Rapid measurement system for emergency cabin opening angle of airplane cabin door system

Abstract

The utility model provides an emergency cabin opening angle rapid measuring system of an airplane cabin door system, which comprises a microswitch and a tilt angle sensor which are arranged on a cabin door, and a tilt angle sensor and a tilt angle digital display instrument. The tilt angle sensor can collect cabin door rotation angle information and upload the information to the tilt angle digital display instrument; when the cabin door rotates to a specified emergency cabin opening angle, the converter converts an emergency launching signal of an airplane into a locking signal which can be identified by the inclination angle digital display instrument and transmits the locking signal to the inclination angle digital display instrument, and the locking signal quickly disconnects the inclination angle sensor to transmit the signal. The inclination angle digital display instrument displays the rotation angle of the cabin door at the moment of disconnection in real time, so that an operator can conveniently and quickly read the rotation angle of the cabin door, the measurement result is accurate, repeated measurement work caused by human factors is avoided, and the working efficiency is greatly improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of angle measurement and adjustment, and in particular relates to a rapid angle measurement system for emergency cabin opening of an aircraft cabin door system. Background Art

[0002] The emergency hatch door opening angle refers to the specified angle that the bomb bay door is required to turn to during emergency release of the bomb bay, so as to ensure that the items can be released quickly and effectively without hitting the hatch door. In aviation repair, the emergency hatch door opening angle is an important indicator that must be measured. The hatch door opening process is uncontrolled, but the closing process is controllable, so the hatch door opening angle during emergency release can be measured in reverse. At present, an optical quadrant is usually used for measurement. The specific method is: close the hatch door by manual hand-cranking. When the hatch door moves to the point where the micro switch turns from on to off, stop shaking manually, place the optical quadrant on the flat surface of the right hatch door, adjust the bubble of the optical quadrant to the center position, and then record the data of the optical quadrant. However, when using an optical quadrant for measurement, firstly, the human ear is needed to judge the on and off of the micro switch. The sound of the hatch door is noisy and the sound of the micro switch is small, which is not conducive to the timely judgment of the human ear. Secondly, due to the structure of the optical quadrant itself, it takes a long time to adjust the horizontal bubble, and the hatch door will slowly open under the action of gravity, and the accuracy of the measured angle is not high. Thirdly, since the optical quadrant cannot be fixed on the inner surface of the hatch door, the reference surface of each measurement is inconsistent, resulting in inconsistent initial angles and deviations in the measured angles each time. Therefore, the use of an optical quadrant for measurement results in a slow process, many repeated measurements, and low efficiency. Utility Model Content

[0003] The utility model aims to solve the problems of low efficiency and inaccurate measurement of the emergency angle of a cabin door using an optical quadrant, and to provide a rapid measurement system for the emergency opening angle of an aircraft cabin door system.

[0004] To achieve the above purpose, the technical solution provided by the utility model is:

[0005] A rapid measurement system for emergency opening angle of an aircraft cabin door system, the aircraft cabin door system comprising an aircraft wall panel, a drum wheel located in the middle of the aircraft wall panel and two cabin doors located on both sides of the aircraft wall panel, the drum wheel is used to drive the cabin doors to rotate; the rapid measurement system comprises a micro switch, a pressure-actuated component, a converter, a self-locking inclination digital display and an inclination sensor;

[0006] When the door needs to be opened for delivery, the aircraft control system outputs an emergency delivery signal according to the delivery instruction, and the emergency delivery signal is a DC voltage signal;

[0007] The inclination sensor is installed on the surface of the hatch door, and is used to collect angle information when the hatch door is folded or opened and upload it to the self-locking inclination display;

[0008] The pressing assembly and the micro switch are both fixed on the aircraft wall panel and are located between the two cabin doors; the micro switch is close to the pressing assembly, and when the cabin door is rotated to open, the pressing assembly can move under the drive of the drum wheel, and can trigger the micro switch to turn on when the cabin door is fully opened;

[0009] The normally open end of the micro switch is connected to the positive input terminal of the converter, and the negative input terminal of the converter is connected to the ground return terminal of the aircraft cabin door; the output end of the converter is connected to the circuit module of the self-locking inclination digital display;

[0010] When the hatch is closed, the normally closed end of the micro switch is connected to the common end; when the hatch is opened to a set angle, the common end of the micro switch is connected to the normally open end; the converter can convert the emergency release signal into a digital signal and transmit it to the self-locking inclination digital display, cut off the inclination sensor from continuing to transmit angle information, lock and display the hatch opening angle at the moment of disconnection.

