CN112319849A

CN112319849A - Method for detecting surface damage of aircraft air inlet

Info

Publication number: CN112319849A
Application number: CN202110015616.6A
Authority: CN
Inventors: 张良; 崔明宝; 王文良
Original assignee: Beijing Tianchuang Kairui Technology Co ltd
Current assignee: Beijing Tianchuang Kairui Technology Co ltd
Priority date: 2021-01-07
Filing date: 2021-01-07
Publication date: 2021-02-05
Anticipated expiration: 2041-01-07
Also published as: CN112319849B

Abstract

The invention relates to the field of airplane detection, in particular to a method for detecting surface damage of an airplane air inlet. The method comprises the following steps: establishing a rectangular coordinate system by taking an inlet plane of the air inlet passage as an X-Y plane and the central axis direction of the air inlet passage as a Z direction; the method comprises the following steps that a surface damage detection device obtains the distance from each point on the surface of a standard air inlet to a central axis to form a standard surface three-dimensional curve graph; the method comprises the following steps that surface damage detection equipment obtains the distance from each point on the surface of an air inlet to be detected to a central axis, and a three-dimensional curve graph of the detection surface is formed; and comparing the standard surface three-dimensional curve graph with the detection surface three-dimensional curve graph to judge the surface damage of the air inlet to be detected. The detection method provided by the invention converts the damage condition of the surface of the air inlet into a digital expression form, so that the surface damage of the air inlet can be embodied more visually, and the detection accuracy and reliability of the surface damage of the air inlet of the airplane are improved.

Description

Method for detecting surface damage of aircraft air inlet

Technical Field

The invention relates to the field of airplane detection, in particular to a method for detecting surface damage of an airplane air inlet.

Background

In the process of aircraft inspection, the inspection of an aircraft air inlet passage is one of the key points of ground service inspection, and the inspection of whether the surface of the aircraft air inlet passage is damaged mainly comprises the steps of inspecting whether rivets are complete or not, whether parts are loosened or not, whether foreign matters exist or not and the like.

At present, the traditional inspection method is to carry out manual visual inspection through ground staff, namely, during inspection, the inspection staff drills into the air inlet channel to carry out visual inspection. Because human eyes have limited resolving power, tiny damage of the air inlet channel cannot be detected, so that the detection result is inaccurate, and the detection reliability is low.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is to overcome the defects of inaccurate inspection result and low reliability of manual visual inspection of the aircraft air inlet in the prior art, thereby providing a method for detecting the surface damage of the aircraft air inlet.

In order to solve the technical problems, the technical scheme adopted by the invention is as follows:

a method for detecting surface damage of an aircraft air inlet comprises the following steps:

establishing a rectangular coordinate system by taking an inlet plane of the air inlet passage as an X-Y plane and the central axis direction of the air inlet passage as a Z direction;

controlling the surface damage detection equipment to enter the standard air inlet channel along the central axis direction of the standard air inlet channel;

the method comprises the following steps that a surface damage detection device obtains the distance from each point on the surface of a standard air inlet to a central axis to form a standard surface three-dimensional curve graph;

controlling the surface damage detection equipment to enter the air inlet to be detected along the central axis direction of the air inlet to be detected;

the method comprises the following steps that surface damage detection equipment obtains the distance from each point on the surface of an air inlet to be detected to a central axis, and a three-dimensional curve graph of the detection surface is formed;

and comparing the standard surface three-dimensional curve graph with the detection surface three-dimensional curve graph to judge the surface damage of the air inlet to be detected.

Optionally, the surface damage detection apparatus includes:

a support frame;

the shape of the annular bracket is the same as that of the inlet of the air inlet;

the scanning radars are arranged on the annular support and are used for measuring the distance between each point on the surface of the air inlet channel and the central axis;

the feeding assembly is mounted on the support frame, is assembled with the annular support and is used for driving the annular support to move along the central axis of the air inlet channel, and when the annular support moves, the central axis of the annular support is superposed with the central axis of the air inlet channel;

and the controller is electrically connected with the scanning radar and the feeding assembly and is used for controlling the scanning radar and the feeding assembly to work.

