WO2016066094A1 - Buffering apparatus for landing gear buffering strut - Google Patents

Buffering apparatus for landing gear buffering strut Download PDF

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Publication number
WO2016066094A1
WO2016066094A1 PCT/CN2015/093053 CN2015093053W WO2016066094A1 WO 2016066094 A1 WO2016066094 A1 WO 2016066094A1 CN 2015093053 W CN2015093053 W CN 2015093053W WO 2016066094 A1 WO2016066094 A1 WO 2016066094A1
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Prior art keywords
strut
buffer
cushioning
buffering
landing gear
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PCT/CN2015/093053
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French (fr)
Chinese (zh)
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陈宝琦
李生杰
曹丹青
王鸿鑫
是贤珠
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中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Publication of WO2016066094A1 publication Critical patent/WO2016066094A1/en

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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 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/60—Oleo legs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
    • F16F9/32—Details
    • F16F9/50—Special means providing automatic damping adjustment, i.e. self-adjustment of damping by particular sliding movements of a valve element, other than flexions or displacement of valve discs; Special means providing self-adjustment of spring characteristics

Definitions

  • the present invention generally relates to the field of aircraft technology, and more particularly to a cushioning device for a landing gear cushioning strut.
  • the landing gear strut adopts the structure of installing the oil-filled buffer strut.
  • Figure 1 shows a typical oil and gas buffer strut.
  • the buffer strut outer cylinder 101 is connected to the upper mass, and a chamber containing high-pressure gas, for example, the nitrogen chamber 102 is located at the upper portion of the pillar inner chamber, and there is no separation piston between the oil and gas.
  • An oil hole support tube 103 is provided in the nitrogen chamber 102, and a small hole 104 is provided therein to maintain the oil level 108 in the chamber in balance.
  • the oil hole support tube 103 can provide a plane with the oil hole 107 between the oil and gas, and the pressure of the hydraulic oil flowing through the oil hole 107 acts to resist the compression of the column, while the nitrogen chamber 102 compresses the absorption portion of the landing impact energy.
  • the inner cylinder piston or inner cylinder 105 which is movable along the inner wall of the outer cylinder 101, is provided with a variable-section oil needle 106.
  • the oil needle 106 enters the oil as the stroke changes.
  • the depth of the holes 107 is different, which causes a change in the effective flow area of the oil holes 107, thereby achieving the effect of adjusting the oil damping.
  • the oil passes from one cavity through the oil hole or the orifice to the other cavity, absorbing the landing energy.
  • the compression of the pillar causes the volume of nitrogen in the cavity to be compressed, and the absorbed energy acts as a shock absorber.
  • the friction at the upper and lower supports also affects the cushioning performance.
  • the oil and gas buffer struts have high buffering efficiency and are excellent in terms of energy dissipation.
  • the existing oil-gas buffering strut can change its range as the stroke and acceleration change, but its adjustment range is limited. Due to the pre-pressing pressure adjustment of the air chamber, it is difficult to adjust a large range according to the change of the external impact load of the aircraft, so it is mostly passive control. In this case, the damping effect is obviously limited, and the initial stiffness of the aircraft is small.
  • the buffering efficiency is low, the peak load during the buffering process is obvious, and the structure and material requirements are high.
  • the better buffer form should have certain active control or semi-active control performance. It can adjust the damping and stiffness of the system according to the external excitation, and has certain dynamic response capability, which can effectively reduce the load peak and effectively improve the buffer efficiency. .
  • the general object of the present invention is to solve the defects in the prior art, improve the structure of the aircraft landing gear buffer strut, and propose a semi-active control mode-based design scheme to improve the performance of the buffer strut to improve the original oil and gas buffer.
  • the pillar structure has unadjustable defects, which effectively improves the buffering efficiency of the buffer strut and reduces the overload protection structure and improves the dynamic performance.
  • a cushioning device for a landing gear cushioning strut including an outer cylinder and an inner cylinder movable along an inner wall of the outer cylinder, the cushioning device comprising: at least one excitation component, Arranging on the inner side of the outer cylinder wall of the buffer strut; at least one inductive component disposed in the inner cylinder of the buffer strut in response to actuation of the energizing component such that the inner cylinder is along the outer side of the buffer strut
  • the barrel movement generates a buffer damping; a control unit that controls the excitation component in real time according to a motion signal of the buffer post; and a sensing component that is disposed at a lower end of the buffer post to detect a motion signal of the buffer post and The motion signal is fed back to the control unit.
  • the energizing means of the damping device are a single component or a plurality of components arranged symmetrically around the inner side of the outer cylinder wall of the buffer strut.