[0011] Further, the converter includes an ADC quantization encoding circuit and a sampling and holding circuit connected in series;

[0012] The ADC quantization encoding circuit is used to convert the voltage signal input through the micro switch into a digital signal, so that the digital signal on the inclination digital display is maintained when the signal is cut off;

[0013] The sampling and holding circuit is used to maintain the stability of the voltage signal during the process of converting the voltage signal into a digital signal.

[0014] Furthermore, the sampling and holding circuit includes an analog switch and a capacitor, the analog switch input end is connected to the normally open end of the micro switch, the analog switch output end is connected to one end of the capacitor, and the other end of the capacitor is connected to the ground return end of the hatch.

[0015] Furthermore, the pressing assembly comprises a bracket, a pull rod and a pressing block, wherein the bracket is fixed on the aircraft wall panel, and the pull rod is installed on the bracket; when the cabin door rotates, the pull rod can move up and down along the bracket under the push of the drum wheel;

[0016] The pressing block is fixed at the bottom of the pull rod, and is used to press the roller of the micro switch when the cabin door is opened to a set angle, so that the common end of the micro switch is connected to the normally open end.

[0017] The advantages of the utility model are:

[0018] 1. The measuring system of the utility model is provided by installing a pressing assembly and a micro switch on the wall panel of the aircraft, and installing a tilt sensor on the cabin door; the tilt sensor can collect the cabin door rotation angle information and upload it to the tilt digital display for display; the micro switch is connected to the tilt digital display through a converter, and when the cabin door is rotated to a specified emergency cabin opening angle, the converter converts the emergency release signal of the aircraft into a locking signal recognizable by the tilt digital display and transmits it to the tilt digital display, the locking signal quickly disconnects the transmission signal of the tilt sensor, and the tilt digital display displays the cabin door rotation angle at the moment of disconnection in real time, so that the operator can conveniently and quickly read the angle of the cabin door.

[0019] 2. In the utility model, when the micro switch is turned on, the converter immediately converts and transmits the aircraft emergency signal, so that the locking signal instantly disconnects the subsequent signal transmission of the tilt sensor, so that the angle value displayed by the tilt digital display at the moment of locking is the emergency opening angle of the aircraft when the aircraft control system issues a release command. The measurement using the utility model device only requires 2 people to complete the measurement within 20 minutes, avoiding repeated measurement work caused by human factors, greatly improving work efficiency, and the measurement results are accurate. The existing method requires 4 people to complete the measurement in about 120 minutes.

[0020] 3. In the utility model, a compact and lightweight inclination sensor is used to replace the optical quadrant used in the traditional technology. The inclination sensor can be fixed on the inner surface of the cabin door by ordinary means such as double-sided adhesive tape or adhesive tape, thereby ensuring the consistency of the initial angle in each measurement. The inclination sensor is connected to the inclination digital display by a wire, so that the sensor can synchronize the collected cabin door rotation angle information to the inclination digital display in real time, which is convenient for the operator to read the angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a block diagram of the utility model of an emergency cabin opening angle rapid measurement system for an aircraft cabin door system;

[0022] Figure 2 yes Figure 1 Circuit diagram of the converter;

[0023] Figure 3 This is a schematic diagram of the coordinated installation of the micro switch, pressure-actuated assembly and hatch system.

[0024] In the figure: 1- micro switch, 2- converter, 3- self-locking inclination digital display, 4- inclination sensor, 5- cable, 6- emergency release signal, 7- pressing assembly, 8- aircraft wall panel, 9- drum wheel, 10- left cabin door, 11- right cabin door. DETAILED DESCRIPTION

[0025] The embodiments of the present invention are described in detail below. The embodiments are exemplary and intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0026] Reference Figure 1-Figure 3 A rapid measurement system for the emergency opening angle of an aircraft cabin door system includes a micro switch 1, a pressure-actuated component, a converter 2, a self-locking inclination digital display 3 and an inclination sensor 4.

