A method of testing folding wing deployment time

Abstract

The present application relates to a kind of folding wing deployment time test method, belong to product detection field, solve the low precision of the wing piece deployment time test of folding wing in prior art.The present application is tested using folding wing deployment time test device, the test method includes the following steps: step S1: the folding wing to be detected is fixed to folding wing fixed component and is fixed, and the wing piece is locked and positioned by wing piece bundle group component;Step S2: unlock folding wing;The wing piece of folding wing is unfolded, and the release time of wing piece is monitored by release photoelectric sensor;Step S3: when folding wing unfolds, the in-place time of each wing piece is monitored by in-place photoelectric sensor.The present application realizes the release time and in-place time of wing piece are monitored, and the unfolding time and unfolding consistency of wing piece are detected.

Description

Technical Field

[0001] This invention relates to the field of product testing technology, and in particular to a method for testing the unfolding time of a folding wing. Background Technology

[0002] As a component for adjusting the flight attitude of an aircraft, the folding wing deployment mechanism requires the use of relevant testing equipment to calculate key performance parameters such as the folding wing deployment time, ensuring that the aircraft's folding mechanism deploys synchronously and in place.

[0003] Currently, the commonly used traditional folding wing deployment time testing devices are expensive, have complex data processing, and low measurement accuracy, making them unable to accurately measure the deployment time and synchronization of folding wings.

[0004] Therefore, a new detection method is needed to detect the deployment time of the folding wings of an aircraft and the synchronization of the deployment of multiple winglets, thereby improving the detection accuracy. Summary of the Invention

[0005] Based on the above analysis, the present invention aims to provide a method for testing the deployment time of folding wings, in order to solve the problems of low measurement accuracy and inability to accurately measure the deployment time and synchronization of folding wings in existing folding wing testing methods.

[0006] The objective of this invention is mainly achieved through the following technical solutions:

[0007] A method for testing the deployment time of a folding wing, using a folding wing deployment time testing device, includes the following steps:

[0008] Step S1: Install the folding wing to be tested onto the folding wing fixing assembly and lock and limit the wing using the wing extension assembly;

[0009] Step S2: Unlock the folding wing; the wing flaps unfold, and the release signal of the flaps is monitored by releasing the photoelectric sensor;

[0010] Step S3: When the folding wing unfolds, the positioning signal of each wing piece is monitored by the positioning photoelectric sensor;

[0011] Step S4: Record the trigger times of the release signal and the position signal using the timer of the test circuit, and then calculate the deployment time of the winglets.

[0012] Furthermore, in step S2, before the wing is unlocked, the wing blocks the unlocking photoelectric sensor, the unlocking photoelectric sensor is at a low level, and the positioning photoelectric sensor is at a high level; in step S3, after the wing is deployed to the position, the wing blocks the positioning photoelectric sensor, the unlocking photoelectric sensor is at a high level, and the positioning photoelectric sensor is at a low level.

[0013] Furthermore, in step S4, a timer is started when the release photoelectric sensor detects the first unlock signal; the timer records the unlocking time of each winglet by the level change of each release photoelectric sensor.

[0014] Furthermore, in step S4, the timer records the arrival time of each winglet by the level change of each positioning photoelectric sensor; the timer is turned off when the positioning photoelectric sensor detects the last positioning signal.

[0015] Furthermore, in step S4, based on the unlocking time and arrival time of each winglet measured by the timer, the deployment time Ti of each winglet, the unlocking time difference Ts of multiple winglets, and the arrival time difference Te are calculated.

[0016] Furthermore, in step S4, the deployment time Ti, the wing unlocking asynchronous time Ts, and the wing deployment asynchronous time Te of each wing are displayed by multiple digital tubes on the display window panel on the supporting column.

[0017] Furthermore, the unfolding time Ti of the wing is the difference between the wing's arrival time and the unlocking time; where i is the number of multiple winglets; the value of i is a natural number greater than or equal to 1; the maximum value of i is determined according to the number of winglets in the folding wing.

[0018] Furthermore, the wing unlocking asynchronous time Ts is the difference between the acquisition time of the last wing unlocking signal and the acquisition time of the first wing unlocking signal.

[0019] Furthermore, the winglet deployment asynchronous time Te is the acquisition time of the last winglet arrival signal minus the acquisition time of the first winglet arrival signal; the acquisition time of the winglet arrival signal is the time when the winglet arrives at the corresponding positioning photoelectric sensor.

[0020] Furthermore, in step S4, after one test is completed, pressing the reset switch will clear the multiple digital tubes on the display window; repeat steps S1-S4 to test the unfolding time and synchronization of the next folding wing.

