Aircraft movable part ground verification test follow-up heating device

Abstract

The invention belongs to the technical field of ground verification tests of aircraft movable parts, and particularly relates to a follow-up heating device for ground verification tests of aircraft movable parts, which can keep the relative position of an electric heating element and a movable part unchanged in the test, so that accurate control of temperature distribution on the movable part can be ensured, and the test efficiency is improved. The thermal environment of the movable part in flight is effectively restored, and a reliable test result is obtained.

Description

Technical Field

[0001] This application belongs to the technical field of ground verification tests for movable components of aircraft, and specifically relates to a follow-up heating device for ground verification tests of movable components of aircraft. Background Art

[0002] During the flight of hypersonic aircraft, aerodynamic heating has a significant impact on their structural strength. In ground test verification, to obtain accurate test results, it is necessary to accurately control the temperature distribution on the structure.

[0003] There are a large number of movable components in the aircraft, such as moving wing surfaces. During high-speed flight, due to the effect of aerodynamic heating, the drive structure of the wing surface movement will not only have thermal mismatch with other components of the aircraft, but also the internal electronic control system that controls the wing surface deflection is in a harsh thermal environment and is prone to functional failure.

[0004] Due to the continuous change of the position of the movable component, it is difficult to accurately control the temperature distribution on it during the ground verification test, and it is impossible to effectively restore the thermal environment in which it is located during flight, resulting in difficulty in obtaining reliable test results.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide a follow-up heating device for ground verification tests of movable components of aircraft to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] A follow-up heating device for ground verification tests of movable components of aircraft includes an electric heating element, a heating bracket, a temperature controller, a speed reducer, a servo motor, a PLC controller, and a host computer;

[0009] The electric heating element is arranged on the heating bracket and is connected to the temperature controller through a cable;

[0010] The temperature controller is connected to a movable component temperature sensor arranged on the movable component through a cable, and controls the electric heating element to heat the movable component according to the temperature fed back by the movable component temperature sensor, and performs negative feedback control on the temperature distribution on the movable component;

[0011] The speed reducer is connected to the heating bracket;

[0012] The servo motor is arranged on the speed reducer and is connected to the PLC controller through a cable. The PLC controller is connected to a heating bracket position sensor arranged on the heating bracket and the host computer through a cable;

[0013] The upper computer is connected to a movable component position sensor and a driving system of the movable component via a cable, and controls the rotation of the movable component via the driving system according to the position feedback from the movable component position sensor, thereby performing negative feedback control on the rotation position of the movable component;

[0014] The PLC controller can receive the position feedback from the movable part position sensor through the host computer, and then drive the reducer through the servo motor according to the position feedback from the heating bracket position sensor, drive the heating bracket to rotate, and perform negative feedback control on the position of the heating bracket, so that the heating bracket rotates synchronously with the movable part.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft movable component ground verification test follow-up heating device, the electric heating element includes a plurality of ceramic-end quartz lamp tubes, each of which is inserted into the wiring bus with a metal terminal through a high-temperature-resistant positive and negative wire, and is connected to the copper plate of the cable transfer panel, and further connected to the temperature controller;

[0016] The temperature controller is an output power adjustment device. According to the temperature feedback from the movable component temperature sensor on the movable component, the power of each ceramic end quartz lamp is adjusted in real time to achieve negative feedback control of the temperature distribution on the movable component.

[0017] The copper plate in the cable transfer panel passes through and is fixed on the electrical bakelite board, and insulation measures are provided between the copper plate and the electrical bakelite board.

[0018] According to at least one embodiment of the present application, in the above-mentioned follow-up heating device for ground verification test of movable parts of aircraft, the heating bracket is a plate-like structure, which is welded from 6061 series aluminum plates.

[0019] According to at least one embodiment of the present application, in the above-mentioned follow-up heating device for ground verification test of movable parts of an aircraft, the reducer is connected to the heating bracket via a rotating shaft;

[0020] One end of the rotating shaft is connected to the reducer through a coupling, and the other end is connected to the heating bracket through a flange.

[0021] According to at least one embodiment of the present application, in the above-mentioned follow-up heating device for ground verification test of movable parts of aircraft, the reducer is fixed on the base plate, a rotating shaft bracket is arranged on the base plate, two bearings are installed on the rotating shaft bracket, and the two bearings are sleeved on the rotating shaft.

[0022] According to at least one embodiment of the present application, in the follow-up heating device for ground verification test of the movable component of the aircraft, when the distance between the heating element and the movable component is less than the safety distance threshold, the PLC controller controls the heating bracket to stop rotating, and uploads the signal of the heating bracket stopping rotation to the host computer. After receiving the signal of the heating bracket stopping rotation, the host computer controls the movable component to stop rotating.