[0027] The aircraft door system comprises an aircraft panel 8, a drum 9, a left door 10 and a right door 11. The drum 9 is installed in the middle of the aircraft panel and is used to drive the left door 10 and the right door 11 located on both sides of the aircraft panel to rotate.

[0028] When it is necessary to open the cabin door for a delivery operation, the aircraft control system outputs an emergency delivery signal 6 according to the delivery instruction, and the emergency delivery signal 6 is a DC voltage signal.

[0029] The inclination sensor 4 is installed on the surface of the door and connected to the self-locking inclination display 3 via a cable, so as to collect the angle information of the door when it is folded or opened in real time and upload it to the self-locking inclination display 3 synchronously.

[0030] The pressure assembly and the micro switch are both fixed on the aircraft wall panel and are located between the two cabin doors. The micro switch is close to the pressure assembly. When the cabin door is rotated to open, the pressure assembly can move under the drive of the drum wheel, and can press the micro switch to turn on the micro switch when the cabin door is fully opened. The connection and disconnection of the micro switch 1 is controlled by the movement of the cabin door. When the cabin door is closed, the common end o of the micro switch 1 is connected to the normally closed section cb and disconnected from the normally open end ck; when the cabin door is opened and rotated through a set angle, the pressure assembly connected to the cabin door moves with the rotation of the cabin door, pressing the roller on the micro switch and disconnecting the common end o on the micro switch from the normally closed end cb and connecting to the normally open end ck.

[0031] The pressing assembly includes a bracket, a pull rod and a pressure block. The bracket is fixed on the aircraft wall panel 8, and the pull rod is installed on the bracket. When the cabin door rotates, the pull rod can move up and down along the bracket under the push of the drum wheel 9. The pressure block is fixed at the bottom of the pull rod and is used to press the roller of the micro switch when the cabin door is opened to a set angle, so that the common end of the micro switch is connected to the normally open end.

[0032] The normally open end of the micro switch 1 is connected to the positive input terminal of the converter 2, and the negative input terminal of the converter 2 is connected to the ground return terminal of the aircraft cabin door through a cable 5; the output end of the converter is connected to the circuit module of the self-locking inclination digital display 3.

[0033] When the hatch is closed, the normally closed end cb of the micro switch is connected to the common end; when the hatch is opened to a set angle, the common end o of the micro switch is connected to the normally open end ck; the converter 2 can convert the emergency release signal 6 into a digital signal and transmit it to the self-locking inclination angle digital display 3, cutting off the inclination sensor from continuing to transmit angle information, and the self-locking inclination angle digital display 3 locks and displays the hatch opening angle at the time of disconnection, which is the hatch emergency opening angle.

[0034] Reference Figure 2 The converter includes a sampling and holding circuit and an ADC quantization and coding circuit connected in series; the ADC quantization and coding circuit is used to convert the voltage signal into a digital signal so that the digital signal on the inclinometer is maintained when the signal is cut off. The sampling and holding circuit is used to maintain the stability of the voltage signal during the process of converting the voltage signal into a digital signal.

[0035] The sampling and holding circuit includes an analog switch and a capacitor. The input end of the analog switch is connected to the normally open end of the micro switch. The output end of the analog switch is connected to one end of the capacitor. The other end of the capacitor is connected to the ground return end of the hatch.

[0036] When using the utility model for measurement, first install the inclination sensor 1 on the surface of the hatch, and at the same time retract the hatch. The inclination sensor 1 collects the angle information of the hatch and transmits it to the self-locking inclination digital display 3. Press the reset key of the inclination digital display to perform the zeroing operation, and set the angle of the initial position of the hatch to zero. The angle value displayed by the inclination digital display 2 is the angle of the hatch turned.