  • the excitation component consists of a silicon steel sheet, a three-phase winding, and the control unit is a winding current control unit.
  • the inductive component comprises an inductive alloy.
  • the induction alloy may be an aluminum iron alloy or a copper iron alloy.
  • the sensing component comprises a displacement sensor.
  • the core idea is to adjust the amplitude and phase of the current flowing in the winding in real time by detecting the motion signal of the buffer strut, thereby generating a damping buffer force and improving the cushioning performance of the landing gear.
  • the invention can utilize the original structural form of the aircraft landing gear buffering strut and perform a small number of modifications. Under the function of not affecting the original oil and gas buffering strut, an electromagnetic buffering device is added to realize semi-active control of the buffering strut, and the buffer damping is adjusted in real time. Stiffness, effectively improve the cushioning performance of existing structures and improve the safety and comfort of the aircraft.
  • a cushioning device for a landing gear buffer strut in an oil and gas buffer strut comprising:
  • the sensing component detects a motion signal of the buffer strut and feeds the motion signal to the control unit;
  • the control unit calculates and determines the load and the external impact state of the buffer strut according to the motion signal fed back by the sensing component, and controls the excitation component to generate the excitation of the sensing component in real time;
  • the inductive component urges the inner barrel of the buffer strut to move along the outer barrel in response to the energizing to create additional cushioning damping.
  • the motion signal includes a compression stroke, a speed, and an acceleration magnitude
  • the control unit changes the magnitude and phase of the control current to the excitation component in real time according to a change in the compression stroke, the velocity, and the acceleration magnitude of the buffer strut.
  • the control mode of the electromagnetic buffer strut is to change the winding current, which is easy to realize by automatic control;
  • the semi-active adjustment of the buffer strut is realized, and the adaptability of the dynamic characteristics is enhanced, which can effectively improve the initial buffering efficiency, and can reduce the load of the oil and gas spring at the peak of the load, thereby improving the safety and reliability of the structure.
  • the induction of the induction alloy in the winding magnetic field adds additional damping force to the buffering process of the landing gear buffer strut, which is not only simple in structure, easy to implement, but also has It has a wide range of applications, such as rapid response, large adjustment range and little influence on the original structure of the landing gear.
  • Figure 1 shows a schematic structural view of an existing oil and gas buffering strut
  • FIG. 2 shows a schematic view of a cushioning device for a landing gear cushioning strut in accordance with an embodiment of the present invention.
  • FIG. 2 An embodiment of a cushioning device for a landing gear cushioning post according to the present invention is shown in Figure 2, the typical composition of which comprises an energizing member disposed inside the outer wall of the buffer strut, an inductive member on the inner cylinder of the buffer strut, and a winding current
  • the control unit is three parts.
  • the cushioning device according to the present invention can be applied to various existing buffer strut structures, particularly oil and gas cushioning strut.
  • the inner side of the outer wall 201 of the buffer strut is provided with an energizing member, and the sensing member is attached to the lower end of the baffle strut.
  • a displacement sensor (not shown).
  • the excitation component is mainly composed of a silicon steel sheet 203 and a three-phase winding 204. Thereby, the pillar wall outside the winding 204 can effectively prevent the magnetic field from leaking out, improve the efficiency, and reduce the influence on other components on the landing gear. Winding 204 can be wound by an explicit connection.
  • This structure utilizes the original structure of the buffer strut and can be lubricated by the oil in the strut, and the heat generated by the eddy current of the winding can be dissipated through the oil and the wall of the cylinder.
  • the induction member can be modified by the buffer post inner cylinder 205, and a composite structure is adopted, and the induction alloy 202 is disposed in the inner cylinder 205, so that the electromagnetic force generated by the outer cylinder 201 can generate electromagnetic force to the inner cylinder 205 of the buffer post.
  • the inner cylinder 205 moves along the outer cylinder 201 of the buffer strut to create additional cushioning damping.
  • the inner cylinder 205 can utilize the original structure and shape, and the material can be selected from 45 gauge steel to provide high rigidity. Aluminum or copper can be used on the outside and surface treated to improve wear resistance (eg chrome plating) for increased service life.
  • a traveling wave magnetic field along the axial direction of the buffer strut can be generated in the coil winding 204.
  • the relative movement between the excitation component and the inductive component causes the induction alloy to move in the traveling wave magnetic field, cutting the traveling wave magnetic field, and generating electromagnetic force.
  • the traveling wave magnetic field is opposite to the relative motion direction, the electromagnetic force blocks the relative motion between the energizing member and the sensing member, that is, additional damping is applied to the buffer post inner cylinder 205.
