阅读说明：本技术 飞机的起落架健康管理系统 (Landing gear health management system for aircraft ) 是由 孙魁 杨弘 李冰 董进 和建增 欧思凡 于 2021-10-29 设计创作，主要内容包括：本发明公开了一种飞机的起落架健康管理系统,该系统包括：起落架缓冲器压力传感器,其布置于缓冲器上并能够检测缓冲器的内部气腔的压力；车架定位器压力传感器,其布置于车架定位器上并能够检测车架定位器的内部气腔的压力；轮胎压力传感器,其布置于机轮并能够检测机轮的轮胎压力；机载传感数据采集装置及手持式终端,二者被配置为能够彼此独立地通信连接至各个压力传感器,从而自各个压力传感器获取并存储其检测到的压力数据。根据本发明的飞机的起落架健康管理系统,能够帮助实现可靠且高效的对于飞机起落架装置的全面检查,并显著减轻勤务人员的工作负担,缩短飞机的过站时间。(The invention discloses a landing gear health management system of an airplane, which comprises: a landing gear buffer pressure sensor disposed on the buffer and capable of detecting a pressure of an internal air cavity of the buffer; the frame positioner pressure sensor is arranged on the frame positioner and can detect the pressure of an internal air cavity of the frame positioner; a tire pressure sensor disposed on the wheel and capable of detecting a tire pressure of the wheel; the handheld terminal comprises an onboard sensing data acquisition device and a handheld terminal, wherein the onboard sensing data acquisition device and the handheld terminal are configured to be capable of being independently connected with each pressure sensor in a communication mode, so that pressure data detected by each pressure sensor can be acquired and stored. The undercarriage health management system of the airplane can help to realize reliable and efficient comprehensive inspection of the undercarriage device of the airplane, remarkably reduce the workload of service personnel and shorten the station-passing time of the airplane.)

1. A landing gear health management system for an aircraft, the aircraft including a landing gear arrangement including a bumper, a bogie frame with a frame locator and wheels, the landing gear health management system comprising:

a landing gear bumper pressure sensor disposed on the bumper and configured to detect a pressure of an internal air cavity of the bumper;

a frame locator pressure sensor disposed on the frame locator and configured to detect a pressure of an interior air cavity of the frame locator;

a tire pressure sensor disposed on the wheel and configured to detect a tire pressure of the wheel;

the pressure sensor comprises an onboard sensing data acquisition device and a handheld terminal, wherein the onboard sensing data acquisition device and the handheld terminal are configured to be capable of being independently connected with each pressure sensor in a communication mode, so that pressure data detected by each pressure sensor can be acquired and stored.

2. The landing gear health management system of an aircraft according to claim 1, wherein the onboard sensory data collection device and the hand-held terminal are each provided with a first bluetooth module, and each of the pressure sensors is provided with a second bluetooth module, such that the onboard sensory data collection device and the hand-held terminal can wirelessly communicate with the pressure sensor via the first bluetooth module and the second bluetooth module.

3. The landing gear health management system for an aircraft according to claim 1, wherein the onboard sensory data collection device and the hand-held terminal are respectively provided with a first bluetooth module, the landing gear health management system further comprising:

and the third Bluetooth module is in communication connection with the pressure sensor through a data transmission line so as to acquire pressure data detected by the pressure sensor, and the pressure data is sent to the airborne sensing data acquisition device and the handheld terminal through wireless communication between the third Bluetooth module and the first Bluetooth module.

4. An aircraft landing gear health management system according to claim 3, wherein the third Bluetooth module is secured in the landing gear arrangement between the pressure sensors.

5. An aircraft landing gear health management system according to claim 4, wherein the bumpers comprise longitudinal shock struts.

6. An aircraft landing gear health management system according to claim 5, wherein the landing gear bumper pressure sensor is disposed at an upper portion of the longitudinal shock strut, and the third Bluetooth module is secured to a lower portion of the longitudinal shock strut or near a lower end of the longitudinal shock strut.

7. An aircraft landing gear health management system according to claim 1, wherein each of the pressure sensors is provided with a battery, and each of the pressure sensors is further configured to be able to send sensor information data to the on-board sensory data collection device or the hand-held terminal, the sensor information data including a sensor device number and a battery level and/or a battery life.

Technical Field

The invention relates to an undercarriage device of an aircraft, in particular to an undercarriage health management system of the aircraft.

Background

Whether the landing gear device of the aircraft can work normally is an important factor related to the flight safety of the aircraft. Typically, the landing gear arrangement is inspected during ground maintenance operations. Currently, inspection is generally performed by means of manual visual inspection, tire pressure measurement, electronic meter inspection, and the like.