[0021] Furthermore, in step S1, the folding wing fixing assembly fixes the folding wing in the following way:

[0022] The folding wing fixing assembly includes: a folding wing fixing plate, a sensor fixing bracket, and a folding wing fixing base plate; the main structure of the folding wing is placed above the folding wing fixing base plate, and the folding wing fixing plate is installed above the folding wing; a vertical screw is provided on the folding wing fixing base plate, and the screw passes through the folding wing fixing plate; a wing nut is installed on the screw, and tightening the wing nut clamps and fixes the folding wing between the folding wing fixing plate and the folding wing fixing base plate.

[0023] Furthermore, in step S1, multiple sets of locking components are installed on the winglet assembly.

[0024] The winglet clustering assembly includes: a clustering base, a winglet clustering substrate, an electric push rod, and a locking assembly; the winglet clustering substrate is provided with a locking assembly, which is used to lock or unlock the winglets of the folding wing mechanism; the electric push rod is used to drive the winglet clustering substrate to move.

[0025] The locking assembly includes: a guide shaft seat, a guide shaft, a locking pin, and a return spring; the guide shaft seat is fixedly mounted on the winglet bundle substrate; the guide shaft is slidably mounted inside the guide shaft seat, and a return spring is provided between the guide shaft and the guide shaft seat; the locking pin is fixedly mounted above the guide shaft, and the locking pin is used to lock the winglet. A handle screw is fixedly mounted on the guide shaft, and a T-shaped limiting groove is provided on the guide shaft seat. The handle screw extends out of the T-shaped limiting groove and can slide along the T-shaped limiting groove; when the handle screw slides along the T-shaped limiting groove, the guide shaft slides linearly or rotates inside the guide shaft seat.

[0026] The method by which the winglet assembly locks and limits the winglets is as follows:

[0027] Step S11: Press down the handle screw of the locking assembly until it reaches the bottom of the T-shaped limiting groove; this causes the guide shaft to slide in the guide shaft seat, and at the same time drives the locking pin to move down, so that the locking pin is in the unlocked state.

[0028] Step S12: Bend the wing flaps of the folding wing so that the flaps are parallel to the support column and can block the release photoelectric sensor on the support column;

[0029] Step S13: Loosen the handle screw, and the guide shaft will move upward under the elastic force of the return spring. The locking pin will move upward to limit and lock the wing piece, restricting the rotation of the wing piece and completing the locking of the wing piece; Move the handle screw to make it engage in the transverse groove of the T-shaped limiting groove, restricting the displacement of the locking pin.

[0030] Step S14: Repeat steps S11 to S13 to complete the locking and limiting of multiple blades.

[0031] Furthermore, in step S2, the unlocking process of the winglet is as follows:

[0032] Step S21: Move the winglet bundle substrate downwards using an electric push rod;

[0033] Step S22: The winglet beam release substrate drives the locking assembly to move downwards as a whole;

[0034] Step S23: The locking pin of the locking assembly moves down to release the locking limit on the wing, and the wing is unlocked.

[0035] Furthermore, when the wing unlocks, the wing no longer folds to unlock the photoelectric sensor; the unlock photoelectric sensor detects the unlock signal of the wing.

[0036] Furthermore, the folding wing fixing assembly and the winglet assembly are connected by a support column; the support column is circumferentially equipped with multiple unlocking photoelectric sensors that cooperate with multiple winglets to monitor the unlocking time of multiple winglets.

[0037] Furthermore, in step S3, the monitoring process of the winglet positioning signal is as follows:

[0038] Step S31: After the winglets are unlocked, they automatically deploy;

[0039] Step S32: The positioning photoelectric sensor has a C-shaped structure with a concave groove; during the unfolding process of the wing, it gradually gets into the groove of the positioning photoelectric sensor;

[0040] Step S33: When the winglet is fully deployed, it is completely inserted into the groove of the positioning photoelectric sensor, thereby blocking the positioning photoelectric sensor, and the positioning photoelectric sensor detects the positioning signal of the winglet.

[0041] The technical solution of this invention can achieve at least one of the following effects:

[0042] 1. The folding wing deployment mechanism deployment time test method of the present invention has high measurement accuracy and can accurately measure the synchronicity of wing deployment.

[0043] 2. The folding wing deployment mechanism deployment time test method of the present invention adds a reliable locking component, which is convenient to implement. The symmetrical design ensures that the locking state of each wing is consistent. The wing release assembly structure design ensures the synchronicity of wing release.

[0044] 3. The folding wing deployment mechanism deployment time test method of the present invention uses a positioning photoelectric sensor to detect the release and positioning status of the wing, which is small in size and has high sensitivity and accuracy; it uses a timer hardware capture and count, which has high precision, reaching the microsecond level, and can calculate the deployment asynchronous time to obtain the deployment synchronization index.

[0045] 4. The folding wing deployment mechanism deployment time testing method of the present invention has the advantages of lower cost, simple and reliable data processing, high measurement accuracy, and can accurately measure wing deployment time and synchronization index compared with traditional wing deployment time testing devices such as high-speed cameras.