Optionally, the feeding assembly includes:

the mounting seat is mounted on the supporting frame;

one end of the rack is assembled with the mounting seat in a sliding mode, and the other end of the rack is assembled with the annular bracket;

the gear is arranged on the mounting seat and meshed with the rack;

the encoder is arranged on the gear and rotates along with the rotation of the gear;

the decoder is arranged on the mounting seat and used for receiving and processing the signals sent by the encoder;

and the driving source is arranged on the mounting seat, is assembled with the gear and is used for driving the gear to rotate.

Optionally, the annular bracket is detachably assembled with the rack.

Optionally, the annular support is provided with a mounting shaft, the mounting shaft is located on a central axis of the annular support, the mounting shaft is provided with a containing groove, and the surface damage detection device further includes a locking assembly, and the locking assembly is used for locking or unlocking the annular support and the rack when the rack is contained in the containing groove.

Optionally, a clamping groove is formed at an end of the rack, and the locking assembly includes:

the clamping plates are positioned in the accommodating grooves and hinged with the mounting shaft, the free ends of the clamping plates can rotate around the hinged shaft to be close to or far away from the bottom walls of the accommodating grooves, the clamping plates correspond to the clamping grooves one by one, and the clamping plates are accommodated in the clamping grooves when the racks are locked with the mounting shaft;

and one end of the torsion spring is assembled with the clamping plate, the other end of the torsion spring is assembled with the mounting shaft, and when the torsion spring is in an initial state, the clamping plate and the side wall of the accommodating groove form a preset inclination angle.

Optionally, at least two card slots are provided.

Optionally, when the torsion spring is in the initial state, the free end of the clamping plate faces the bottom wall of the accommodating groove.

Optionally, the locking assembly further comprises a force application rod, and the force application rod is assembled with the clamping plate and used for driving the clamping plate to rotate around the hinge shaft.

The technical scheme of the invention has the following advantages:

1. according to the method for detecting the surface damage of the aircraft air inlet, the standard surface three-dimensional curve graph and the detection surface three-dimensional curve graph of the air inlet are obtained by the surface damage detection equipment, and the surface damage of the air inlet is judged by comparing the standard surface three-dimensional curve graph and the detection surface three-dimensional curve graph.

2. The invention provides a method for detecting the surface damage of an aircraft air inlet, wherein surface damage detection equipment comprises a support frame, an annular support, a scanning radar, a feeding assembly and a controller, when the surface of the air inlet is detected, the annular support is only needed to be arranged at a coordinate origin of an inlet of the air inlet, then the feeding assembly is controlled by the controller to move forward, the scanning radar arranged on the annular support is driven to continuously scan the surface of the air inlet, so that the distance from the surface of the air inlet to the central axis of the air inlet is measured, a surface three-dimensional curve graph can be formed, the distance from each point on the surface of the air inlet to the central axis is measured by the scanning radar, and the detection.

3. According to the method for detecting the damage to the surface of the aircraft inlet, the feeding assembly is internally provided with the gear rack, so that the annular support moves more stably in the Z-axis direction, and the annular support can move more accurately in the Z-axis direction through setting of the encoder and the decoder.

4. According to the method for detecting the surface damage of the aircraft inlet, the annular support and the rack are detachably assembled, so that the surface damage detection equipment can adapt to the inlets with different shapes and specifications for detection by replacing the annular support, and the application of the detection method is expanded.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic flowchart of a method for detecting surface damage of an aircraft inlet according to embodiment 1 of the present invention;

fig. 2 is a schematic structural view of a surface damage detection apparatus in embodiment 1 of the present invention;

fig. 3 is a schematic structural view of a feed assembly in embodiment 1 of the present invention;

fig. 4 is an assembly view of the mounting shaft and the rack in embodiment 1 of the present invention;

fig. 5 is a schematic view showing the assembly of the force application rod and the chucking plate in embodiment 1 of the present invention.

