A test system for detecting folding wing deployment time

Abstract

The present application relates to a kind of test system for detecting folding wing deployment time, belong to the field of detection equipment, solve the measurement precision of existing folding wing deployment time detection equipment is lower, cannot accurately measure the problems such as folding wing deployment time and synchronism.The test system of the present application, including: folding wing fixed component, support column, wing piece bundle release component and test circuit;Folding wing fixed component is used to fix the folding wing to be detected;Wing piece bundle release component is used to lock or release the wing piece of folding wing;Folding wing fixed component is installed with in-place photoelectric sensor;Support column is provided with unlocking photoelectric sensor;Unlocking photoelectric sensor and in-place signal sensor are used to acquire the unlocking signal and in-place signal of wing piece, test circuit is used to process unlocking signal and in-place signal and calculate and obtain wing piece deployment time and different time.This application realizes the detection of the wing piece deployment time and deployment consistency of folding wing.

Description

Technical Field

[0001] This invention relates to the field of testing equipment technology, and more particularly to a testing system for detecting the deployment time of folding wings. 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 traditional testing systems commonly used to detect the deployment time of folding wings 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 testing device 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 testing system for detecting the deployment time of folding wings, in order to solve the problem that existing folding wing deployment time detection equipment has low measurement accuracy and cannot accurately measure the deployment time and synchronization of folding wings.

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

[0007] A testing system for detecting the deployment time of a folding wing, characterized in that it comprises: a folding wing fixing assembly, a support column, a winglet assembly, and a testing circuit;

[0008] The folding wing fixing assembly is used to fix the folding wing to be tested;

[0009] The winglet assembly is used to lock or release the winglets of the folding wing;

[0010] The folding wing fixing assembly is equipped with a positioning photoelectric sensor, which is used to detect whether the wing has been fully deployed.

[0011] The support column is disposed between the folding wing fixing assembly and the winglet bundling assembly; the support column is provided with an unlocking photoelectric sensor, which is used to detect whether the winglet bundling assembly releases the winglets;

[0012] The unlocking photoelectric sensor and the positioning signal sensor are used to collect the unlocking signal and positioning signal of the wing respectively. The test circuit is used to process the unlocking signal and positioning signal and calculate the wing deployment time and asynchronous time.

[0013] Furthermore, when the folding wing is in the folded state, the wing flap bends downward and blocks the unlocking photoelectric sensor; when the folding wing is in the unfolded state, the wing flap blocks the positioning photoelectric sensor.

[0014] Furthermore, the folding wing fixing assembly includes: a folding wing fixing pressure plate, a sensor fixing bracket, and a folding wing fixing base plate; the folding wing fixing pressure plate is arranged parallel to the folding wing fixing base plate, and the main structure of the folding wing is pressed and fixed between the folding wing fixing base plate and the folding wing fixing pressure plate; the sensor fixing bracket is fixedly installed on the folding wing fixing base plate, and the positioning photoelectric sensor is fixedly installed on the sensor fixing bracket.

[0015] Furthermore, the number of sensor fixing brackets is the same as the number of winglets of the folding wing, and the sensor fixing brackets are circumferentially arranged on the folding wing fixing base plate.

[0016] Furthermore, the upper end of the support column is fixedly connected to the folding wing fixing base plate, and the lower end of the support column is fixedly connected to the connecting flange of the wing bundle assembly.

[0017] Furthermore, the vane beam assembly further includes: a vane beam base plate; the vane beam base plate is disposed above the connecting flange and is slidably connected to the connecting flange; the vane beam base plate is capable of sliding up and down relative to the connecting flange.

[0018] Furthermore, the wing-shaped beam-forming substrate has an annular structure. When the wing-shaped beam-forming substrate slides downward, it can release the wing by releasing its restraining effect.

[0019] Furthermore, the vane beam assembly also includes an electric push rod; the electric push rod is used to drive the vane beam substrate to move relative to the connecting flange.

[0020] Furthermore, the testing system also includes: a cabinet; the connecting flange is fixedly installed on the upper mounting plate of the cabinet.