[0046] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0047] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0048] Figure 1 A folding wing deployment time testing device for implementing the folding wing deployment time testing method of the present invention;

[0049] Figure 2 for Figure 1 The test instrument for the folding wing deployment time test device in the middle;

[0050] Figure 3 for Figure 1 The folding wing fixing component of the folding wing deployment time test device in the middle;

[0051] Figure 4 for Figure 1 The support column of the folding wing deployment time test device in the middle;

[0052] Figure 5 for Figure 1 The locked state of the winglet bundle assembly in the folding wing deployment time test device;

[0053] Figure 6 for Figure 1 The unlocked state of the winglet bundle assembly of the folding wing deployment time test device in the middle;

[0054] Figure 7 for Figure 5 , Figure 6 The locking state of the locking assembly of the vane bundle assembly;

[0055] Figure 8 for Figure 7 The unlocking status of the locking component;

[0056] Figure 9 for Figure 1 The cabinet containing the folding wing deployment time test device;

[0057] Figure 10 This is a control flowchart of the folding wing deployment time test method of the present invention;

[0058] Figure 11Timing diagram for unlock signal and arrival signal;

[0059] Figure 12 This is the circuit architecture diagram of the tester;

[0060] Figure 13 To unlock the signal detection circuit;

[0061] Figure 14 For arrival signal detection circuit.

[0062] Figure label:

[0063] 1- Folding wing fixing assembly; 2- Support column; 3- Wing blade assembly; 4- Cabinet;

[0064] 101-Folding wing fixing plate; 102-Position photoelectric sensor; 103-Sensor fixing bracket; 1031-First stiffener; 1032-Second stiffener; 1033-Third stiffener; 1034-Fourth stiffener; 104-Folding wing fixing base plate; 105-Wing nut; 106-Position sensor mounting plate; 107-Positioning block;

[0065] 201 - Display window panel; 202 - Mounting hole for fixed components; 203 - Reset switch; 204 - Power switch; 205 - Unlock photoelectric mounting base; 206 - Unlock photoelectric sensor; 207 - Side cover;

[0066] 301- Bundle base; 302- Wing bundle base plate; 303- Linear bearing; 304- Guide slide bar; 305- Electric push rod; 306- Push rod base; 307- Locking assembly; 308- Wing screw holder; 309- Wing screw; 310- Motion connecting rod;

[0067] 3071 - Guide shaft seat; 3072 - T-shaped limiting groove; 3073 - Guide shaft; 3074 - Locking pin; 3075 - Handle screw; 3076 - Fixing screw; 3077 - Return spring;

[0068] 401 - Upper mounting plate; 402 - Tester mounting hole; 403 - Casters. Detailed Implementation

[0069] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0070] A specific embodiment of the present invention discloses a method for testing the deployment time of a folding wing, such as... Figure 1-14 As shown, the present invention uses a folding wing deployment time testing device to test the deployment time of the folding wing.

[0071] The testing method includes the following steps:

[0072] Step S1: Install the folding wing to be tested onto the folding wing fixing assembly 1 and fix it, and lock and limit the wing piece by the wing piece bundle assembly 3;

[0073] Step S2: Unlock the folding wing; the wing flaps unfold, and the release signal of the flaps is monitored by the release photoelectric sensor 206;

[0074] Step S3: When the folding wing unfolds, the positioning signal of each wing piece is monitored by the positioning photoelectric sensor 102;

[0075] Step S4: Record the trigger times of the release signal and the position signal using the timer of the test circuit, and then calculate the deployment time of the winglets.

[0076] The test method of the present invention is as follows: Figure 10 As shown; in step S1, after the folding wing is installed and limited, the power switch 204 is pressed to power on the folding wing unfolding time testing device and start the monitoring device.

[0077] Furthermore, the release photoelectric sensor 206 and the positioning photoelectric sensor 102 are at a low level when blocked by the wing and at a high level when not blocked by the wing.

[0078] In step S2, before the winglet unlocks, the winglet blocks the unlocking photoelectric sensor 206, causing the unlocking photoelectric sensor 206 to be at a low level and the positioning photoelectric sensor 102 to be at a high level. In step S3, after the winglet deploys to its position, the winglet blocks the positioning photoelectric sensor 102, causing the unlocking photoelectric sensor 206 to be at a high level and the positioning photoelectric sensor 102 to be at a low level.

[0079] like Figure 10 As shown, in step S4, a timer is started when the release photoelectric sensor 206 detects the first unlock signal.

[0080] In step S4, the timer records the unlocking time of each winglet by the level change of each release photoelectric sensor 206; the timer records the arrival time of each winglet by the level change of each position photoelectric sensor 102; the timer is turned off when the position photoelectric sensor 102 detects the last position signal.