  • the motion signals of the buffer strut can be collected in real time by the displacement sensor, including but not limited to the compression stroke, velocity and acceleration magnitude, and these motion signals are fed back into the coil current control unit (not shown), and the control unit passes Calculate the state of the load and external impact of the oil and gas buffer strut, calculate the amplitude and phase of the current through the winding 204 in real time, and generate additional damping force to compensate.
  • the buffer strut is low in rigidity. If the external impact load is too large, the winding 204 can generate additional repulsive force to increase the buffer strut stiffness and improve the initial buffering efficiency; during the entire buffering process, the winding 204 is additionally generated.
  • the damping force can reduce the load of the oil and gas buffer strut, reduce the pressure of the oil and gas chamber, and increase the reliability and safety of the structure; in the case of insufficient compression, the electromagnetic coil 204 can also increase the compression amount by changing the current direction to the aircraft wheel.
  • the generation of the carrier signal plays a certain auxiliary role.
  • the semi-active control mode according to the present invention is advantageous for adapting to more complicated external conditions, improving the landing buffer efficiency of the aircraft, and using a good control algorithm can further increase the safety and comfort of the aircraft landing process.
  • the use of electromagnetic to generate additional cushioning resistance can greatly expand the buffer range of the original buffer strut structure, increase the adaptability to the external environment of the landing gear, make the load curve tend to be stable, weaken the amplitude of the load change, and improve the safety and reliability of the buffer strut. Sex.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Damping Devices (AREA)

Abstract

A buffering apparatus for a landing gear buffering strut and a method for using same in an air-oil buffering strut. The buffering strut (200) comprises an outer cylinder (201) and an inner cylinder (205) able to move along the inside wall of the outer cylinder (201); the buffering apparatus comprises: at least one excitation component, arranged on the inner side of the wall of the outer cylinder (201) of the buffering strut (200); at least one induction component, arranged in the inner cylinder (205) of the buffering strut (200) to respond to the excitation of the excitation component, such that the inner cylinder (205) moves along the inside wall of the outer cylinder (201) of the buffering strut (200) and produces buffer damping; a control unit, used for controlling the excitation component in real time on the basis of a motion signal of the buffering strut (200); and a sensing component, arranged on the lower end of the buffering strut (200) to detect the motion signal of the buffering strut (200) and to feed the motion signal back to the control unit. The semi-active control method of the present buffering apparatus is beneficial for adaptation to more complex external conditions, improves the buffering efficiency of an aircraft on landing, and, by using an excellent control algorithm, further enhances the safety and comfort of the aircraft landing process.

Description

起落架缓冲支柱的缓冲装置Damping device for landing gear cushioning strut 技术领域Technical field
本发明总的涉及飞行器技术领域，尤其涉及一种用于起落架缓冲支柱的缓冲装置。The present invention generally relates to the field of aircraft technology, and more particularly to a cushioning device for a landing gear cushioning strut.
背景技术Background technique
现代飞机在降落过程中，起落架需要承受较大的冲击载荷，为保证降落过程的平稳性和安全性，起落架支柱多采用安装油气式缓冲支柱的结构形式。In the process of landing, the landing gear of the modern aircraft needs to bear a large impact load. To ensure the stability and safety of the landing process, the landing gear strut adopts the structure of installing the oil-filled buffer strut.
图1示出了一种典型的油气缓冲支柱。在这种油气式缓冲支柱100的结构中，缓冲支柱外筒101与上部质量相连接，容纳有高压气体的腔室，例如氮气腔102位于支柱内腔上部，油气之间不设分离活塞。氮气腔102中设有油孔支撑管103，其上设有小孔104以使腔内油液液面108保持平衡。油孔支撑管103可在油气之间提供带油孔107的平面，液压油流经油孔107的压力会产生抵抗支柱压缩的作用，同时氮气腔102压缩可吸收部分着陆撞击能量。如图1所示，可沿外筒101的内壁移动的内筒活塞或内筒105中装有变截面油针106，当支柱受力而伸长或压缩时，随行程变化油针106进入油孔107的深度不同，这就引起油孔107有效过流面积的变化，从而达到调节油液阻尼的作用。也就是说，油液从一腔通过油孔或阻尼孔进入另一腔，吸收着陆能量。同时支柱压缩引起腔内氮气体积压缩，吸收能量起到减震作用。除液压力和气动力之外，上下支撑处的摩擦力也会对缓冲性能产生影响。油气缓冲支柱具有较高的缓冲效率，且从能量耗散的观点上看也较为优秀。Figure 1 shows a typical oil and gas buffer strut. In the structure of the oil-gas cushioning strut 100, the buffer strut outer cylinder 101 is connected to the upper mass, and a chamber containing high-pressure gas, for example, the nitrogen chamber 102 is located at the upper portion of the pillar inner chamber, and there is no separation piston between the oil and gas. An oil hole support tube 103 is provided in the nitrogen chamber 102, and a small hole 104 is provided therein to maintain the oil level 108 in the chamber in balance. The oil hole support tube 103 can provide a plane with the oil hole 107 between the oil and gas, and the pressure of the hydraulic oil flowing through the oil hole 107 acts to resist the compression of the column, while the nitrogen chamber 102 compresses the absorption portion of the landing impact energy. As shown in Fig. 1, the inner cylinder piston or inner cylinder 105, which is movable along the inner wall of the outer cylinder 101, is provided with a variable-section oil needle 106. When the strut is stretched or compressed by force, the oil needle 106 enters the oil as the stroke changes. The depth of the holes 107 is different, which causes a change in the effective flow area of the oil holes 107, thereby achieving the effect of adjusting the oil damping. That is to say, the oil passes from one cavity through the oil hole or the orifice to the other cavity, absorbing the landing energy. At the same time, the compression of the pillar causes the volume of nitrogen in the cavity to be compressed, and the absorbed energy acts as a shock absorber. In addition to the hydraulic pressure and aerodynamic forces, the friction at the upper and lower supports also affects the cushioning performance. The oil and gas buffer struts have high buffering efficiency and are excellent in terms of energy dissipation.
