landing gear sucks out the hydraulic oil in the oil chambers of the corresponding actuators through the first oil circuit a, the second oil circuit b, and the third oil circuit c, and then locks the hydraulic valves in all three oil circuits to keep the landing gear in the retracted state.

[0017] Optionally, in the pitching-type adaptive landing gear as described above,

[0018] The pitching-type adaptive landing gear extends the second actuator cylinder 5 to its fully extended state through the third oil circuit c, uses the second actuator cylinder 5 as the oil chamber of the landing gear buffer 3, and controls the flow direction and oil volume of the first oil circuit a and the second oil circuit b to achieve adaptive adjustment of landing or landing-on-ship with the whole machine in a horizontal attitude.

[0019] Optionally, in the pitching-type adaptive landing gear as described above,

[0020] The pitching-type adaptive landing gear achieves adaptive adjustment during parking by placing the third oil circuit c in the locked state and adjusting the first oil circuit a and the second oil circuit b to keep the fuselage in a horizontal state.

[0021] Optionally, in the pitching-type adaptive landing gear as described above,

[0022] The pitching-type adaptive landing gear supplies oil to the first oil circuit a, the second oil circuit b, and the third oil circuit c to fill the oil chambers of the landing gear with hydraulic oil.

[0023] Advantages of the present utility model: The embodiment of the present utility model provides a pitching type adaptive landing gear. On the basis of realizing the functions of the traditional rocker landing gear (including towing and mooring), it further increases the retracting and extending ability, and has the advantage of a small retracting and extending range of motion, which is conducive to the layout of the landing gear bay space; it has the ability to dynamically adjust the balance, and can maintain the balance of the airframe within a large range in the adaptive working mode, greatly enhancing the adaptability to complex terrains / harsh sea conditions. The technical solution provided by the present utility model has the following beneficial effects:

[0024] 1. The retracting and extending movement trajectory of the adaptive landing gear provided by the present utility model is within the rocker movement plane, so the space required for the retraction and extension of the landing gear can be reduced.

[0025] 2. The two-stage buffer of the landing gear can have a longer buffer stroke and can absorb more crash energy.

[0026] 3. In the adaptive adjustment mode, the position of the wheel axle of the landing gear is flexible and variable, and various adjustment functions can be completed. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The drawings are used to provide a further understanding of the technical solution of the present utility model, and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present utility model, and do not constitute a limitation to the technical solution of the present utility model.

[0028] Figure 1 is a schematic structural diagram of the pitching type adaptive landing gear provided by the embodiment of the present utility model;

[0029] Figure 2 is a schematic oil circuit diagram of the pitching type adaptive landing gear provided by the embodiment of the present utility model in the landing gear retracted state;

[0030] Figure 3 is a schematic oil circuit diagram of the pitching type adaptive landing gear provided by the embodiment of the present utility model in the landing / landing ship adaptive adjustment state;

[0031] Figure 4 is a schematic oil circuit diagram of the pitching type adaptive landing gear provided by the embodiment of the present utility model in the landing gear extended state;

[0032] Figure 5 is a schematic diagram of the wheel axle movement range of the pitching type adaptive landing gear provided by the embodiment of the present utility model in each working state;

[0033] Figure 6 is a schematic diagram of the pitching type adaptive landing gear provided by the embodiment of the present utility model during the adaptive adjustment process. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0034] The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0035] As described in the above background art, for the rocker-type landing gear of existing helicopters, the following two problems generally exist:

[0036] First, since helicopters have requirements for the flatness and stability of the landing site, when landing on a ground with large unevenness, there are problems such as great operation difficulty and easy overturning of the fuselage.

[0037] Second, for the landing gear in the form of a rocker, it is difficult to retract and extend the rocker in a small space.

[0038] In view of the above problems, the embodiments of the present utility model provide a pitching-type adaptive landing gear. By designing two freely controllable hydraulic components, the pitching-type landing gear can adjust the postures of retraction / extension, landing, and parking by adjusting the lengths of the rocker and the buffer (i.e., having the ability of adaptive adjustment under multiple working conditions). By adopting the pitching-type adaptive landing gear provided by the embodiments of the present utility model, the functions of the landing gear are expanded, so as to be applicable to landing environments with greater unevenness, give play to the flexible and maneuverable characteristics of the helicopter, and expand the task ability range.

[0039] The following several specific embodiments provided by the present utility model can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.

[0040] Figure 1 FIG. is a schematic structural diagram of the pitching-type adaptive landing gear provided by the embodiments of the present utility model. The composition structure of the pitching-type adaptive landing gear provided by the embodiments of the present utility model includes: a rocker 1 with a primary actuator, a buffer 3 with a secondary actuator, and a wheel tire 6.

[0041] As Figure 1 shown, the bottom end of the rocker 1 is installed on the wheel tire 6 through a bearing, the top end is hinged to the fuselage, the top end of the buffer 3 is hinged to the fuselage, and the bottom end is hinged to the rocker 1.