[0081] Furthermore, in step S4, based on the unlocking time and arrival time of each winglet measured by the timer, the deployment time Ti of each winglet, the unlocking time difference Ts of multiple winglets, and the arrival time difference Te are calculated.

[0082] Furthermore, in step S4, the deployment time Ti, the wing unlocking asynchronous time Ts, and the wing deployment asynchronous time Te of each wing are displayed by multiple digital tubes on the display window panel 201 on the support column 2.

[0083] Furthermore, the unfolding time Ti of the wing is the difference between the wing's arrival time and the unlocking time; where i is the number of multiple winglets; the value of i is a natural number greater than or equal to 1; the maximum value of i is determined according to the number of winglets in the folding wing.

[0084] Furthermore, the wing unlocking asynchronous time Ts is the difference between the acquisition time of the last wing unlocking signal and the acquisition time of the first wing unlocking signal.

[0085] Furthermore, the winglet deployment asynchronous time Te is the acquisition time of the last winglet arrival signal minus the acquisition time of the first winglet arrival signal; the acquisition time of the winglet arrival signal is the time when the winglet arrives at the corresponding positioning photoelectric sensor 102.

[0086] Furthermore, after pressing the reset switch 203, the multiple digital tubes on the display window 201 are cleared; repeat steps S1-S4 to test the unfolding time and synchronization of the next folding wing.

[0087] The specific implementation methods for each step are explained below:

[0088] (I) Step S1:

[0089] Furthermore, in step S1, the folding wing fixing assembly 1 fixes the folding wing in the following way:

[0090] like Figure 3 As shown, the folding wing fixing assembly 1 includes: a folding wing fixing plate 101, a sensor fixing bracket 103, and a folding wing fixing base plate 104; the folding wing fixing plate 101 is arranged parallel to the folding wing fixing base plate 104, and the main structure of the folding wing is pressed and fixed between the folding wing fixing base plate 104 and the folding wing fixing plate 101; the sensor fixing bracket 103 is fixedly installed on the folding wing fixing base plate 104, and the positioning photoelectric sensor 102 is fixedly installed on the sensor fixing bracket 103. A screw is vertically arranged on the folding wing fixing base plate 104; the folding wing fixing plate 101 is provided with a through hole; the folding wing fixing plate 101 is sleeved on the screw through the through hole, and a wing nut 105 is installed on the portion of the screw protruding from the folding wing fixing plate 101.

[0091] Specifically, such as Figure 3As shown, the sensor mounting bracket 103 includes: a first stiffener 1031, a second stiffener 1032, a third stiffener 1033, and a fourth stiffener 1034; wherein, the first stiffener 1031 and the fourth stiffener 1034 are arranged at an angle, and the included angle between the first stiffener 1031 and the fourth stiffener 1034 is the same as the included angle between adjacent winglets. The lower end of the second stiffener 1032 is fixedly connected to the folding wing mounting base plate 104, and its left and right ends are fixedly connected to the first stiffener 1031 and the fourth stiffener 1034 respectively. The third stiffener 1033 connects the first stiffener 1031 and the fourth stiffener 1034.

[0092] Specifically, the two ends of the sensor mounting bracket 103 are fixedly mounted to the sensor mounting plate 106 by screws, and the position photoelectric sensor 102 is fixedly mounted on the position sensor mounting plate 106.

[0093] Specifically, a positioning plate 107 is also provided on the folding wing fixing base plate 104. The positioning plate 107 is aligned with the positioning point on the folding wing and is used to position the folding wing on the folding wing fixing assembly 1 to ensure that the wing and the positioning photoelectric sensor 102 are aligned, so that the wing can be precisely inserted into the groove of the positioning photoelectric sensor 102 when it is unfolded.

[0094] When fixing the folding wing: First, place the main structure of the folding wing on top of the folding wing fixing base plate 104, and install the folding wing fixing pressure plate 101 on top of the folding wing; a vertical screw is provided on the folding wing fixing base plate 104, and the screw passes through the folding wing fixing pressure plate 101; then, install a wing nut 105 on the screw, and tighten the wing nut 105 to clamp and fix the folding wing between the folding wing fixing pressure plate 101 and the folding wing fixing base plate 104.

[0095] Furthermore, in step S1, multiple sets of locking components 307 are installed on the winglet bundle assembly 3.

[0096] like Figure 5 , Figure 6 As shown, the winglet bundle assembly 3 includes: a bundle base 301, a winglet bundle base plate 302, an electric push rod 305, and a locking assembly 307; the winglet bundle base plate 302 is provided with the locking assembly 307, which is used to lock or unlock the winglets of the folding wing mechanism; the electric push rod 305 is used to drive the winglet bundle base plate 302 to move.