为提高油气式缓冲支柱的缓冲性能，本领域设计人员近年在结构形式和内部构造上都进行了大量的设计尝试，如变油孔、双腔等技术，但改进空间越来越小。此外，现有油气式缓冲支柱虽然阻尼力可随着行程和加速度的变化而变化，但其调节范围是有限的，基 本靠气腔预冲压压力调节，很难根据飞机外部冲击载荷的变化进行大范围的调节，因此多属于被动控制，这种情况下减震效果会受到明显的限制，且飞机着陆初期刚度较小、缓冲效率较低，缓冲过程中的峰值负载明显，对结构和材料的要求较高。In order to improve the cushioning performance of the oil-gas cushioning struts, designers in the field have made a lot of design attempts in structural forms and internal structures in recent years, such as oil-changing holes, double-cavity and the like, but the improvement space is getting smaller and smaller. In addition, the existing oil-gas buffering strut can change its range as the stroke and acceleration change, but its adjustment range is limited. Due to the pre-pressing pressure adjustment of the air chamber, it is difficult to adjust a large range according to the change of the external impact load of the aircraft, so it is mostly passive control. In this case, the damping effect is obviously limited, and the initial stiffness of the aircraft is small. The buffering efficiency is low, the peak load during the buffering process is obvious, and the structure and material requirements are high.
发明内容Summary of the invention
较为优秀的缓冲形式，应该具备一定的主动控制或半主动控制性能，可以根据外界的激励来调节***的阻尼和刚度，具备一定的动态响应能力，进而能够有效降低负载峰值，并有效提高缓冲效率。The better buffer form should have certain active control or semi-active control performance. It can adjust the damping and stiffness of the system according to the external excitation, and has certain dynamic response capability, which can effectively reduce the load peak and effectively improve the buffer efficiency. .
因此，本发明总的目的在于解决现有技术中的缺陷，对飞机起落架缓冲支柱结构进行改进，提出一种可改善缓冲支柱性能的基于半主动控制方式的设计方案，以改善原有油气缓冲支柱结构不可调节的缺陷，从而有效提高缓冲支柱的缓冲效率并减小过载保护结构，改善动态性能。Therefore, the general object of the present invention is to solve the defects in the prior art, improve the structure of the aircraft landing gear buffer strut, and propose a semi-active control mode-based design scheme to improve the performance of the buffer strut to improve the original oil and gas buffer. The pillar structure has unadjustable defects, which effectively improves the buffering efficiency of the buffer strut and reduces the overload protection structure and improves the dynamic performance.
根据本发明的一个方面，提供一种起落架缓冲支柱的缓冲装置，所述缓冲支柱包括外筒和能够沿所述外筒的内壁移动的内筒，所述缓冲装置包括：至少一个激励部件，其布置于所述缓冲支柱的外筒壁内侧；至少一个感应部件，其布置于所述缓冲支柱的内筒中以响应于所述激励部件的激励，使得所述内筒沿所述缓冲支柱的外筒移动产生缓冲阻尼；控制单元，其根据所述缓冲支柱的运动信号实时控制所述激励部件；以及感测部件，其布置于所述缓冲支柱下端以检测所述缓冲支柱的运动信号并将所述运动信号反馈至所述控制单元。According to an aspect of the invention, a cushioning device for a landing gear cushioning strut is provided, the cushioning strut including an outer cylinder and an inner cylinder movable along an inner wall of the outer cylinder, the cushioning device comprising: at least one excitation component, Arranging on the inner side of the outer cylinder wall of the buffer strut; at least one inductive component disposed in the inner cylinder of the buffer strut in response to actuation of the energizing component such that the inner cylinder is along the outer side of the buffer strut The barrel movement generates a buffer damping; a control unit that controls the excitation component in real time according to a motion signal of the buffer post; and a sensing component that is disposed at a lower end of the buffer post to detect a motion signal of the buffer post and The motion signal is fed back to the control unit.