However, the above conventional inspections of aircraft landing gear still have practical limitations. For example, in view of the construction of the landing gear device, the bumper included therein functions to support the aircraft by the oil and gas inside, and the bogie positioner for the bogie type landing gear functions to position the bogie by the oil and gas inside. The pressure at these components should also be checked to reliably determine if the aircraft is capable of normal flight. Otherwise, it indicates that a remedial or maintenance operation is required for the components such as the bumper, the frame aligner and the tire.

Currently, the above-described full inspection of landing gear arrangements relies heavily on the ground service personnel to observe by manual visual means and to find possible hazards, then additional dedicated equipment is additionally employed for pressure measurement for further confirmation, and the ground service personnel need to be close to the relevant position of the landing gear during the inspection to achieve a suitable viewing angle. Such inspections are therefore extremely inconvenient and impose a considerable burden on the service personnel, as well as increase the time of passing the aircraft.

Accordingly, there is a need to provide a new landing gear health management system for an aircraft that at least partially alleviates or solves the above-mentioned problems and disadvantages of the existing solutions

Disclosure of Invention

The invention aims to overcome the defect that the prior art has obvious inspection limitation on the undercarriage by a relatively efficient inspection mode aiming at the defect that the comprehensive inspection of the undercarriage device relies on the observation of ground service personnel in a manual visual mode to a great extent, and provides a novel undercarriage health management system of an airplane.

The invention solves the technical problems through the following technical scheme:

the invention provides a landing gear health management system of an airplane, wherein the airplane comprises a landing gear device, the landing gear device comprises a buffer, a small car frame with a frame positioner and an airplane wheel, and the landing gear health management system is characterized by comprising:

a landing gear bumper pressure sensor disposed on the bumper and configured to detect a pressure of an internal air cavity of the bumper;

a frame locator pressure sensor disposed on the frame locator and configured to detect a pressure of an interior air cavity of the frame locator;

a tire pressure sensor disposed on the wheel and configured to detect a tire pressure of the wheel;

the pressure sensor comprises an onboard sensing data acquisition device and a handheld terminal, wherein the onboard sensing data acquisition device and the handheld terminal are configured to be capable of being independently connected with each pressure sensor in a communication mode, so that pressure data detected by each pressure sensor can be acquired and stored.

According to one embodiment of the invention, the airborne sensing data acquisition device and the handheld terminal are respectively provided with a first bluetooth module, and each pressure sensor is respectively provided with a second bluetooth module, so that the airborne sensing data acquisition device and the handheld terminal can wirelessly communicate with the pressure sensor through the first bluetooth module and the second bluetooth module.

According to an embodiment of the present invention, the airborne sensing data collecting device and the handheld terminal are respectively provided with a first bluetooth module, and the undercarriage health management system further includes:

and the third Bluetooth module is in communication connection with the pressure sensor through a data transmission line so as to acquire pressure data detected by the pressure sensor, and the pressure data is sent to the airborne sensing data acquisition device and the handheld terminal through wireless communication between the third Bluetooth module and the first Bluetooth module.

According to one embodiment of the invention, the third bluetooth module is fixed in the landing gear device between the pressure sensors.

According to one embodiment of the invention, the bumper comprises longitudinal cushioning struts.

According to one embodiment of the invention, the landing gear bumper pressure sensor is arranged at the upper part of the longitudinal cushioning strut, and the third bluetooth module is fixed at the lower part of the longitudinal cushioning strut or near the lower end of the longitudinal cushioning strut.

According to one embodiment of the present invention, each of the pressure sensors is provided with a battery, and each of the pressure sensors is further configured to send sensor information data to the onboard sensory data collection device or the handheld terminal, wherein the sensor information data includes a sensor device number and a battery level and/or a battery life.

On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.

The positive progress effects of the invention are as follows:

according to the undercarriage health management system of the airplane, the pressure data of a plurality of key positions on the undercarriage can be efficiently and reliably collected in two modes of the airborne collecting device and the portable terminal device which can be held by ground service personnel, so that the undercarriage device can be reliably and efficiently comprehensively checked, the workload of the service personnel is obviously reduced, and the station passing time of the airplane is shortened.

Drawings

FIG. 1 is a schematic view of a landing gear health management system for an aircraft according to a preferred embodiment of the present invention.

Figure 2 is a schematic structural view of a landing gear arrangement for deploying a landing gear health management system of an aircraft according to a preferred embodiment of the present invention.

Detailed Description

The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, is intended to be illustrative, and not restrictive, and it is intended that all such modifications and equivalents be included within the scope of the present invention.

In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", and the like, are used with reference to the orientation as illustrated in the drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.