[0021] Furthermore, a display window panel is installed on the support column; the display window panel serves as a display module for displaying the deployment time and asynchronous time of each wing; the display window panel includes 5 sets of LED digital tubes.

[0022] The technical solution of this invention can achieve at least one of the following effects:

[0023] 1. The test system for detecting the deployment time of a folding wing of the present invention records the release time and deployment time of the wing by using an unlock photoelectric sensor and a positioning photoelectric sensor, respectively, thereby enabling the monitoring of the deployment time of the wing.

[0024] 2. The test system for monitoring the deployment time of a folding wing of the present invention is equipped with a winglet assembly to lock, limit, and unlock the winglets of the folding wing, thereby realizing automatic control of the deployment of the winglets; and the winglet assembly of the present invention is driven by an electric push rod, ensuring the reliability and safety of the entire testing process.

[0025] 3. The test system for monitoring the deployment time of a folding wing according to the present invention sets up multiple sets of positioning photoelectric sensors according to the number of winglets of the folding wing. By monitoring the deployment time of multiple winglets through multiple positioning photoelectric sensors, the system realizes the detection of the deployment consistency of multiple winglets of the folding wing mechanism.

[0026] 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

[0027] 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.

[0028] Figure 1 This is a schematic diagram of the test system for detecting the deployment time of a folding wing according to the present invention;

[0029] Figure 2 The detection mechanism of the test system for detecting the deployment time of folding wings according to the present invention;

[0030] Figure 3 The folding wing fixing component of the test system for detecting the deployment time of a folding wing according to the present invention;

[0031] Figure 4 The support column of the test system for detecting the deployment time of a folding wing according to the present invention;

[0032] Figure 5 This is the locked state of the winglet assembly of the test system for detecting the deployment time of a folding wing according to the present invention;

[0033] Figure 6 The unlocked state of the winglet assembly of the test system for detecting the deployment time of a folding wing according to the present invention;

[0034] Figure 7 for Figure 5 , Figure 6 The locking state of the locking assembly of the vane bundle assembly;

[0035] Figure 8 for Figure 7 The unlocking status of the locking component;

[0036] Figure 9 The cabinet of the test system for detecting the deployment time of folding wings according to the present invention;

[0037] Figure 10 This is a control flowchart of the folding wing deployment time test method of the present invention;

[0038] Figure 11 Timing diagram for unlock signal and arrival signal;

[0039] Figure 12 This is the circuit architecture diagram of the tester.

[0040] Figure label:

[0041] 1- Folding wing fixing assembly; 2- Support column; 3- Wing blade assembly; 4- Cabinet;

[0042] 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-First wing nut; 106-Position sensor mounting plate; 107-Positioning block;

[0043] 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;

[0044] 301-Connecting flange; 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;

[0045] 3071 - Guide shaft seat; 3072 - T-shaped limiting groove; 3073 - Guide shaft; 3074 - Locking pin; 3075 - Handle screw; 3076 - Fixing screw; 3077 - Return spring;

[0046] 401 - Upper mounting plate; 402 - Tester mounting hole; 403 - Casters. Detailed Implementation

[0047] 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.

[0048] One specific embodiment of the present invention discloses a test system for detecting the deployment time of a folding wing, such as... Figure 1 As shown, it includes a tester and cabinet 4.

[0049] The testing instrument includes: a folding wing fixing assembly 1, a support column 2, a winglet assembly 3, and a testing circuit.

[0050] like Figure 1 , Figure 2 , Figure 4 As shown, the tester is installed above cabinet 4. Specifically, the tester includes: a folding wing fixing assembly 1, a support column 2, and a wing assembly 3.

[0051] The folding wing fixing assembly 1 is used to fix the folding wing to be tested; the winglet bundling assembly 3 is used to lock or release the winglets of the folding wing; a positioning photoelectric sensor 102 is installed on the folding wing fixing assembly 1, and the positioning photoelectric sensor 102 is used to detect whether the winglets are deployed in place; a support column 2 is disposed between the folding wing fixing assembly 1 and the winglet bundling assembly 3; an unlocking photoelectric sensor 206 is provided on the support column 2, and the unlocking photoelectric sensor 206 is used to detect whether the winglet bundling assembly 3 releases the winglets.