[0042] The rocker 1 in the embodiments of the present utility model includes a primary actuator 2 and is installed on the wheel tire 6 through the primary actuator 2; in addition, the buffer 3 includes a first actuator cylinder 4 and a second actuator cylinder 5 that form a secondary actuator, and the bottom end of the second actuator cylinder 5 is hinged to the rocker 1.

[0043] Based on the pitching structure of the adaptive landing gear provided by the embodiments of the present utility model, a pitching type adaptive landing gear with three-stage adjustment ability is formed. By using this pitching type adaptive landing gear, adaptive adjustment during landing and parking can be achieved, and the realization of this adjustment function is executed by the telescoping of the primary actuator 2, the first actuator cylinder 4, and the second actuator cylinder 5. Additionally, longitudinal retraction or longitudinal extension can also be achieved, and the realization of this function is executed by the telescoping of the primary actuator 2, the first actuator cylinder 4, and the second actuator cylinder 5.

[0044] Referring to Figures 2 to 4 As shown, the oil circuit relationship of the pitching type adaptive landing gear provided by the embodiments of the present utility model is given. This pitching type adaptive landing gear further includes: a first oil circuit a connected to the primary actuator 2, a second oil circuit b connected to the first actuator cylinder 4, and a third oil circuit c connected to the second actuator cylinder 5.

[0045] Based on the three-stage adjustment structure of the pitching type adaptive landing gear provided by the embodiments of the present utility model and its cooperating oil circuit structure, the pitching type adaptive landing gear provided by the embodiments of the present utility model has the following states:

[0046] (1) Landing gear retracted state.

[0047] The way to achieve this state is that the first oil circuit a, the second oil circuit b, and the third oil circuit c suck out the hydraulic oil in the corresponding actuator oil chambers, and then the three oil circuits are all locked by hydraulic valves to keep the landing gear in the retracted state. As Figure 2 shown, it is the oil circuit schematic diagram of the pitching type adaptive landing gear provided by the embodiments of the present utility model when implementing the landing gear retracted state.

[0048] (2) Landing / landing on ship adaptive adjustment state.

[0049] The on-board sensors measure the height of the touchdown points of the landing gear wheels at the landing interface. The second actuator cylinder 5 connected to the third oil circuit c serves as the oil chamber of the landing gear buffer 3. Therefore, it is necessary to first fill the second actuator cylinder 5 with hydraulic oil and then lock the third oil circuit c. The first oil circuit a and the second oil circuit b control the flow direction and the amount of hydraulic oil through the on-board attitude adjustment system to keep the whole machine landing in a horizontal attitude on an uneven road surface / rough sea surface of the ship. As Figure 3 shown, it is the oil circuit schematic diagram of the pitching type adaptive landing gear provided by the embodiments of the present utility model when implementing the landing / landing on ship adaptive adjustment state.

[0050] (3) Parking adaptive adjustment state.

[0051] In this state, the third oil circuit c corresponding to the second actuating oil cylinder 5 is in a locked state. The adjustment amount of each landing gear is calculated through the pitch and roll angle sensors on the aircraft, and the fuselage is made horizontal by adjusting the first oil circuit a and the second oil circuit b. As Figure 3 shown.

[0052] (4) Landing gear extended state.

[0053] The way to achieve this state is to supply oil to the first oil circuit a, the second oil circuit b, and the third oil circuit c through the fuel tank oil pump, so that each oil chamber of the landing gear is filled with oil. As Figure 4 shown, it is a schematic diagram of the oil circuit for the pitching type adaptive landing gear provided by the embodiment of the present invention to implement the landing gear extended state.

[0054] Combining the above various states, Figure 5 it is a schematic diagram of the wheel axle movement range of the pitching type adaptive landing gear provided by the embodiment of the present invention in each working state. Figure 6 It is a schematic diagram of the pitching type adaptive landing gear provided by the embodiment of the present invention during the adaptive adjustment process. As Figure 5 shown, the wheel axle movement range that the wheel 6 of the wheel tire of the adaptive landing gear can achieve. The range within the dotted fan-shaped frame is the range of landing / landing ship adaptive adjustment, and the extreme position extended from the extreme point of the fan is the wheel axle position center of gravity in the fully extended state of the landing gear. In the landing gear retracted state, since the oil in the actuating oil cylinder 5 needs to be discharged, the wheel axle position can be higher than the fan-shaped range.

[0055] The pitching type adaptive landing gear provided by the embodiment of the present invention has the following key points:

[0056] 1) The adaptive landing gear has energy absorption and actuation working modes, and can also complete the retraction and extension functions;

[0057] 2) The landing gear provided by the present invention, in addition to meeting the functional requirements of the traditional rocker type landing gear, also has the ability to adapt to complex terrains / harsh sea conditions, has dynamic balance control ability, can maintain the balance of the airframe under harsh working conditions, and the adaptive working mode can make the wheels move perpendicular to the ground within the movement range;

[0058] 3) The buffer 3 has a two-stage actuation ability, and it can also play a two-stage buffering function under anti-crash working conditions, absorbing more crash energy.