[0097] Furthermore, the vane beam assembly substrate 302 is slidably mounted on the beam assembly base 301 via a linear bearing 303 and a guide slide rod 304. Specifically, the linear bearing 303 is fixedly mounted on the beam assembly base 301, and the guide slide rod 304 is fixedly mounted on the vane beam assembly substrate 302; the guide slide rod 304 is sleeved inside the linear bearing 303 and can slide relative to it. The vane beam assembly substrate 302 has a ring structure; multiple sets of locking components 307 are provided and are circumferentially mounted on the vane beam assembly substrate 302.

[0098] like Figure 7 , Figure 8 As shown, the locking assembly 307 includes: a guide shaft seat 3071, a guide shaft 3073, a locking pin 3074, and a return spring 3077; the guide shaft seat 3071 is fixedly mounted on the winglet bundle base plate 302; the guide shaft 3073 is slidably mounted inside the guide shaft seat 3071, and a return spring 3077 is provided between the guide shaft 3073 and the guide shaft seat 3071; the locking pin 3074 is fixedly mounted above the guide shaft 3073 by a fixing screw 3076, and the locking pin 3074 is used to lock the winglet.

[0099] A handle screw 3075 is fixedly installed on the guide shaft 3073, and a T-shaped limiting groove 3072 is provided on the guide shaft seat 3071. The handle screw 3075 extends out of the T-shaped limiting groove 3072 and can slide along the T-shaped limiting groove 3072. When the handle screw 3075 slides along the T-shaped limiting groove 3072, the guide shaft 3073 slides linearly or rotates inside the guide shaft seat 3071.

[0100] The method by which the winglet assembly 3 locks and limits the winglets is as follows:

[0101] Step S11: Press down the handle screw 3075 of the locking assembly 307, pressing the handle screw 3075 down to the bottom of the T-shaped limiting groove 3072; causing the guide shaft 3073 to slide in the guide shaft seat 3071, while driving the locking pin 3074 to move down, so that the locking pin 3074 is in the unlocked state.

[0102] Step S12: Bend the wing flaps of the folding wing so that the flaps are parallel to the support column 2 and can block the release photoelectric sensor 206 on the support column 2;

[0103] Step S13: Loosen the handle screw 3075. Under the elastic force of the return spring 3077, the guide shaft 3073 moves upward, and the locking pin 3074 moves upward to limit and lock the wing piece, restricting the rotation of the wing piece and completing the locking of the wing piece; Move the handle screw 3075 to make it engage in the transverse groove of the T-shaped limiting groove 3072 to limit the displacement of the locking pin 3074.

[0104] Step S14: Repeat steps S11 to S13 to complete the locking and limiting of multiple blades.

[0105] (II) Step S2:

[0106] To unlock the winglets, this invention incorporates an electric push rod 305 that displaces the winglet assembly substrate 302. For example... Figure 5 As shown, the upper end of the electric push rod 305 is fixedly connected to the winglet beaming substrate 302 via the motion connecting rod 310, and the lower end of the electric push rod 305 is fixedly connected to the beaming base 301 via the push rod base 306.

[0107] Specifically, such as Figure 5 , Figure 6 As shown, the motion connecting rod 310 is fixedly mounted on the winglet bundled base plate 302, and the push rod base 306 is fixedly mounted on the bundled base 301; the upper end of the electric push rod 305 is fixedly connected to the motion connecting rod 310, and the lower end is fixedly connected to the push rod base 306. When it is necessary to lock and limit the winglet, the electric push rod 305 extends to drive the winglet bundled base plate 302 upward; when it is necessary to unlock the winglet, the electric push rod 305 retracts to drive the winglet bundled base plate 302 downward.

[0108] Furthermore, in step S2, the unlocking process of the winglet is as follows:

[0109] Step S21: The winglet bundle substrate 302 is moved downward by the electric push rod 305;

[0110] Step S22: The winglet beam distribution substrate 302 drives the locking assembly 307 to move downward as a whole;

[0111] Step S23: The locking pin 3074 of the locking assembly 307 moves down to release the locking limit on the wing, and the wing is unlocked.

[0112] Furthermore, when the wing is unlocked, the wing no longer folds the unlocking photoelectric sensor 206; the unlocking photoelectric sensor 206 detects the unlocking signal of the wing.

[0113] Furthermore, such as Figure 2 As shown, the folding wing fixing assembly 1 and the winglet bundle assembly 3 are connected by a support column 2; the support column 2 is circumferentially equipped with multiple unlocking photoelectric sensors 206 that cooperate with multiple winglets to monitor the unlocking time of multiple winglets.

[0114] Furthermore, such as Figure 4As shown, the upper part of the support column 2 is provided with a mounting hole 202 for fixing the folding wing fixing base plate 104; the side of the support column 2 is provided with a reset switch 203, a power switch 204, an unlocking photoelectric mounting base 205, an unlocking photoelectric sensor 206, and a side cover 207. The support column 2 integrates electrical components and cables for the test circuit; the side cover 207 is connected to the support column 2 by screws and is detachable, facilitating maintenance of the internal circuitry.