[0052] When in use, the folding wing is in the folded state, the main structure of the folding wing is clamped and fixed by the folding wing fixing component 1, the wing flap is bent downward and the wing flap blocks the unlocking photoelectric sensor 206 on the support column 2; when the folding wing is in the unfolded state, the wing flap blocks the positioning photoelectric sensor 102.

[0053] The testing system of the present invention can monitor the deployment time of the winglets by recording the release time and deployment time of the winglets respectively through the unlock photoelectric sensor 206 and the positioning photoelectric sensor 102.

[0054] The composition and working principle of the testing system of this invention are explained in five parts below:

[0055] (1) Part 1: Folding Wing Fixing Assembly

[0056] In one specific embodiment of the present invention, the folding wing fixing assembly 1 includes: a folding wing fixing pressure plate 101, a sensor fixing bracket 103, and a folding wing fixing base plate 104; the folding wing fixing pressure 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 pressure 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.

[0057] Furthermore, the number of sensor fixing brackets 103 is the same as the number of winglets of the folding wing, and the sensor fixing brackets 103 are circumferentially arranged on the folding wing fixing base plate 104.

[0058] Specifically, such as Figure 3 As 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.

[0059] 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.

[0060] Furthermore, the positioning photoelectric sensor 102 has a C-shaped structure with a concave groove. When the winglet is deployed into position, it can be engaged in the groove of the positioning photoelectric sensor 102.

[0061] 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.

[0062] When securing the folding wings:

[0063] First, the main structure of the folding wing is placed above the folding wing fixing base plate 104, and the circumferential orientation of the folding wing is adjusted to align with the positioning plate 107. Next, a folding wing fixing plate 101 is installed above 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 plate 101. Finally, a wing nut 105 is installed on the screw, and the wing nut 105 is tightened to clamp and fix the folding wing between the folding wing fixing plate 101 and the folding wing fixing base plate 104.

[0064] (2) Part Two: Supporting Columns

[0065] like Figure 2 As shown, the folding wing fixing assembly 1 and the winglet assembly 3 are parallel to each other and are connected by a support column 2. Specifically, the upper end of the support column 2 is fixedly connected to the folding wing fixing base plate 104, and the lower end of the support column 2 is fixedly connected to the connecting flange 301 of the winglet assembly 3.

[0066] like Figure 4 As 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 internally integrates the control module, electrical components, and cables of 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.

[0067] Specifically, 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.

[0068] When the wing is in the locked state, the unlocking photoelectric sensor 206 is blocked; when the wing is in the unlocked state, the unlocking photoelectric sensor 206 is not blocked. The unlocking photoelectric sensor 206 starts working when the wing is released, and sends a deployment signal to the control module when the wing is released.

[0069] Furthermore, the test circuit of the test device is installed inside the support column 2. The test circuit controls the test device of the present invention and processes the unlocking signal and positioning signal collected by the release photoelectric sensor 206 and the positioning photoelectric sensor 102 to calculate the wing deployment time and the asynchronous time.

[0070] (3) Part Three: Wing Bundle Assembly

[0071] The wing bundle assembly 3 further includes: a wing bundle substrate 302; the wing bundle substrate 302 is disposed above the connecting flange 301 and is slidably connected to the connecting flange 301; the wing bundle substrate 302 is capable of sliding up and down relative to the connecting flange 301.

[0072] In one specific embodiment of the present invention, the vane beam assembly substrate 302 is slidably mounted on the connecting flange 301 via a linear bearing 303 and a guide slide rod 304. The vane beam assembly substrate 302 and the connecting flange 301 are arranged parallel to each other. Specifically, as shown... Figure 5 , Figure 6 As shown, four sets of linear bearings 303 and guide slides 304 are arranged circumferentially along the circumferential direction of the vane beam distribution substrate 302. The linear bearings 303 are fixedly mounted on the connecting flange 301, and the guide slides 304 are fixedly mounted on the vane beam distribution substrate 302; the guide slides 304 are sleeved inside the linear bearings 303 and can slide relative to them.