根据一种优选形式，所述缓冲装置的激励部件为围绕所述缓冲支柱的外筒壁内侧布置的单一部件或对称设置的多个部件。According to a preferred form, the energizing means of the damping device are a single component or a plurality of components arranged symmetrically around the inner side of the outer cylinder wall of the buffer strut.
根据一种优选形式，所述激励部件由硅钢片、三相绕组组成，所述控制单元为绕组电流控制单元。According to a preferred form, the excitation component consists of a silicon steel sheet, a three-phase winding, and the control unit is a winding current control unit.
根据一种优选形式，所述感应部件包括感应合金。优选地，所述感应合金可以为铝铁合金或铜铁合金。 According to a preferred form, the inductive component comprises an inductive alloy. Preferably, the induction alloy may be an aluminum iron alloy or a copper iron alloy.
根据一种优选形式，所述感测部件包括位移传感器。According to a preferred form, the sensing component comprises a displacement sensor.
在上述例示实施方式中，核心思路为通过检测缓冲支柱的运动信号，实时调节绕组中流过的电流幅值及相位，从而产生阻尼缓冲力，改善起落架的缓冲性能。In the above exemplary embodiment, the core idea is to adjust the amplitude and phase of the current flowing in the winding in real time by detecting the motion signal of the buffer strut, thereby generating a damping buffer force and improving the cushioning performance of the landing gear.
本发明可利用飞机起落架缓冲支柱的原有结构形式，进行少量改装，在不影响原有油气缓冲支柱的功能下，增加一套电磁缓冲装置，实现缓冲支柱的半主动控制，实时调节缓冲阻尼刚度，有效改善现有结构的缓冲性能，提高飞机的安全性和舒适度。The invention can utilize the original structural form of the aircraft landing gear buffering strut and perform a small number of modifications. Under the function of not affecting the original oil and gas buffering strut, an electromagnetic buffering device is added to realize semi-active control of the buffering strut, and the buffer damping is adjusted in real time. Stiffness, effectively improve the cushioning performance of existing structures and improve the safety and comfort of the aircraft.
根据本发明的另一方面，提供了一种起落架缓冲支柱的缓冲装置在油气缓冲支柱中的使用方法，包括：According to another aspect of the present invention, there is provided a method of using a cushioning device for a landing gear buffer strut in an oil and gas buffer strut comprising:
a、感测部件检测缓冲支柱的运动信号，并将运动信号反馈至控制单元；a, the sensing component detects a motion signal of the buffer strut and feeds the motion signal to the control unit;
b、控制单元根据所述感测部件反馈的运动信号，计算并判断缓冲支柱所承受的载荷及外部冲击状态，实时控制激励部件产生对感应部件的激励；b. The control unit calculates and determines the load and the external impact state of the buffer strut according to the motion signal fed back by the sensing component, and controls the excitation component to generate the excitation of the sensing component in real time;
c、感应部件响应于所述激励促使缓冲支柱的内筒沿外筒移动，以产生额外的缓冲阻尼。c. The inductive component urges the inner barrel of the buffer strut to move along the outer barrel in response to the energizing to create additional cushioning damping.
进一步地，所述运动信号包括压缩行程、速度和加速度大小，所述控制单元根据缓冲支柱的压缩行程、速度和加速度大小的改变而实时改变对所述激励部件的控制电流的幅值及相位。Further, the motion signal includes a compression stroke, a speed, and an acceleration magnitude, and the control unit changes the magnitude and phase of the control current to the excitation component in real time according to a change in the compression stroke, the velocity, and the acceleration magnitude of the buffer strut.