[0115] like Figure 4 As shown, the outer surface of the support column 2 is provided with multiple sets of unlocking photoelectric mounting bases 205 and unlocking photoelectric sensors 206 corresponding to the number and position of the wing pieces. The unlocking photoelectric mounting bases 205 are fixedly mounted on the support column 2, and the unlocking photoelectric sensors 206 are fixedly mounted on the unlocking photoelectric mounting bases 205. When the folding wing is in the folded state, the wing pieces block the unlocking photoelectric sensors 206.

[0116] (III) Step S3:

[0117] Furthermore, in step S3, the monitoring process of the winglet positioning signal is as follows:

[0118] Step S31: After the winglets are unlocked, they automatically deploy;

[0119] Step S32: The positioning photoelectric sensor 102 has a C-shaped structure with a concave groove; during the unfolding process of the wing, it gradually gets into the groove of the positioning photoelectric sensor 102;

[0120] Step S33: When the winglet is fully deployed, it is completely inserted into the groove of the positioning photoelectric sensor 102, thereby blocking the positioning photoelectric sensor 102. The positioning photoelectric sensor 102 detects the positioning signal of the winglet.

[0121] Furthermore, the two ends of the motion connecting rod 310 are fixedly connected to wing screw fixing seats 308, and are fixedly installed below the wing bundle expansion substrate 302 by the two wing screw fixing seats 308. To prevent accidental descent of the wing bundle expansion substrate 302 due to accidental contact, the present invention installs wing screws 309 on the wing screw fixing seats 308. Specifically, as Figure 6 As shown, two wing screw holders 308 and a moving connecting rod 310 form a C-shaped structure. The wing screw holders 308 are provided with threaded holes, and the wing screws 309 are positioned perpendicular to the wing screw holders 308 and connected to them via threads. Correspondingly, the support column 2 is provided with wing screw positioning holes, into which the wing screws 309 can be inserted.

[0122] During implementation, rotating the wing screw 309 allows it to insert into the wing screw positioning hole, which restricts the relative displacement between the wing-shaped expansion substrate 302 and the support column 2, thereby limiting the downward movement of the wing-shaped expansion substrate 302 and preventing accidental wing deployment from affecting measurement accuracy or injuring personnel. When it is necessary to perform an deployment test on the folding wing, unscrewing the wing screw 309 allows the wing-shaped expansion substrate 302 to be moved under the action of the electric push rod 305, thus unlocking the wing.

[0123] like Figure 1 , Figure 9 As shown, the testing device further includes: a cabinet 4; the bundle-laying base 301 is fixedly mounted on the upper mounting plate 401 of the cabinet 4. The upper mounting plate 401 is provided with a tester mounting hole 402, which is used to avoid moving parts of the blade bundle-laying assembly 3. The cabinet 4 is used to house the electrical components required to implement the testing method of the present invention. Casters 403 are provided at the bottom of the cabinet 4 for moving the testing device of the present invention.

[0124] (IV) Step S4:

[0125] Furthermore, in step S4 shown, control and signal processing are performed through a test circuit.

[0126] The circuit architecture of the test circuit is as follows: Figure 12 As shown, the test circuit specifically consists of a control module, a display module, a detection module, and a power supply module.

[0127] The power module consists of an AC / DC power supply, which outputs a +12V power supply to power the detection module and the control module.

[0128] The detection module includes eight photoelectric sensors, including four unlocking photoelectric sensors 206 and four positioning photoelectric sensors 102; used to detect the unlocking and positioning status of winglets 1, 2, 3, and 4 and provide signals to the control module.

[0129] The control module includes a microprocessor and a timer. The timer is used to capture the unlocking and positioning times of the four winglets. The microprocessor uses an STM32F103, and the functional modules are initialized using STM32CubeMX. The program is designed using Keil C language on the MDK-ARM platform. The microprocessor can calculate the deployment time based on the unlocking and positioning signals of winglets 1, 2, 3, and 4 detected by the detection module and drive the display module to display the results.

[0130] The display module is a display window panel 201 set on the support column 2; the display module consists of 5 sets of LED digital tubes, which can display the deployment time and asynchronous time of each wing.

[0131] Furthermore, the unlock signal detection circuit is as shown in the attached diagram. Figure 13 As shown, the position signal detection circuit is as follows: Figure 14 As shown, this invention uses an STM32 timer to capture unlock and position signals. The timer's counting accuracy is at the microsecond level; therefore, the measurement accuracy of this invention can reach the microsecond level. The photoelectric sensor mainly completes the acquisition of unlock and position signals, and the microprocessor calculates the deployment time and asynchronous time of a single winglet, then converts the calculated results and displays them through the digital tube of the display window 201. Circuit design based on the test method of this invention is an operation that can be performed by those skilled in the art; therefore, it will not be described in detail here.