Description of reference numerals:

1. a support frame; 2. an annular support; 21. installing a shaft; 211. a containing groove; 3. scanning a radar; 4. a feed assembly; 41. a mounting seat; 42. a rack; 421. a card slot; 43. a gear; 44. a drive source; 5. a controller; 6. a locking assembly; 61. clamping a plate; 611. a chute; 62. a torsion spring; 63. a force application rod.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Example 1

With reference to fig. 1 to 5, the present embodiment relates to a method for detecting surface damage of an aircraft air inlet, which is mainly applied to surface damage detection of a straight line portion of an air inlet, and specifically includes the following steps:

s1, establishing a rectangular coordinate system by taking the inlet plane of the air inlet as an X-Y plane and the central axis direction of the air inlet as a Z direction;

s2, controlling the surface damage detection equipment to enter the standard air inlet channel along the central axis direction of the standard air inlet channel;

s3, the surface damage detection equipment obtains the distance from each point on the surface of the standard air inlet to the central axis to form a standard surface three-dimensional curve graph;

s4, controlling the surface damage detection equipment to enter the air inlet to be detected along the central axis direction of the air inlet to be detected;

s5, the surface damage detection equipment obtains the distance from each point on the surface of the air inlet to be detected to the central axis, and a three-dimensional curve graph of the detection surface is formed;

and S6, comparing the standard surface three-dimensional curve graph with the detection surface three-dimensional curve graph to judge the surface damage of the air inlet to be detected.

The comparison means that the standard surface three-dimensional graph and the detection surface three-dimensional graph are overlapped, if the standard surface three-dimensional graph and the detection surface three-dimensional graph can be completely overlapped in an error range, no surface damage exists, and the position where the standard surface three-dimensional graph and the detection surface three-dimensional graph cannot be overlapped proves that the surface damage exists.

According to the method for detecting the surface damage of the aircraft inlet, the surface damage detection equipment is used for obtaining the standard surface three-dimensional curve graph and the detection surface three-dimensional curve graph of the inlet, and then the surface damage of the inlet is judged through comparison between the standard surface three-dimensional curve graph and the detection surface three-dimensional curve graph.

In the present embodiment, the adopted surface damage detection device includes a support frame 1, an annular support 2, a plurality of scanning radars 3, a feeding assembly 4, and a controller 5.

Support frame 1 is the main part bearing structure of surface damage check out test set, the shape of ring carrier 2 is the same with aircraft intake duct entry shape, scanning radar 3 is provided with a plurality of, scanning radar 3 installs on each equant point on ring carrier 2, scanning radar 3 is used for surveing the distance between intake duct surface each point and the intake duct axis, it installs on support frame 1 to feed subassembly 4 one end, the other end assembles with ring carrier 2 mutually, it removes to feed subassembly 4 is used for driving ring carrier 2 along the axis direction of intake duct, and when ring carrier 2 removed, the axis of ring carrier 2 and the axis coincidence of intake duct, controller 5 is connected with scanning radar 3 and feed subassembly 4 electricity all, controller 5 is used for controlling scanning radar 3 and feeds subassembly 4 work.

When the distance from each point on the surface of the air inlet channel to the central axis of the air inlet channel is to be measured, firstly, the annular support 2 is placed at the position where the central axis of the annular support 2 coincides with the central axis of the air inlet channel, namely, the origin of coordinates on a coordinate system of the air inlet channel, then the controller 5 controls the feeding assembly 4 to work, the feeding assembly 4 drives the annular support 2 to gradually move along the central axis direction of the air inlet channel so as to gradually go deep, in the process that the annular support 2 moves along the central axis direction of the air inlet channel, the scanning radar 3 continuously scans, the distance from the scanning radar 3 to the surface of the air inlet channel is obtained, and the distance from the surface of the air inlet channel to.