[0023] The present application has at least the following beneficial technical effects:

[0024] Provided is a follow-up heating device for ground verification test of the movable component of the aircraft, which can keep the relative position between the electric heating element and the movable component unchanged during the test, so as to ensure the accurate control of the temperature distribution on the movable component, effectively restore the thermal environment of the movable component during flight, and obtain reliable test results. Description of the Drawings

[0025] Figure 1 is a schematic diagram of the follow-up heating device for ground verification test of the movable component of the aircraft provided by the embodiment of the present application;

[0026] Wherein:

[0027] 1 - Electric heating element; 2 - Heating bracket; 3 - Temperature controller; 4 - Reducer; 5 - Servo motor; 6 - PLC controller; 7 - Host computer; 8 - Rotating shaft; 9 - Bottom plate; 10 - Rotating shaft bracket.

[0028] For better illustration of this embodiment, some contents in the drawings will be omitted, enlarged or reduced, which are only for exemplary illustration and should not be construed as a limitation to the present application. Detailed Embodiments

[0029] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application and not to limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the normal design.

[0030] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0031] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0032] A follow-up heating device for ground verification test of movable parts of aircraft, such as Figure 1 As shown, it includes an electric heating element 1, a heating bracket 2, a temperature controller 3, a reducer 4, a servo motor 5, a PLC controller 6, and a host computer 7.

[0033] The electric heating element 1 is arranged on a heating support 2 and is connected to a temperature controller 3 via a cable.

[0034] The temperature controller 3 is connected to the movable component temperature sensor provided on the movable component through a cable, and controls the electric heating element 1 to heat the movable component according to the temperature feedback from the movable component temperature sensor, thereby performing negative feedback control on the temperature distribution on the movable component.

[0035] The electric heating element 1 may specifically include a plurality of ceramic-end quartz lamp tubes, each of which is inserted into a wiring bus with a metal terminal through a high-temperature-resistant positive and negative wire, and is connected to a copper plate of a cable transfer panel, and further connected to a temperature controller 3. The temperature controller 3 is an output power adjustment device, which adjusts the power of each ceramic-end quartz lamp tube in real time according to the temperature feedback from a movable component temperature sensor on the movable component, thereby realizing negative feedback control of the temperature distribution on the movable component.

[0036] The copper plate in the cable transfer panel passes through and is fixed on the electrical bakelite board, and insulation measures are provided between the two.

[0037] The heating bracket 2 is used to support the electric heating element 1 and can be designed as a plate-like structure welded from 6061 series aluminum plates, which can reduce the weight of the heating device.

[0038] The reducer 4 is connected to the heating bracket 2 , and specifically, the reducer 4 can be designed to be connected to the heating bracket 2 via a rotating shaft 8 .

[0039] One end of the rotating shaft 8 is connected to the reducer 4 through a coupling, and the other end is connected to the heating bracket 2 through a flange.

[0040] The speed reducer 4 can be fixed on the bottom plate 9. A rotating shaft bracket 10 can be further arranged on the bottom plate 9. Two bearings are installed on the rotating shaft bracket 10, and the two bearings are sleeved on the rotating shaft 8.

[0041] The servo motor 5 is arranged on the speed reducer 4 and is connected to the PLC controller 6 through a cable. The PLC controller 6 is connected to a heating bracket position sensor arranged on the heating bracket 2 and a host computer 7 through a cable.

[0042] The host computer 7 is connected to a movable part position sensor arranged on the movable part and a drive system of the movable part through a cable. According to the position feedback by the movable part position sensor, the host computer 7 controls the rotation of the movable part through the drive system, and performs negative feedback control on the rotation position of the movable part.

[0043] The PLC controller 6 can receive the position feedback by the movable part position sensor through the host computer 7. Then, according to the position feedback by the heating bracket position sensor, the PLC controller 6 drives the speed reducer 4 through the servo motor 5 to drive the heating bracket 2 to rotate, and performs negative feedback control on the position of the heating bracket 2, so that the heating bracket 2 rotates synchronously with the movable part, that is, the relative position between the heating bracket 2 and the movable part remains unchanged, which means the relative position between the electric heating element 1 and the movable part remains unchanged. Thus, it can ensure the accurate control of the temperature distribution on the movable part, effectively restore the thermal environment of the movable part during flight, and thus reliable test results can be obtained.

[0044] The movable part position sensor and the heating bracket position sensor adopt angle sensors.