Referring to figure 2, the embodiments of the landing gear health management system for an aircraft described below may be adapted for use with a typical aircraft landing gear arrangement, which generally comprises a bumper 1, a bogie frame with a frame locator 2, and wheels.

Referring to fig. 1-2, a landing gear health management system for an aircraft according to a preferred embodiment of the present invention includes a landing gear bumper pressure sensor, a frame locator pressure sensor, and a tire pressure sensor.

Wherein the landing gear bumper pressure sensor is arranged on the bumper 1 and is configured to detect the pressure of the inner air cavity of the bumper 1. The pressure may be a longitudinal pressure experienced by the bumper 1 in a direction substantially perpendicular to the ground. The frame positioner pressure sensor is disposed on the frame positioner 2 and is configured to be able to detect the pressure of the internal air chamber of the frame positioner 2. The tire pressure sensor is disposed on the wheel and is configured to detect a tire pressure of the wheel. It will be appreciated that the internal air chambers are respectively configured to enable the conditions of the shock absorber 1 and the frame positioner 2 to be adjusted by means of fluid pressure,

The landing gear health management system further comprises an onboard sensing data acquisition device and a handheld terminal, wherein the onboard sensing data acquisition device and the handheld terminal are configured to be capable of being independently connected with each pressure sensor in a communication mode, so that pressure data detected by each pressure sensor can be acquired and stored.

It will be appreciated that the on-board sensory data collection device may further provide the relevant pressure data to the on-board maintenance system, such that the status of the landing gear device is monitored in real time by the on-board maintenance system. On the other hand, during service maintenance, the ground crew can directly read the buffer pressure, the frame pressure and the tire pressure through the handheld terminal to more reliably and efficiently inspect the landing gear device. In addition, based on the stored pressure data during long-term operation, further health management/monitoring of the landing gear arrangement and further data analysis based on the long-term monitoring data may be achieved.

According to some preferred embodiments of the present invention, the onboard sensing data collection device and the handheld terminal are respectively provided with a first bluetooth module (i.e., two first bluetooth modules in total), and each pressure sensor is respectively provided with a second bluetooth module (i.e., three first bluetooth modules in total), so that the onboard sensing data collection device and the handheld terminal can wirelessly communicate with the pressure sensor via the first bluetooth module and the second bluetooth module.

Therefore, a distributed scheme can be realized, and each pressure sensor can independently provide detection data to the onboard sensing data acquisition device and the handheld terminal in a Bluetooth communication mode through the Bluetooth module in real time.

According to some alternative preferred embodiments of the invention, the airborne sensing data acquisition device and the handheld terminal are respectively provided with the first bluetooth module, but the landing gear health management system further comprises a single third bluetooth module shared by the three pressure sensors, wherein the third bluetooth module is in communication connection with the pressure sensors through data transmission lines so as to acquire the pressure data detected by the pressure sensors and transmit the pressure data to the airborne sensing data acquisition device and the handheld terminal through wireless communication with the first bluetooth module.

Thereby, a solution is achieved where the pressure sensors share a single third bluetooth module, which may be suitably arranged such that the distance between it and the three pressure sensors is relatively short, in order to shorten the total length of the required connection cable. For example, a third bluetooth module may be secured in the landing gear arrangement between the three pressure sensors. Moreover, compared with the preferred embodiment, the scheme not only reduces the number of required Bluetooth modules, but also reduces the power consumption required by Bluetooth communication.

Further preferably, the bumper comprises a longitudinal cushioning strut, and the landing gear bumper pressure sensor is arranged at an upper portion of the longitudinal cushioning strut, and the third bluetooth module is fixed at a lower portion of the longitudinal cushioning strut or near a lower end of the longitudinal cushioning strut.

Thus, not only is the total length of connection cable required between the single third bluetooth module and the three pressure sensors relatively short, but the connection cable will be arranged or fixed in close proximity to the original longitudinally extending members of the landing gear, such as the longitudinal shock absorber strut, and the original transversely extending members, such as the bogie frame and its positioner 2, as much as possible.

According to some preferred embodiments of the present invention, each of the pressure sensors is provided with a battery, and each of the pressure sensors is further configured to be able to send sensor information data to the onboard sensory data collection device or the handheld terminal, the sensor information data including a sensor device number and a battery level and/or a battery life.

Thereby, the work load of ground service maintenance personnel to inspect the landing gear device can be further reduced.

According to the undercarriage health management system of the airplane, pressure data of a plurality of key positions on the undercarriage can be efficiently and reliably collected in two modes of the airborne collecting device and the portable terminal device which can be held by the ground service personnel, so that the undercarriage device can be reliably and efficiently comprehensively checked, the workload of the service personnel is obviously reduced, and the station passing time of the airplane is shortened.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.