[0132] like Figure 11 , Figure 12 As shown, exemplarily, when the number of winglets is 4, the testing device of the present invention has a total of 8 photoelectric sensors, namely four unlocking photoelectric sensors 206 and four positioning photoelectric sensors 102. The four sets of sensors detect the unlocking and positioning status of the 4 winglets respectively.

[0133] The timing diagrams for the wing unlock signal and the positioning signal are attached. Figure 11 As shown, the timer starts counting when the first unlock signal is triggered and ends when the last winglet is in place. The release signal capture time for all four winglets is t_start. (i) The arrival signal acquisition time is t_end (i) .

[0134] As shown in Table 1, both the unlocking photoelectric sensor 206 and the positioning photoelectric sensor 102 are at a low level when obstructed by an obstacle, and at a high level when unobstructed. Before the winglet unlocks, the unlocking photoelectric sensor 206 is at a low level, and the positioning photoelectric sensor 102 is at a high level. After the winglet is in position, the unlocking photoelectric sensor 206 is at a high level, and the positioning photoelectric sensor 102 is at a low level. The unlocking and positioning status of the winglet can be determined based on the changes in the sensor output levels.

[0135] Table 1. Truth Table of State Logic for Photoelectric Sensors

[0136] Sensor number Wing number initial state Unlock In place Unlock Sensor 1 Wing 1 0 1 1 Unlock Sensor 2 No. 2 wing 0 1 1 Unlock Sensor 3 No. 3 wing 0 1 1 Unlock Sensor 4 No. 4 wing 0 1 1 Position sensor 1 Wing 1 1 1 0 Position sensor 2 No. 2 wing 1 1 0 Position sensor 3 No. 3 wing 1 1 0 Position sensor 4 No. 4 wing 1 1 0

[0137] The measurement method of this invention adopts the principle of timer and counter capture.

[0138] Specifically, such as Figure 13 , Figure 14 As shown, the unlocking signal and the positioning signal of the four blades are both rising edge signals after passing through the detection circuit. Figure 11 , Figure 12As shown, the unlock signal and the position signal are acquired by different channels of the timer; when the unlock signal output by the four unlock photoelectric sensors 206 is detected by the OR gate circuit, the timer starts and the timer captures the unlock signal in sequence; when the position photoelectric sensor 102 receives the position signal, the timer captures the position signal in sequence; the obtained pulse width durations T1, T2, T3, and T4 are the deployment time Ti of each wing, the maximum time difference of wing release is the wing release asynchronous time Ts, and the maximum time difference of wing deployment to position is the wing deployment asynchronous time Te.

[0139] The test method described in this invention measures the winglet deployment time Ti and the asynchronous time Ts / Te, each defined as follows:

[0140] 1) Definition 1: Wing deployment time T i

[0141] Ti = t_end (i) -t_start (i) , i = 1, 2, 3, 4.

[0142] In the above formula, T i t_start is the deployment time of winglet i. (i) t_end represents the detected unlocking time of winglet i. (i) The time of the i-th winglet's arrival signal is the difference between the two, which is the winglet deployment time.

[0143] 2) Definition 2: Asynchronous release time T of the winglets s

[0144] The maximum difference between the unlocking times of the four winglets is defined as the winglet release desynchronization time; that is, the winglet release desynchronization time T. s Subtract the acquisition time of the first wing unlock signal from the acquisition time of the last wing unlock signal.

[0145] Ts = max(t_start) (i) )-min(t_start (i) ), i = 1, 2, 3, 4.

[0146] In the above formula, max(t_start) (i) ) represents the latest winglet unlocking time, min(t_start) (i) This is the earliest time the winglets were unlocked. (See attached image.) Figure 11 , Figure 12 As shown.

[0147] 3) Definition 3: Asynchronous deployment time Te of winglets

[0148] The maximum difference in the arrival times of the four winglets is defined as the winglet deployment asynchronous time; that is, the winglet deployment asynchronous time Te is the acquisition time of the arrival signal of the last winglet minus the acquisition time of the arrival signal of the first winglet.

[0149] Te = max(t_end) (i) )-min(t_end (i) ), i = 1, 2, 3, 4.

[0150] In the above formula, max(t_end) (i) ) represents the latest time the winglet is in place, min(t_end) (i) (This refers to the earliest time the winglet reached its position.) See attached... Figure 11 , Figure 12 As shown.