本发明采用电磁补偿式缓冲支柱至少具有以下优点：The invention adopts electromagnetic compensation type buffer strut at least has the following advantages:
1、非接触式缓冲，无摩擦损耗，缓冲过程平稳无噪声；1. Non-contact buffer, no friction loss, smooth and noise-free buffering process;
2、电磁缓冲支柱的控制方式为改变绕组电流，易于通过自动控制的方式实现；2. The control mode of the electromagnetic buffer strut is to change the winding current, which is easy to realize by automatic control;
3、实现了缓冲支柱的半主动调节，动态特性适应性增强，可有效提高初期的缓冲效率，并可在负载峰值处减轻油气弹簧的负载，提高结构的安全性和可靠性。3. The semi-active adjustment of the buffer strut is realized, and the adaptability of the dynamic characteristics is enhanced, which can effectively improve the initial buffering efficiency, and can reduce the load of the oil and gas spring at the peak of the load, thereby improving the safety and reliability of the structure.
因此，利用感应合金在绕组磁场中的感应在起落架缓冲支柱的缓冲过程中附加额外阻尼力，不仅结构简单、实施容易，而且具有 反应迅速、调节范围大、对起落架原结构影响较小等特点，具有良好广泛的应用前景。Therefore, the induction of the induction alloy in the winding magnetic field adds additional damping force to the buffering process of the landing gear buffer strut, which is not only simple in structure, easy to implement, but also has It has a wide range of applications, such as rapid response, large adjustment range and little influence on the original structure of the landing gear.
附图说明DRAWINGS
本发明的其它特征以及优点将通过以下结合附图详细描述的优选实施方式更好地理解，附图中：Other features and advantages of the present invention will be better understood from the following detailed description taken in conjunction <
图1示出了现有油气缓冲支柱的结构示意图；Figure 1 shows a schematic structural view of an existing oil and gas buffering strut;
图2示出了根据本发明一种实施方式的起落架缓冲支柱的缓冲装置的示意图。2 shows a schematic view of a cushioning device for a landing gear cushioning strut in accordance with an embodiment of the present invention.
具体实施方式detailed description
根据本发明的起落架缓冲支柱的缓冲装置的一种实施方式如图2所示，其典型组成包括布置于缓冲支柱外筒壁内侧的激励部件，缓冲支柱内筒上的感应部件，以及绕组电流控制单元三部分。An embodiment of a cushioning device for a landing gear cushioning post according to the present invention is shown in Figure 2, the typical composition of which comprises an energizing member disposed inside the outer wall of the buffer strut, an inductive member on the inner cylinder of the buffer strut, and a winding current The control unit is three parts.
根据本发明的缓冲装置可应用于现有各种缓冲支柱结构中，尤其是油气式缓冲支柱。相比于图1示出的现有缓冲支柱100，在本发明改进的缓冲支柱200中，缓冲支柱外筒壁201内侧加装有激励部件，，并在缓冲支柱下端处加装有感测部件，例如位移传感器(未示出)。其中激励部件主要由硅钢片203和三相绕组204组成。由此，绕组204外的支柱壁可有效防止磁场外泄，提高效率，减少对起落架上其它元器件的影响。绕组204可采用显式连接的方法缠绕。此结构利用缓冲支柱的原有结构，并可利用支柱内油液润滑，绕组涡流产生的热量可通过油液及筒壁耗散。感应部件可通过对缓冲支柱内筒205改造而成，采用复合结构，在内筒205内装设感应合金202，从而能够通过外筒201产生的磁场来对缓冲支柱的内筒205产生电磁力，使得内筒205沿缓冲支柱的外筒201移动产生额外的缓冲阻尼。内筒205可利用原结构及形状，材料可选用45号钢来提供价高的刚度。外侧可选用铝或铜，并进行表面处理以提高耐磨性(例如镀铬)，增加使用寿命。 The cushioning device according to the present invention can be applied to various existing buffer strut structures, particularly oil and gas cushioning strut. In the improved buffer strut 200 of the present invention, in the improved buffer strut 200 of the present invention, the inner side of the outer wall 201 of the buffer strut is provided with an energizing member, and the sensing member is attached to the lower end of the baffle strut. For example, a displacement sensor (not shown). The excitation component is mainly composed of a silicon steel sheet 203 and a three-phase winding 204. Thereby, the pillar wall outside the winding 204 can effectively prevent the magnetic field from leaking out, improve the efficiency, and reduce the influence on other components on the landing gear. Winding 204 can be wound by an explicit connection. This structure utilizes the original structure of the buffer strut and can be lubricated by the oil in the strut, and the heat generated by the eddy current of the winding can be dissipated through the oil and the wall of the cylinder. The induction member can be modified by the buffer post inner cylinder 205, and a composite structure is adopted, and the induction alloy 202 is disposed in the inner cylinder 205, so that the electromagnetic force generated by the outer cylinder 201 can generate electromagnetic force to the inner cylinder 205 of the buffer post. The inner cylinder 205 moves along the outer cylinder 201 of the buffer strut to create additional cushioning damping. The inner cylinder 205 can utilize the original structure and shape, and the material can be selected from 45 gauge steel to provide high rigidity. Aluminum or copper can be used on the outside and surface treated to improve wear resistance (eg chrome plating) for increased service life.