[0073] In one specific embodiment of the present invention, the wing-shaped beam-forming substrate 302 has an annular structure. When the wing-shaped beam-forming substrate 302 slides downward, it can release the limiting effect on the wing and release the wing. Specifically, when the wing-shaped beam-forming substrate 302 is displaced relative to the connecting flange 301, the locking assembly 307 is displaced relative to the wing as a whole, thereby realizing the locking or unlocking of the wing.

[0074] The present invention ensures the stability of the relative displacement between the vane beam assembly substrate 302 and the connecting flange 301 by setting four sets of linear bearings 303 and guide slide rods 304, ensuring that the vane beam assembly substrate 302 only translates relative to the connecting flange 301 without deflection, thereby ensuring the synchronous unlocking of the vanes by the four sets of locking components 307 and ensuring the accuracy of the detection results.

[0075] Furthermore, the vane beam assembly 3 also includes an electric push rod 305; the electric push rod 305 is used to drive the vane beam substrate 302 to move relative to the connecting flange 301. Figure 5 , Figure 6 As shown, the electric push rod 305 is arranged parallel to the linear bearing 303 and the guide slide rod 304.

[0076] The installation method for the electric linear actuator 305 is as follows:

[0077] like Figure 5 , Figure 6As shown, the motion connecting rod 310 is fixedly mounted on the vane beam assembly base plate 302, and the push rod base 306 is fixedly mounted on the connecting flange 301. Specifically, two fixed connecting wing screw fixing seats 308 are fixedly mounted on the lower part of the vane beam assembly base plate 302, and the motion connecting rod 310 is fixedly connected between the two wing screw fixing seats 308 by bolts. The upper end of the electric push rod 305 is fixedly connected to the vane beam assembly base plate 302 through the motion connecting rod 310, and the lower end of the electric push rod 305 is fixedly connected to the connecting flange 301 through the push rod base 306.

[0078] When it is necessary to lock and limit the wing, the electric push rod 305 extends to move the wing bundle plate 302 upward. When it is necessary to unlock the wing, the electric push rod 305 retracts to move the wing bundle plate 302 downward.

[0079] Furthermore, to prevent accidental descent of the winglet beam distribution substrate 302 due to accidental contact, the present invention installs a wing screw 309 on the wing screw fixing seat 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 have 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 has safety positioning holes into which the wing screws 309 can be inserted.

[0080] During implementation, rotating the wing screw 309 allows it to insert into the safety positioning hole (not shown in the figure) of the support column 2, which restricts the relative displacement between the wing connecting flange 302 and the support column 2, thereby limiting the downward movement of the wing connecting flange 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 connecting flange 302 to be moved under the action of the electric push rod 305, thus unlocking the wing.

[0081] Specifically, the number and installation position of the locking components 307 correspond one-to-one with the number and position of the wing pieces of the folding wing mechanism.

[0082] In one specific embodiment of the present invention, such as 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.

[0083] Specifically, such as Figure 6 As shown, the guide shaft seat 3071 is fixedly installed below the blade bundle substrate 302.

[0084] Specifically, 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 return spring 3077 is sleeved on the lower part of the guide shaft 3073.

[0085] The upper end of the return spring 3077 abuts against the shoulder of the guide shaft 3073, and the lower end of the return spring 3077 abuts against the base plate of the guide shaft seat 3071.

[0086] The locking pin 3074 is fixedly installed above the guide shaft 3073 by a fixing screw 3076, and the locking pin 3074 is used to lock the wing.

[0087] Specifically, the folding wing mechanism includes a main structure and winglets; the winglets are rotatably mounted on the main structure. When the folding wing mechanism is in the folded state, the main structure is fixed by the folding wing fixing assembly 1, and the winglets are bent downwards and limited by the locking pin 3074.