In the embodiment, the feeding assembly 4 is fixedly assembled with the support frame 1, and the shape of the annular bracket 2 and the shape of the inlet of the aircraft air inlet are formed in an equal-scaled reduction mode.

Optionally, in the present embodiment, the feeding assembly 4 includes a mounting seat 41, a rack 42, a gear 43, an encoder, a decoder, and a driving source 44. The mounting seat 41 is mounted on the supporting frame 1, one end of the rack 42 is slidably assembled with the mounting seat 41, the other end of the rack is assembled with the annular bracket 2, the gear 43 is mounted on the mounting seat 41, the gear 43 is meshed with the rack 42, the encoder is mounted on the gear 43 and rotates along with the rotation of the gear 43, the decoder is mounted on the mounting seat 41 and used for receiving and processing signals sent by the encoder, the driving source 44 is mounted on the mounting seat 41, the driving source 44 is assembled with the gear 43, and the driving source 44 is used for driving the gear 43 to rotate.

When the annular assembly is required to gradually penetrate into the air inlet channel, the controller 5 is only required to control the driving source 44 to work, the driving source 44 drives the gear 43 to rotate, and the gear 43 is meshed with the rack 42, so that the rack 42 gradually moves forwards under the action of the gear 43, the annular support 2 is driven to move forwards, and the arrangement of the gear 43 and the rack 42 can enable the annular support 2 to move forwards more stably and with higher accuracy. The encoder and the decoder are arranged to realize digital conversion of Z-axis direction displacement of each point on the surface of the air inlet channel. In the present embodiment, the driving source 44 is a motor. In this embodiment, a flexible telescopic tube for protecting the rack 42 is covered outside the rack 42, and the telescopic tube is a corrugated tube.

Preferably, in order to enable the surface damage detection device to be suitable for airplane air inlets with different shapes for detection, in the embodiment, the annular bracket 2 and the rack 42 are detachably assembled, so that the annular bracket 2 with different specifications can be replaced to match different air inlet shapes.

In this embodiment, the annular bracket 2 is provided with the mounting shaft 21, the mounting shaft 21 is mounted on the central axis of the annular bracket 2, the mounting shaft 21 is provided with an accommodating groove 211, the rack 42 is movably accommodated in the accommodating groove 211 or separated from the accommodating groove 211, the surface damage detecting apparatus further includes a locking assembly 6, and the locking assembly 6 is used for locking or unlocking the rack 42 and the mounting shaft 21 when the rack 42 is accommodated in the accommodating groove 211.

In order to realize the quick detachment of the mounting shaft 21 from the rack 42, in this embodiment, a slot 421 is further formed at an end of the rack 42, and the locking assembly 6 includes a catch plate 61 and a torsion spring 62. The clamping plate 61 is located in the accommodating groove 211, the clamping plate 61 is hinged to the mounting shaft 21, the free end of the clamping plate 61 can rotate around the hinged shaft to be close to the bottom wall of the accommodating groove 211 or far away from the bottom of the accommodating groove 211, the clamping plates 61 correspond to the clamping grooves 421 one by one, and when the rack 42 is locked with the mounting shaft 21, the clamping plate 61 is accommodated in the clamping grooves 421; one end of the torsion spring 62 is mounted on the catch plate 61, and the other end is assembled with the mounting shaft 21, and when the torsion spring 62 is in the initial state, the catch plate 61 and the side wall of the accommodating groove 211 form a predetermined inclination angle, and the predetermined inclination angle is different from 0.