[0059] The pitching-type adaptive landing gear provided by the embodiment of the present utility model, on the basis of realizing the functions of the traditional rocker landing gear (including towing and mooring), further increases the retracting and extending ability, and has the advantages of a small retracting and extending range of motion, which is conducive to the layout of the landing gear compartment space; it has the ability to dynamically adjust the balance and can maintain the balance of the airframe within a large range in the adaptive working mode, greatly enhancing the adaptability to complex terrains / harsh sea conditions. The technical solution provided by the present utility model has the following beneficial effects:

[0060] 1. The retracting and extending movement trajectory of the adaptive landing gear provided by the present utility model is within the rocker movement plane, so the space required for the retracting and extending of the landing gear can be reduced.

[0061] 2. The two-stage buffer of the landing gear can have a longer buffer stroke and can absorb more crash energy.

[0062] 3. In the adaptive adjustment mode, the position of the wheel axle of the landing gear is flexible and variable, and various adjustment functions can be completed.

[0063] Although the disclosed embodiments of the present utility model are as above, the content is only the embodiments adopted for the convenience of understanding the present utility model and is not used to limit the present utility model. Any person skilled in the art within the scope of the present utility model can make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed by the present utility model. However, the scope of patent protection of the present utility model shall still be subject to the scope defined by the appended claims.

Claims

1. A pitch-type adaptive landing gear, characterized in that: include: A rocker arm (1) having a one-stage actuator, a buffer (3) having a two-stage actuator, and a wheel tire (6); The bottom end of the rocker arm (1) is mounted on the wheel tire (6) through a bearing, and the top end is hinged to the machine body; the top end of the buffer (3) is hinged to the machine body, and the bottom end is hinged to the rocker arm (1); The rocker arm (1) comprises a first-stage actuator (2) which is mounted on a wheel tire (6) via the first-stage actuator (2); the buffer (3) comprises a first actuating cylinder (4) and a second actuating cylinder (5) which form a two-stage actuator, and the bottom end of the second actuating cylinder (5) is hinged to the rocker arm (1).

2. The pitch-type adaptive landing gear according to claim 1, characterized in that: The pitch-type adaptive landing gear performs adaptive adjustment during landing and parking by extending and retracting the first-stage actuator (2), the first actuating cylinder (4) and the second actuating cylinder (5); The pitch-type adaptive landing gear is also able to be longitudinally retracted or longitudinally extended through the extension and retraction of the primary actuator (2), the first actuating cylinder (4) and the second actuating cylinder (5).

3. The pitch-adaptive landing gear according to claim 2, characterized in that: Also includes: A first oil circuit (a) connected to the primary actuator (2), a second oil circuit (b) connected to the first actuating cylinder (4), and a third oil circuit (c) connected to the second actuating cylinder (5).

4. The pitch-adaptive landing gear according to any one of claims 1 to 3, characterized in that: The pitch-type adaptive landing gear controls the oil of the corresponding actuators through the first oil circuit (a), the second oil circuit (b), and the third oil circuit (c), so that the pitch-type adaptive landing gear is in a landing gear retracted state, a landing / carrier landing adaptive adjustment state, a shutdown adaptive adjustment state, or a landing gear extended state.

5. The pitch-adaptive landing gear according to claim 4, characterized in that: The pitch-type adaptive landing gear sucks out the hydraulic oil in the oil chamber of the corresponding actuator through the first oil circuit (a), the second oil circuit (b), and the third oil circuit (c), and then the three oil circuits are all hydraulically locked to keep the landing gear in the retracted state.

6. The pitch-adaptive landing gear according to claim 4, characterized in that: The pitch-type adaptive landing gear uses the third oil circuit (c) to fully extend the second actuating oil cylinder (5) so that the second actuating oil cylinder (5) serves as the oil chamber of the landing gear buffer (3), and controls the flow direction and oil volume of the first oil circuit (a) and the second oil circuit (b) so that the whole machine can achieve adaptive adjustment for landing or carrier landing in a horizontal posture.

7. The pitch-adaptive landing gear according to claim 4, characterized in that: The pitch-type adaptive landing gear realizes parking adaptive adjustment by placing the third oil circuit (c) in a locked state and adjusting the first oil circuit (a) and the second oil circuit (b) to ensure that the fuselage is in a horizontal state.

8. The pitch-adaptive landing gear according to claim 4, characterized in that: The pitch-type adaptive landing gear supplies oil to the first oil circuit (a), the second oil circuit (b) and the third oil circuit (c), so that each oil chamber of the landing gear is filled with oil.

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