[0088] In this invention, when the locking post 3074 limits the wing, that is, when the locking post 3074 is in the locked state, the locking post 3074 protrudes out of the wing bundle substrate 302 and can prevent the wing from unfolding.

[0089] Specifically, the guide shaft seat 3071 has a T-shaped limiting groove 3072 on its side; a handle screw 3075 is fixedly installed on the guide shaft 3073, and the handle screw 3075 is set perpendicular to the guide shaft 3073 and extends out from the T-shaped limiting groove 3072.

[0090] Specifically, the T-shaped limiting groove 3072 includes a transverse groove and a longitudinal groove that are interconnected.

[0091] Specifically, such as Figure 7 , Figure 8 As shown, when the handle screw 3075 slides in the longitudinal groove, it can drive the guide shaft 3073 and the locking pin 3074 to move up and down, thereby causing the locking pin 3074 to switch between locked and unlocked states.

[0092] When the handle screw 3075 is pressed down, the guide shaft 3073 moves downward relative to the guide shaft seat 3071, the return spring 3077 is compressed, and the locking pin 3074 moves downward synchronously with the guide shaft 3073, thereby unlocking the vane and allowing it to rotate freely. When the handle screw 3075 is released, the guide shaft 3073 moves upward under the elastic force of the return spring 3077, thereby locking the vane and restricting its rotation.

[0093] Specifically, when the handle screw 3075 is located at the highest point of the longitudinal groove or in the transverse groove, the locking pin 3074 is in a locked state; when the locking pin 3074 is located at the lowest point of the longitudinal groove, the locking pin 3074 is in an unlocked state. When the locking pin 3074 is in the locked state, the wing cannot rotate freely; when the locking pin 3074 is in the unlocked state, the wing can rotate freely.

[0094] During implementation:

[0095] The winglet deployment assembly 3 has two states: the initial state and the release state, which correspond to the winglet being ready to deploy and the release action, respectively.

[0096] Initial state: When the winglet release assembly 3 is in the initial state, the winglet is to be released. At this time, the locking assembly 307 is in the locked state, and its handle screw 3075 is stuck in the T-shaped limiting groove 3072, ensuring that the locking pin 3074 will not release the winglet due to external force. At this time, the winglet is locked and limited by the locking assembly 307, and the release photoelectric sensor 206 is kept in a state of close contact and blockage.

[0097] Unlocking and Release: When performing the wing deployment test, the wing screw 309 must first be pulled out of the safety positioning hole. Then, power is applied to trigger the unlocking and release switch. The electric push rod 305 of the wing deployment assembly 3 drives the wing deployment base plate 302 downward through the motion connecting rod 310, which in turn drives the four sets of locking assemblies 307 downward. When the locking pins 3074 of the locking assembly 307 move to the end of the wing, they lose their locking effect, and the four sets of winglets are released simultaneously, completing the deployment. The unlocking photoelectric sensor 206 starts working when the winglets are released, sending a deployment signal to the control module when the winglets are released.

[0098] Wing reset: Press down the handle screw 3075 to lower the locking pin 3074, then press down the wing of the folding wing mechanism and bring it close to the release photoelectric sensor 206. Loosen the handle screw 3075, and the spring force of the reset spring 3077 will reset the guide shaft 3073 and the locking pin 3074 to lock the wing. Pull the handle screw 3075 into the transverse groove of the T-shaped limit groove 3072 to prevent the guide shaft 3073 and the locking pin 3074 from moving down, thus achieving reliable locking.

[0099] This invention features a wing deployment assembly 3 to ensure the synchronous deployment of the four wings. It employs a highly sensitive photoelectric sensor to measure the unlocking and positioning signals of the wing mechanism and uses an STM32 timer capture function to measure the wing deployment time, achieving high measurement accuracy down to the microsecond level.

[0100] Furthermore, the testing system also includes: cabinet 4.