实际使用过程中，根据电磁感应原理，在当三相交流电流通过线圈绕组204时，即可在线圈绕组204内产生沿缓冲支柱轴向方向的行波磁场。缓冲支柱压缩时，激励部件和感应部件之间相对运动，引起感应合金在行波磁场中运动，切割行波磁场，产生电磁力。当行波磁场与相对运动方向相反时，电磁力阻碍激励部件和感应部件之间的相对运动，即对缓冲支柱内筒205产生额外的阻尼。In actual use, according to the principle of electromagnetic induction, when a three-phase alternating current passes through the coil winding 204, a traveling wave magnetic field along the axial direction of the buffer strut can be generated in the coil winding 204. When the buffer strut is compressed, the relative movement between the excitation component and the inductive component causes the induction alloy to move in the traveling wave magnetic field, cutting the traveling wave magnetic field, and generating electromagnetic force. When the traveling wave magnetic field is opposite to the relative motion direction, the electromagnetic force blocks the relative motion between the energizing member and the sensing member, that is, additional damping is applied to the buffer post inner cylinder 205.
在着陆缓冲过程中，可通过位移传感器实时采集缓冲支柱的运动信号，包括但不限于压缩行程、速度和加速度大小，这些运动信号被反馈至线圈电流控制单元(未示出)中，控制单元通过计算判断油气缓冲支柱所承受的载荷及外部冲击的状态，实时计算通过绕组204的电流的幅值和相位，产生额外的阻尼力进行补偿。在缓冲压缩初期，缓冲支柱刚度较低，如果外界冲击载荷过大，此时绕组204可产生额外的排斥力增加缓冲支柱刚度并提高初期的缓冲效率；在整个缓冲过程中，绕组204额外产生的阻尼力可以减轻油气缓冲支柱的负载，减少油气腔的压力，增加结构的可靠性和安全性；在压缩不足的情况下，电磁线圈204也可通过改变电流方向来增大压缩量，对飞机轮载信号的产生起到一定的辅助作用。During the landing buffering process, the motion signals of the buffer strut can be collected in real time by the displacement sensor, including but not limited to the compression stroke, velocity and acceleration magnitude, and these motion signals are fed back into the coil current control unit (not shown), and the control unit passes Calculate the state of the load and external impact of the oil and gas buffer strut, calculate the amplitude and phase of the current through the winding 204 in real time, and generate additional damping force to compensate. In the initial stage of buffer compression, the buffer strut is low in rigidity. If the external impact load is too large, the winding 204 can generate additional repulsive force to increase the buffer strut stiffness and improve the initial buffering efficiency; during the entire buffering process, the winding 204 is additionally generated. The damping force can reduce the load of the oil and gas buffer strut, reduce the pressure of the oil and gas chamber, and increase the reliability and safety of the structure; in the case of insufficient compression, the electromagnetic coil 204 can also increase the compression amount by changing the current direction to the aircraft wheel. The generation of the carrier signal plays a certain auxiliary role.
根据本发明的半主动的控制方式有利于适应更加复杂的外界情况，提高飞机着陆缓冲效率，使用良好的控制算法可以进一步增加飞机着陆过程的安全性和舒适性。The semi-active control mode according to the present invention is advantageous for adapting to more complicated external conditions, improving the landing buffer efficiency of the aircraft, and using a good control algorithm can further increase the safety and comfort of the aircraft landing process.
利用电磁产生额外的缓冲阻力，可大大拓展原有缓冲支柱结构的缓冲范围，增加对起落架外部环境的适应性，可使负载曲线趋于平稳，削弱负载变化的振幅，提高缓冲支柱的安全可靠性。The use of electromagnetic to generate additional cushioning resistance can greatly expand the buffer range of the original buffer strut structure, increase the adaptability to the external environment of the landing gear, make the load curve tend to be stable, weaken the amplitude of the load change, and improve the safety and reliability of the buffer strut. Sex.
本发明的技术内容及技术特点已揭示如上，应当理解的是，上述实施方式存在许多修改方式，这些方式对相关领域技术人员来说是很明显的。这些修改/变型落入本发明的相关领域中，也应当包括在所附的权利要求的范围中。 The technical content and technical features of the present invention have been disclosed above, and it should be understood that there are many modifications of the above-described embodiments, which will be apparent to those skilled in the art. Such modifications/modifications are intended to fall within the scope of the invention and the scope of the appended claims.