[0037] When the aircraft control system sends out an emergency delivery signal according to the emergency delivery instruction, the cabin door starts to rotate, and the inclination sensor 1 uploads the collected cabin door rotation angle information to the self-locking inclination digital display 3 in real time. The angle displayed by the self-locking inclination digital display is the angle of the cabin door. When the cabin door is opened to a preset angle, the pressing block of the pressing assembly connected to the cabin door contacts the roller of the micro switch, and the pressing block presses the micro switch, so that the normally closed end cb of the micro switch is disconnected from the common end o, and the common end is connected to the normally open end ck. The emergency delivery signal 6 is transmitted to the converter 2 through the normally open end ck of the micro switch. The converter 2 quickly converts the received emergency delivery signal into a digital signal recognizable by the self-locking inclination digital display and outputs it to the self-locking inclination digital display. The converted digital signal is used as a locking signal to disconnect the inclination sensor from transmitting information to the inclination digital display, and lock the current angle value. The locked angle value is the cabin door emergency delivery opening angle. The measured cabin door emergency delivery opening angle is compared with the specified cabin door emergency opening angle to determine whether the cabin door rotation angle meets the design requirements.

[0038] If the measured hatch door emergency opening angle is less than the specified value, rotate the adjusting screw on the microswitch counterclockwise to increase the connection stroke of the microswitch, thereby extending the connection time of the microswitch and increasing the hatch door emergency opening angle; if the measured hatch door emergency opening angle is greater than the specified value, rotate the adjusting screw on the microswitch clockwise to reduce the connection stroke of the microswitch, thereby shortening the connection time of the microswitch and reducing the hatch door emergency opening angle.

[0039] The above description is only a specific implementation mode of the present utility model, but the protection scope of the present utility model is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present utility model, and these modifications or substitutions should be included in the protection scope of the present utility model.

Claims

1. A rapid measurement system for emergency opening angle of an aircraft cabin door system, the aircraft cabin door system comprising an aircraft panel, a drum wheel located in the middle of the aircraft panel, and two cabin doors located on both sides of the aircraft panel, the drum wheel is used to drive the cabin doors to rotate; characterized in that: The rapid measurement system includes a micro switch, a pressure-actuated assembly, a converter, a self-locking inclination digital display and an inclination sensor; When the door needs to be opened for delivery, the aircraft control system outputs an emergency delivery signal according to the delivery instruction, and the emergency delivery signal is a DC voltage signal; The inclination sensor is installed on the surface of the hatch door, and is used to collect angle information when the hatch door is folded or opened and upload it to the self-locking inclination display; The pressing assembly and the micro switch are both fixed on the aircraft wall panel and are located between the two cabin doors; the micro switch is close to the pressing assembly, and when the cabin door is rotated to open, the pressing assembly can move under the drive of the drum wheel, and can trigger the micro switch to turn on when the cabin door is fully opened; The normally open end of the micro switch is connected to the positive input terminal of the converter, and the negative input terminal of the converter is connected to the ground return terminal of the aircraft cabin door; the output end of the converter is connected to the circuit module of the self-locking inclination digital display; When the hatch is closed, the normally closed end of the micro switch is connected to the common end; when the hatch is opened to a set angle, the common end of the micro switch is connected to the normally open end; the converter can convert the emergency release signal into a digital signal and transmit it to the self-locking inclination digital display, cut off the inclination sensor from continuing to transmit angle information, lock and display the hatch opening angle at the moment of disconnection.

2. The aircraft cabin door system emergency opening angle rapid measurement system according to claim 1, characterized in that: The converter includes an ADC quantization encoding circuit and a sampling and holding circuit connected in series; The ADC quantization encoding circuit is used to convert the voltage signal input through the micro switch into a digital signal, so that the digital signal on the inclination digital display is maintained when the signal is cut off; The sampling and holding circuit is used to maintain the stability of the voltage signal during the process of converting the voltage signal into a digital signal.

3. The aircraft cabin door system emergency opening angle rapid measurement system according to claim 2, characterized in that: The sampling and holding circuit includes an analog switch and a capacitor. The input end of the analog switch is connected to the normally open end of the micro switch, the output end of the analog switch is connected to one end of the capacitor, and the other end of the capacitor is connected to the ground return end of the hatch.

4. The aircraft cabin door system emergency opening angle rapid measurement system according to claim 1 or 3, characterized in that: The pressing assembly comprises a bracket, a pull rod and a pressing block, wherein the bracket is fixed on the aircraft wall panel, and the pull rod is installed on the bracket; when the cabin door rotates, the pull rod can move up and down along the bracket under the push of the drum wheel; The pressing block is fixed at the bottom of the pull rod, and is used to press the roller of the micro switch when the cabin door is opened to a set angle, so that the common end of the micro switch is connected to the normally open end.

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