[0101] Specifically, the connecting flange 301 of the wing bundle assembly is fixedly installed on the upper mounting plate 401 of the cabinet 4.

[0102] like Figure 1 , Figure 9 As shown, the upper mounting plate 401 is provided with a tester mounting hole 402. The connecting flange 301 is fixedly installed on the upper mounting plate 401 of the cabinet 4, and the tester mounting hole 402 is used to avoid the moving parts of the wing bundle assembly 3.

[0103] Furthermore, due to the limited internal space of the support column 2, the interior of the cabinet 4 is used to house the electrical components of the test circuit of this invention. Specifically, the support column 2 has a cylindrical structure with a central cavity, and the central cavity is connected to the internal space of the cabinet 4 to facilitate cable arrangement.

[0104] Furthermore, slots are cut on both sides of the lower end of the support column 2 to allow the movement of the motion connecting rod 310 to pass.

[0105] Furthermore, casters 403 are provided at the bottom of the cabinet 4 to facilitate the transfer of the testing device of the present invention.

[0106] (4) Part Four: Test Circuit

[0107] Specifically, such as Figure 12 As shown, the test circuit consists of a control module, a display module, a detection module, and a power supply module.

[0108] 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.

[0109] 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.

[0110] 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.

[0111] The display module is a display window panel 201; the display module consists of 5 sets of LED digital tubes, which can display the deployment time and asynchronous time of each wing.

[0112] Furthermore, the present invention includes a winglet bundle assembly 3 to ensure the synchronous deployment of the four winglets, employs a highly sensitive photoelectric sensor to measure the unlocking signal and positioning signal of the winglet mechanism, and uses an STM32 timer capture function to measure the winglet deployment time, achieving high measurement accuracy down to the microsecond level.

[0113] The usage procedure of the testing device of the present invention is as follows: Figure 10 As shown.

[0114] First, after the folding wing is installed and limited, the power switch 204 is pressed to power on the folding wing deployment time testing device, thus activating the monitoring device. Then, the winglet bundle substrate 302 is moved downward by the electric push rod 305, thereby unlocking the winglets. After the winglets are unlocked, the unlocking time of each winglet is recorded by the level change of the release photoelectric sensor 206; when the release photoelectric sensor 206 detects the first unlocking signal, the timer is started.

[0115] like Figure 10 As shown, the arrival time of each winglet is recorded by the level change of the positioning photoelectric sensor 102; the timer is turned off when the positioning photoelectric sensor 102 detects the last positioning signal.

[0116] As shown in Table 1, the release photoelectric sensor 206 and the positioning photoelectric sensor 102 are at a low level when blocked by the winglets and at a high level when not blocked by the winglets. Before the winglets unlock, the winglets block the unlock photoelectric sensor 206, causing it to be at a low level, while the positioning photoelectric sensor 102 is at a high level. After the winglets deploy to their positions, the winglets block the positioning photoelectric sensor 102, causing the unlock photoelectric sensor 206 to be at a high level and the positioning photoelectric sensor 102 to be at a low level. The control module records the unlocking and positioning times of each winglet based on the level changes of the unlock photoelectric sensor 206 and the positioning photoelectric sensor 102.

[0117] Table 1. Truth Table of State Logic for Photoelectric Sensors

[0118] 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

[0119] Furthermore, based on the measured unlocking and positioning times of each winglet, the control module processes the unlocking and positioning signals to calculate the deployment time Ti of each winglet, the unlocking time difference Ts of multiple winglets, and the positioning time difference Te.

[0120] like Figure 11 As shown, the measurement system of this invention employs a timer capture principle. Specifically, the unlocking signal and the positioning signal of the four blades are both rising edge signals after passing through the detection circuit. Figure 12As shown, the unlock signal and the position signal are acquired by different channels of the timer. The unlock signals output by the four unlock photoelectric sensors 206 are detected by the OR gate circuit to start the timing, and the four unlock signals are captured 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 times of each winglet. The maximum time difference of winglet release is the winglet release asynchronous time Ts, and the maximum time difference of winglet deployment is the winglet deployment asynchronous time Te.