Claims (8)

  1. 起落架缓冲支柱的缓冲装置，所述缓冲支柱包括外筒和能够沿所述外筒的内壁移动的内筒，其特征在于，所述缓冲装置包括：A cushioning device for the landing gear cushioning strut, the buffering strut comprising an outer cylinder and an inner cylinder movable along an inner wall of the outer cylinder, wherein the buffering device comprises:
    至少一个激励部件，其布置于所述缓冲支柱的外筒壁内侧；At least one excitation component disposed on an inner side of the outer cylinder wall of the buffer strut;
    至少一个感应部件，其布置于所述缓冲支柱的内筒中以响应于所述激励部件的激励，使得所述内筒沿所述缓冲支柱的外筒移动产生缓冲阻尼；At least one inductive component disposed in an inner barrel of the buffer strut to cause buffer damping of the inner cylinder to move along an outer cylinder of the buffer strut in response to excitation of the energizing strut;
    控制单元，其根据所述缓冲支柱的运动信号实时控制所述激励部件；以及a control unit that controls the excitation component in real time according to a motion signal of the buffer strut;
    感测部件，其布置于所述缓冲支柱下端以检测所述缓冲支柱的运动信号并将所述运动信号反馈至所述控制单元。A sensing component disposed at a lower end of the buffer post to detect a motion signal of the buffer post and to feed back the motion signal to the control unit.
  2. 根据权利要求1所述的起落架缓冲支柱的缓冲装置，其特征在于，所述缓冲装置的激励部件为围绕所述缓冲支柱的外筒壁内侧布置的单一部件或对称设置的多个部件。A cushioning device for a landing gear cushioning strut according to claim 1, wherein the energizing means of the cushioning means is a single member or a plurality of symmetrically disposed members disposed around the inner side of the outer cylinder wall of the cushioning strut.
  3. 根据权利要求2所述的起落架缓冲支柱的缓冲装置，其特征在于，所述激励部件由硅钢片、三相绕组组成，所述控制单元为绕组电流控制单元。A cushioning device for a landing gear cushioning strut according to claim 2, wherein said energizing means is composed of a silicon steel sheet, a three-phase winding, and said control unit is a winding current control unit.
  4. 根据权利要求3所述的起落架缓冲支柱的缓冲装置，其特征在于，所述感应部件包括感应合金。A cushioning device for a landing gear cushioning strut according to claim 3, wherein said inductive component comprises an inductive alloy.
  5. 根据权利要求4所述的起落架缓冲支柱的缓冲装置，其特征在于，所述感应合金包括铝铁合金或铜铁合金。A cushioning device for a landing gear cushioning strut according to claim 4, wherein said induction alloy comprises an aluminum-iron alloy or a copper-iron alloy.
  6. 根据权利要求4所述的起落架缓冲支柱的缓冲装置，其特征在于，所述感测部件包括位移传感器。A cushioning device for a landing gear cushioning strut according to claim 4, wherein the sensing component comprises a displacement sensor.
  7. 根据权利要求1至6任一所述的起落架缓冲支柱的缓冲装置在油气缓冲支柱中的使用方法，包括：A method of using a cushioning device for a landing gear cushioning strut according to any one of claims 1 to 6 in an oil and gas buffering strut, comprising:
    a、感测部件检测缓冲支柱的运动信号，并将运动信号反馈至控制单元；a, the sensing component detects a motion signal of the buffer strut and feeds the motion signal to the control unit;
    b、控制单元根据所述感测部件反馈的运动信号，计算并判断缓冲支柱所承受的载荷及外部冲击状态，实时控制激励部件产生对感 应部件的激励；b. The control unit calculates and determines the load and the external impact state of the buffer strut according to the motion signal fed back by the sensing component, and controls the excitation component to generate a sense of right in real time. Incentives for components;
    c、感应部件响应于所述激励促使缓冲支柱的内筒沿外筒移动，以产生额外的缓冲阻尼。c. The inductive component urges the inner barrel of the buffer strut to move along the outer barrel in response to the energizing to create additional cushioning damping.
  8. 根据权利要求7所述的缓冲装置在油气缓冲支柱中的使用方法，其特征在于，所述运动信号包括压缩行程、速度和加速度大小，所述控制单元根据缓冲支柱的压缩行程、速度和加速度大小的改变而实时改变对所述激励部件的控制电流的幅值及相位。 The method of using a buffer device according to claim 7, wherein the motion signal comprises a compression stroke, a speed and an acceleration magnitude, and the control unit is based on a compression stroke, a speed and an acceleration of the buffer strut. The change and change the amplitude and phase of the control current to the excitation component in real time.
PCT/CN2015/093053 2014-10-29 2015-10-28 Buffering apparatus for landing gear buffering strut WO2016066094A1 (en)

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