[0151] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for testing the deployment time of a folding wing, characterized in that, The folding wing deployment time testing device is used for testing. The testing method includes the following steps: Step S1: The folding wing to be tested is installed and fixed on the folding wing fixing assembly, and the winglets are locked and limited by the winglet bundling assembly; Step S2: The folding wing is unlocked; the winglets of the folding wing are deployed, and the release signal of the winglets is monitored by the release photoelectric sensor; Step S3: When the folding wing is deployed, the position signal of each winglet is monitored by the position photoelectric sensor; Step S4: The trigger time of the release signal and the position signal is recorded by the timer of the test circuit, and then the deployment time of the winglets is calculated. In step S1, the winglet assembly includes: an assembly base, a winglet assembly substrate, an electric push rod, and a locking assembly; the winglet assembly substrate is provided with a locking assembly, which is used to lock or unlock the winglets of the folding wing mechanism; the electric push rod is used to drive the winglet assembly substrate to move; the locking assembly includes: a guide shaft seat, a guide shaft, a locking pin, and a return spring; the guide shaft seat is fixedly installed on the winglet assembly substrate; the guide shaft is slidably installed inside the guide shaft seat and a return spring is provided between them; the locking pin is fixedly installed above the guide shaft and is used to lock the winglets; a handle screw is fixedly installed on the guide shaft, and a T-shaped limiting groove is provided on the guide shaft seat; the handle screw extends out of the T-shaped limiting groove and can slide along the T-shaped limiting groove; when the handle screw slides along the T-shaped limiting groove, the guide shaft slides linearly or rotates inside the guide shaft seat; The method by which the winglet assembly locks and limits the winglets is as follows: Step S11: Press down the handle screw of the locking assembly to the bottom of the T-shaped limiting groove; the guide shaft slides in the guide shaft seat and moves the locking pin down, so that the locking pin is in the unlocked state; Step S12: Bend the winglets of the folding wing so that the winglets are parallel to the support column and can block the release photoelectric sensor; Step S13: Loosen the handle screw, the guide shaft moves upward under the elastic force of the return spring, the locking pin moves upward to limit and lock the winglets, restricting the rotation of the winglets and completing the locking of the winglets; Move the handle screw to make it engage in the transverse groove of the T-shaped limiting groove, restricting the displacement of the locking pin; Step S14: Repeat steps S11 to S13 to complete the locking and limiting of multiple winglets; In step S2, the unlocking process of the wing is as follows: Step S21: The wing bundle plate is moved down by the electric push rod; Step S22: The wing bundle plate moves down the locking assembly as a whole; Step S23: The locking pin of the locking assembly moves down to release the locking limit on the wing, and the wing is unlocked.

2. The method for testing the deployment time of a folding wing according to claim 1, characterized in that, In step S2, before the wing is unlocked, the wing blocks the unlock photoelectric sensor, the unlock photoelectric sensor is at a low level, and the position photoelectric sensor is at a high level; in step S3, after the wing is deployed to the position, the wing blocks the position photoelectric sensor, the unlock photoelectric sensor is at a high level, and the position photoelectric sensor is at a low level.

3. The method for testing the deployment time of a folding wing according to claim 2, characterized in that, In step S4, a timer is started when the photoelectric sensor detects the first unlock signal.

4. The method for testing the deployment time of a folding wing according to claim 3, characterized in that, In step S4, the timer records the unlocking time of each winglet by the level change of each unlocking photoelectric sensor; the timer records the arrival time of each winglet by the level change of each arrival photoelectric sensor; the timer is turned off when the arrival photoelectric sensor detects the last arrival signal.

5. The method for testing the deployment time of a folding wing according to claim 4, characterized in that, In step S4, based on the unlocking time and arrival time of each winglet measured by the timer, the deployment time Ti of each winglet, the unlocking time difference Ts of multiple winglets, and the arrival time difference Te are calculated.

6. The method for testing the deployment time of a folding wing according to claim 5, characterized in that, In step S4, the deployment time Ti, the wing unlocking asynchronous time Ts, and the wing deployment asynchronous time Te of each wing are displayed by multiple digital tubes on the display window panel on the supporting column.

7. The method for testing the deployment time of a folding wing according to claim 5 or 6, characterized in that, The unfolding time Ti of the wing is the difference between the wing's arrival time and the unlocking time; where i is the number of multiple winglets; the value of i is a natural number greater than or equal to 1; the maximum value of i is determined according to the number of winglets in the folding wing.

8. The method for testing the deployment time of a folding wing according to claim 5 or 6, characterized in that, The wing unlocking asynchrony time Ts is the difference between the acquisition time of the last wing unlocking signal and the acquisition time of the first wing unlocking signal.

9. The method for testing the deployment time of a folding wing according to claim 5 or 6, characterized in that, The wing deployment asynchronous time Te is the acquisition time of the last wing arrival signal minus the acquisition time of the first wing arrival signal; the acquisition time of the wing arrival signal is the time when the wing arrives at the corresponding positioning photoelectric sensor.

10. The method for testing the deployment time of a folding wing according to claim 1, characterized in that, In step S4, after one test is completed, pressing the reset switch will clear the multiple digital tubes on the display window; repeat steps S1-S4 to test the deployment time and synchronization of the next folding wing.

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