[0121] like Figure 11 As shown, 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 of the folding wing.

[0122] like Figure 11 As shown, 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.

[0123] like Figure 11 As shown, the asynchronous time Te of wing deployment 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 102.

[0124] Furthermore, the control module controls the display module to display; specifically, 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.

[0125] 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.

[0126] 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 testing system for detecting the deployment time of a folding wing, characterized in that, include: The system comprises a folding wing fixing assembly, a support column, a winglet deployment assembly, and a testing circuit. The folding wing fixing assembly is used to fix the folding wing to be tested. The winglet deployment assembly is used to lock or release the winglets of the folding wing. A positioning photoelectric sensor is installed on the folding wing fixing assembly to detect whether the winglets are fully deployed. The support column is located between the folding wing fixing assembly and the winglet deployment assembly. An unlocking photoelectric sensor is installed on the support column to detect whether the winglet deployment assembly releases the winglets. The unlocking photoelectric sensor and the positioning photoelectric sensor are used to collect unlocking signals and positioning signals of the winglets, respectively. The testing circuit processes the unlocking signals and positioning signals and calculates the winglet deployment time and asynchronous time. The winglet bundle assembly includes: a connecting flange, a winglet bundle base plate, an electric push rod, and a locking assembly; the winglet bundle base plate is disposed above the connecting flange and is slidably connected to the connecting flange; the winglet bundle base plate has an annular structure; the electric push rod is used to drive the winglet bundle base plate to move relative to the connecting flange; when the winglet bundle base plate slides downward, it can release the limiting effect on the winglets and release the winglets; 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 below the winglet bundle expansion substrate; the guide shaft is slidably installed 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 installed above the guide shaft; the locking pin protrudes from the winglet bundle expansion substrate and can prevent the winglets from unfolding; a T-shaped limiting groove is provided on the side of the guide shaft seat; the T-shaped limiting groove includes a transverse groove and a longitudinal groove that are interconnected; a handle screw is fixedly installed on the guide shaft, the handle screw is set perpendicular to the guide shaft and extends out of the T-shaped limiting groove; when the handle screw slides in the longitudinal groove, it can drive the guide shaft and the locking pin to move up and down, so that the locking pin switches between a locked state and an unlocked state.

2. The test system for detecting the deployment time of a folding wing according to claim 1, characterized in that, When the folding wing is in the folded state, the wing flap bends downward and blocks the unlocking photoelectric sensor; when the folding wing is in the unfolded state, the wing flap blocks the positioning photoelectric sensor.

3. The test system for detecting the deployment time of a folding wing according to claim 1 or 2, characterized in that, The folding wing fixing assembly includes: a folding wing fixing plate, a sensor fixing bracket, and a folding wing fixing base plate; the folding wing fixing plate is arranged parallel to the folding wing fixing base plate, and the main structure of the folding wing is pressed and fixed between the folding wing fixing base plate and the folding wing fixing plate; the sensor fixing bracket is fixedly installed on the folding wing fixing base plate, and the positioning photoelectric sensor is fixedly installed on the sensor fixing bracket.

4. The test system for detecting the deployment time of a folding wing according to claim 3, characterized in that, The number of sensor mounting brackets is the same as the number of winglets of the folding wing, and the sensor mounting brackets are circumferentially arranged on the folding wing mounting base plate.

5. The test system for detecting the deployment time of a folding wing according to claim 4, characterized in that, The upper end of the support column is fixedly connected to the folding wing fixing base plate, and the lower end of the support column is fixedly connected to the connecting flange of the wing bundle assembly.

6. The test system for detecting the deployment time of a folding wing according to claim 5, characterized in that, The testing system also includes a cabinet; the connecting flange is fixedly installed on the upper mounting plate of the cabinet.

7. The test system for detecting the deployment time of a folding wing according to any one of claims 1-6, characterized in that, A display window panel is installed on the support column; the display window panel serves as a display module for displaying the deployment time and asynchronous time of each wing.

Images