[0045] The ceramic-end quartz lamp tube is a fragile device. If the relative position error between the heating element 1 and the movable part exceeds the safety distance during the movement process, the ceramic-end quartz lamp tube is likely to be damaged and endanger the safety of personnel.

[0046] To ensure the safety during the synchronous movement of the heating element 1 and the movable part, a communication protection mechanism between the PLC controller 6 and the host computer 7 is designed. When the distance between the heating element 1 and the movable part is less than the safety distance threshold, that is, when the relative distance calculated from the position feedback by the movable part position sensor and the position feedback by the heating bracket position sensor is less than the safety distance threshold, the safety distance threshold can be set according to the actual test situation, aiming to ensure that the ceramic-end quartz lamp tube is not damaged. Specifically, it can be taken as 2 / 3 of the safety distance. The PLC controller 6 controls the heating bracket 2 to stop rotating and uploads the signal of the heating bracket 2 stopping rotating to the host computer 7. After receiving the signal of the heating bracket 2 stopping rotating, the host computer 7 controls the movable part to stop rotating, performs troubleshooting. After troubleshooting, the system is restarted and the test continues.

[0047] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. A follow-up heating device for ground verification test of movable parts of aircraft, characterized in that: It comprises an electric heating element (1), a heating bracket (2), a temperature controller (3), a reducer (4), a servo motor (5), a PLC controller (6), and a host computer (7); The electric heating element (1) is arranged on the heating support (2) and is connected to the temperature controller (3) via a cable; The temperature controller (3) is connected to a movable component temperature sensor provided on the movable component via a cable, and controls the electric heating element (1) to heat the movable component according to the temperature feedback from the movable component temperature sensor, thereby performing negative feedback control on the temperature distribution on the movable component; The reducer (4) is connected to the heating bracket (2); The servo motor (5) is arranged on the reducer (4) and is connected to the PLC controller (6) via a cable. The PLC controller (6) is connected to a heating support position sensor arranged on the heating support (2) and a host computer (7) via a cable. The upper computer (7) is connected to a movable component position sensor provided on the movable component and a driving system of the movable component through a cable, and controls the rotation of the movable component through the driving system according to the position feedback from the movable component position sensor, thereby performing negative feedback control on the rotation position of the movable component; The PLC controller (6) can receive the position feedback from the movable component position sensor through the host computer (7), and then drive the reducer (4) through the servo motor (5) according to the position feedback from the heating bracket position sensor, so as to drive the heating bracket (2) to rotate, and perform negative feedback control on the position of the heating bracket (2), so that the heating bracket (2) rotates synchronously with the movable component.

2. The aircraft movable component ground verification test follow-up heating device according to claim 1, characterized in that: The electric heating element (1) comprises a plurality of ceramic-end quartz lamp tubes, each of which is inserted into a wiring bus with a metal terminal through a high-temperature-resistant positive and negative lead wire, and connected to a copper plate of a cable transfer panel, and further connected to a temperature controller (3); The temperature controller (3) is an output power adjustment device, which adjusts the power of each ceramic end quartz lamp in real time according to the temperature feedback from the movable component temperature sensor on the movable component, thereby realizing negative feedback control of the temperature distribution on the movable component; The copper plate in the cable transfer panel passes through and is fixed on the electrical bakelite board, and insulation measures are provided between the copper plate and the electrical bakelite board.

3. The aircraft movable component ground verification test follow-up heating device according to claim 2, characterized in that: The heating support (2) is a plate-shaped structure formed by welding 6061 series aluminum plates.

4. The aircraft movable component ground verification test follow-up heating device according to claim 3, characterized in that: The reducer (4) is connected to the heating support (2) via a rotating shaft (8); One end of the rotating shaft (8) is connected to the reducer (4) via a coupling, and the other end is connected to the heating bracket (2) via a flange.

5. The follow-up heating device for ground verification test of aircraft movable parts according to claim 4, characterized in that: The reducer (4) is fixed on a base plate (9), a rotating shaft bracket (10) is arranged on the base plate (9), two bearings are installed on the rotating shaft bracket (10), and the two bearings are sleeved on the rotating shaft (8).

6. The follow-up heating device for ground verification test of aircraft movable parts according to claim 5, characterized in that: When the distance between the heating element (1) and the movable part is less than the safety distance threshold, the PLC controller (6) controls the heating support (2) to stop rotating, and uploads a signal indicating that the heating support (2) has stopped rotating to the host computer (7). After receiving the signal indicating that the heating support (2) has stopped rotating, the host computer (7) controls the movable part to stop rotating.

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