When the annular bracket 2 is to be installed, the rack 42 is only required to be inserted along the accommodating groove 211, the rack 42 gradually approaches the clamping plate 61 until abutting against the clamping plate 61 in the process of inserting the rack 42, then the rack 42 is continuously inserted, the clamping plate 61 rotates in the counterclockwise direction under the action of the rack 42, the torsion spring 62 elastically deforms, the clamping groove 421 moves to the position below the clamping plate 61 along with the continuous advance of the rack 42, at the moment, the abutting action of the rack 42 on the clamping plate 61 disappears, therefore, the pressure exerted on the torsion spring 62 is lost, the torsion spring 62 loses the external force compression and recovers the elastic deformation, the clamping plate 61 rotates clockwise under the action of the torsion spring 62 to be accommodated in the clamping groove 421 and abutted against the clamping groove 421, so as to complete the installation of the annular bracket 2, when the annular bracket 2 is to be disassembled, the annular bracket is only required to be pushed to move to one side where the gear 43 is firstly exerted by the external force, meanwhile, a simple tool is taken out and extends into the accommodating groove 211 to drive the clamping plate 61 to rotate to the free end of the clamping plate 61 to abut against the accommodating groove 211, so that the rack 42 can be drawn out, and then the tool is taken out, so that the clamping plate 61 can be restored to the original position under the action of the torsion spring 62.

In this embodiment, in order to make the engagement between the clamping plate 61 and the rack 42 more stable, at least two clamping grooves 421 are provided, and at the same time, when the torsion spring 62 is in the initial state, the free end of the clamping plate 61 faces the bottom wall of the accommodating groove 211.

In addition, in this embodiment, in order to facilitate the detachment of the ring-shaped support 2, a force applying rod 63 is further disposed in the locking assembly 6, a slider (not shown in the figure) is disposed on the force applying rod 63, a sliding slot 611 is disposed on a side of the catch plate 61, the sliding slot 611 extends from a hinged end of the catch plate 61 to a free end of the catch plate 61 along a length direction of the catch plate 61, the slider is slidably assembled with the sliding slot 611, the force applying rod 63 can move back and forth in the receiving slot 211 under an external force, and when the force applying rod 63 moves towards a bottom wall of the receiving slot 211, the slider is slidably assembled with the sliding slot 611, so that the catch plate 61 tends to rotate counterclockwise under the action of the slider. When dismantling ring carrier 2, only need exert thrust earlier to ring carrier 2, make ring carrier 2 remove to gear 43 place one side, exert external force simultaneously and promote the direction of application force pole 63 toward storage tank 211 diapire, under the drive of application force pole 63, the slider removes to the free end of cardboard 61 by the hinged end of cardboard 61 along spout 611 gradually, when the slider removes the free end to cardboard 61, the free end and the installation axle 21 butt of cardboard 61, can take out rack 42 this moment, after rack 42 takes out, relax application force pole 63, cardboard 61 can return the normal position under the effect of torsional spring.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.

Claims

1. A method for detecting surface damage of an aircraft inlet is characterized by comprising the following steps:

2. The detection method according to claim 1, wherein the surface damage detection apparatus comprises:

a support frame;

the feeding assembly is mounted on the support frame, is assembled with the annular support and is used for driving the annular support to move along the central axis direction of the air inlet channel, and when the annular support moves, the central axis of the annular support is superposed with the central axis of the air inlet channel;

3. The inspection method of claim 2, wherein the feed assembly comprises:

the mounting seat is mounted on the supporting frame;

the gear is arranged on the mounting seat and meshed with the rack;

4. The detection method according to claim 3, wherein the ring-shaped support is detachably assembled with the rack.

5. The detecting method according to claim 4, wherein the annular bracket is provided with a mounting shaft, the mounting shaft is located on a central axis of the annular bracket, the mounting shaft is provided with a receiving groove, and the surface damage detecting apparatus further comprises a locking assembly for locking or unlocking the mounting shaft and the rack when the rack is received in the receiving groove.

6. The detection method according to claim 5, wherein a slot is formed at an end of the rack, and the locking assembly comprises:

7. The detection method according to claim 6, wherein at least two card slots are provided.

8. The detecting method according to claim 7, wherein the free end of the clamping plate faces the bottom wall of the accommodating groove when the torsion spring is in the initial state.

9. The test method of claim 8, wherein the locking assembly further comprises an application lever, the application lever being assembled with the card for driving the card to rotate about a hinge axis.